System and applications of lighter-than-air (lta) platforms

(54) Title: SYSTEM AND APPLICATIONS OF

LIGHTER THAN AIR (LTA) PLATFORMS (30) Unionist Priority: 30/09/2003 us 10 / 673,474 (71) Depositor (s): Space Data Corporation (US) (72) Inventor (s): Gerald M. Knoblach, Erica A. Frische, BruceA. Barkley (74) Attorney: Orlando de Souza (86) International Request: pct US2004 / 032206 of 30/09/2004 (87) International Publication: wo 2005/032936 of 14/04/2005 (57) Summary: SYSTEM AND APPLICATIONS OF PLATFORMS LIGHTER THAN AIR (LTA). Innovative new methods relating to floating clear of air (LTA) platforms, of facilitating legal operation of the transmitter, termination of the flight of the platform when appropriate, environmentally acceptable landing, and recovery of these devices are provided. New systems and methods relate to rise rate control, the geo-position of an LTA platform including 0 grounded payload and ground-based vehicle positions, and manageable recovery systems.

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SYSTEM Ε PLATFORM APPLICATIONS Lighter Than Air (LTA)

RELATED REQUESTS

This order claims the priority of previously filed US Order No. 10 / 673,474, which is part of a continuation of US Order No. 09 / 342,440, filed on June 29, 1999 and US Order No. 10 / 129,666, filed on May 9, 2002, which claims priority from US Provisional Application No. 60 / 284,799, filed on April 18, 2001, all of which are incorporated herein by reference.

TECHNICAL FIELD OF THE INVENTION

The present invention relates to lighter than unmanned air platforms operating in the stratosphere and, more particularly, their termination and recovery.

BACKGROUND OF THE INVENTION

Unmanned balloons lighter than air have been used for many years to perform tasks such as researching nearby space, and meteorological measurements. These balloons even transported payloads with instrumentation that sometimes included radio transmission capabilities.

Until recently, all communications satellites were located in an orbit called the geosynchronous arc, which is located 35888.4 km above the Earth's equator. Since international treaties required satellites to be spaced two degrees apart, there were only 180 locations in the geosynchronous orbit. An optimally engineered three-stage chemical rocket should typically have 94% propellant at launch for

2/125 reach geosynchronous orbit, which, after allocating about 5.6% of the weight to the rocket, leaves only 0.4% of the initial launch weight for the satellite. To put this in perspective, a typical 1361 kg car with the same performance would only be able to carry a 91 kg person, would need a 31.8 m fuel tank³ and would be discarded after a trip! Finally, while NASA's space shuttle can perform services on a few low-orbit satellites at great cost, most satellites cannot be maintained or upgraded after being launched.

Currently, since there are a limited number of locations in the geosynchronous orbit, geosynchronous satellites are growing in size and performance, now being able to broadcast television signals directly to homes. Recently, additional satellite networks have been developed, which do not require a geosynchronous orbit. All of these new networks have launched smaller communication satellites in much lower orbits, where there are an unlimited number of locations. Due to the fact that the satellites required for a network are more numerous and because the satellites are smaller, up to 8 satellites per rocket have been launched. Although satellites have become smaller and more numerous, there are still no personal satellites and no mass producer of consumer products in today's satellite industry. It could be estimated that a network of microsatellites in a low Earth orbit and equipment on the ground to accommodate monitoring, transmission, reception, signal transfer among the plurality of

3/125 microsatellites and the system network required for a voice system would cost at least $ 3 billion to employ. In four years of using a system, each of five million subscribers would be expected to invest as much as $ 3,000 in the equipment, resulting in a combined total investment by users in the new equipment of around $ 15 billion. The cost of employing a smaller system of advanced low-orbit Earth-sending satellites would be estimated at around $ 475 million. Such a system would be expected to serve two to three million subscribers, each with equipment costing $ 300 to $ 1000. Thus, the total investments by users for their equipment can be at least 600 million dollars.

Currently, there is an industry involving radiosondes for the purpose of accumulating climate information. Radiosondes are the instrument packages launched in climatological balloons for the accumulation of climatic data. Radiosondes are launched from a network of locations around the world at noon and midnight at Greenwich Mean Time each day. Weather service radiosondes collect data on temperature, humidity, pressure and wind as they rise from the Earth's surface to approximately 3 0.48 km during a two-hour flight. These data are then introduced into atmospheric models that are run on supercomputers. The accumulated information from the network of ascending radiosonde is critical in predicting the climate. Most countries in the world are bound by a treaty to launch radiosonde

4/125 from designated locations and to share data with other countries. Currently, there are around 800,000 radiosondes launched each year around the world. This number represents 997 global weather stations launching two radiosondes per day, 3,665 days per year (727,000) plus a small number of radiosondes launched for research purposes. About 18% of the radiosondes are recovered, reconditioned and regenerated, resulting in a new production of around 650,000 radiosondes for accumulating climate data per year.

The location systems currently used for monitoring climate balloons are either being deactivated (Omega, starting before 2000, and Loran-C, just after 2000), or are so old that operation and maintenance are becoming prohibitively low. expensive (radar and radioteodolites).

Changes in radiosonde systems are usually very slow, as meteorologists study climate trends by comparing data collected over decades. Thus, they are very alert to any changes that may introduce new directions in the data, as they are collected. This is evident from the fact that large users, such as the US National Weather Services (NWS), still use analog radiosondes accompanied by radioteodolites, when digital aided navigation probes have been around for many years. Tightening government budgets has made some users unable to pay for the new technology required. At present, there is an impetus in the probe market for conversion to the use of the Global Positioning System

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This new inability required for (GPS) wind tracking in radiosondes. From 1995 to 1998, the NWS tried and failed to obtain funding from the United States Congress for a program to develop a GPS tracking system for the United States Observation Network to obtain technology plus replacement of the old radiosonde infrastructure. and unsupportable is occurring simultaneously with the rapid reallocation of the radiosonde RF spectrum for commercial uses. Radiosondes traditionally transmitted at 400 MHz for navigation aid probes and 1680 MHz for radioteodolite probes. The 400 MHz band is being auctioned by the Federal Communications Commission (FCC) in the United States for simultaneous use by commercial services. Thus, interference is growing and waves can be forced to use narrower bandwidths with digital downlink instead of wide bandwidth with analog downlink still in common use.

Very large and expensive NASA balloons have been launched individually and maintained at a floating altitude for extended periods of time. These balloons carry hundreds of pounds of equipment and cost tens of thousands of dollars each. Single balloons do not have the ability to cover line of sight with entire geographic areas.

Personal communications services (PCS) are a new category of digital services, for which the FCC started the spectrum auction in 1994. The PCS is divided into two categories: broadband and narrowband PCS. The broadband category is primarily for broadband services

6/125 voice and PCS broadband phones currently compete with traditional cell phones. The narrowband category is for advanced message sending, which is essentially a two-way radio call. The radio call industry sees advanced messaging as a mobile extension of someone's email account, just as the cell phone has been the mobile extension of someone's landline. 0 National narrowband PCS (NPCS) was the first spectrum ever auctioned by the FCC. About 30 regional and national NPCS licenses were auctioned and sold to private commercial ventures. The fact that the spectrum was auctioned is significant in that there are fewer restrictions on the use of this spectrum than on the use of the traditional spectrum licensed by the FCC. Before the auctions, the FCC granted spectrum on a fragmented basis, and companies had to prove that they were using airwaves for the public good. There was usually very little federal regulation on how the frequency could be used. Once companies paid for their PCS licenses, they essentially owned the spectrum. The FCC only imposed minimum regulations required to prevent systems from interfering with systems from other utilities and other countries. In addition, the FCC and Industry Canada arrived at what is known as the Terrestrial Radio Communication Agreement and Arrangement, in which Canada allocated the same frequencies for NPCS with the same channel structure as the spectrum auctioned for NPCS in the United States. This made it possible for an NPCS across the border and, in 1996, at least one system company

7/125 radio call granted an NPCS license in Canada to operate on the same frequencies as its licensee in the United States. Mexico also specified the same channel spacing as used in the United States.

One of the FCC's goals is to encourage the provision of radio frequency (RF) communications services to consumers in rural areas at an affordable price. This market was largely ignored by the largest communications companies, because of the diminishing return on investment in the provision of wireless communications for sparingly occupied areas. These wireless services include radio call, advanced messaging, telemetry, voice, etc. Although both voice and message services are available for rural areas using satellite systems, the costs are usually in the thousands of dollars per unit and well out of reach for most consumers. In addition, satellite systems have problems in the provision of services in urban areas, because they lack the signal strength necessary for the provision of penetration into buildings.

SUMMARY OF THE INVENTION

The invention relates to an elevation rate control system for controlling the elevation rate of a platform lighter than free floating air comprising a ventilation actuator, an altitude sensor and a device that controls the ventilation actuator, when the elevation rate is greater than a predefined elevation rate. Preferably, the altitude sensor determines a free floating platform altitude and elevation rate, the device determines the rate

8/125 elevation and the device is located on the free floating platform. The system could further comprise a ballast container, a ballast and a ballast discharge actuator that controls a ballast discharge from the ballast container, when the lift rate is less than a particular lift rate.

Another modality is a method of controlling the rate of elevation of a platform lighter than free floating air by a rate control system of elevation comprising a ventilation actuator, an altitude sensor and a device that controls the actuator. of ventilation, when the elevation rate is greater than a predefined elevation rate, the method comprising determining the elevation rate and controlling the elevation rate. Preferably, the lift rate comprises ventilation of the ventilation actuator by the device. Preferably, the elevation rate control system further comprises a ballast container, a ballast and a ballast discharge actuator that controls a ballast discharge from the ballast container, when the elevation rate is less than an elevation rate in particular, and where the elevation rate control comprises the discharge of ballast from the ballast container.

Another embodiment is a method for determining the location of a device that transmits wireless signals with a plurality of platforms lighter than free floating air comprising taking signal path delay measurements from the plurality of platforms lighter than free floating air and determining the location of the device that

9/125 transmits wireless signals based on signal path delay measurements, where the plurality of platforms lighter than free floating air has a speed relative to the Earth's surface of less than 160.9 km / h and floating at an altitude of 18,288 to 42,672 km, where the method does not require a Doppler effect correction. Preferably, signal path delay measurements are performed by measuring the difference between a wireless signal arrival time from the wireless transmitting device and a standardized time and determining the location of the wireless transmitting device is based on signal path delay measurements from at least three independent lighter-than-air floating platforms. In one embodiment, the device that transmits wireless signals is located on (a) a platform lighter than the free floating air that landed on Earth, or (b) a land-based vehicle, and the device is a transmitter or a transceiver. In one variation, determining the location of the device that transmits wireless signals based on signal path delay measurements comprises determining the distances from the device to the plurality of platforms lighter than free floating air, the layout of approximate circles on Earth, based on distances, and determining a point of intersection of the circles, the point of intersection being substantially the location of the device that transmits wireless signals. In one variation, taking signal path delay measurements is taking only two signal path delay measurements, while in one

10/125 another variation the taking of signal path delay measurements is made by sectored or directional antennas.

Another embodiment is a method for determining a payload location comprising a device that transmits wireless signals and an OPS unit, the method comprising measuring a location of the device that transmits wireless signals by the GPS unit, checking for a shift in the location of the device that transmits wireless signals and communication d, the location of the payload for a platform lighter than free floating air. Preferably, the payload landed on Earth and the platform lighter than free-floating air floats at an altitude of 18,288 to 42,672 km, where the method does not require a Dopplêr effect correction.

Another embodiment is a system for locating and determining the use of a land-based vehicle comprising a housing affixed to a land-based vehicle hub, the housing comprising a GPS unit, a device that transmits wireless signals and a power source. The housing could further comprise a tire rotation sensor. 0 The system could further comprise a lighter platform than free floating air comprising a device that receives wireless signals that receives signals from the device that transmits wireless signals. IPreferentially, the power source is a solar power source, a battery, a generator or combinations of the same.

Another modality is a method for steering a steerable system comprising the flight of the system

11/125 steerable in a circle in relation to a local wind in the steerable system, thereby canceling out a steerable system flight vector and determining a local wind vector with respect to a position on Earth, without using data obtained from a compass or an airspeed indicator. Preferably, the steerable system is an autonomous GPS-guided steerable system that does not have a compass or airspeed indicator on board the steerable system. Most preferably, the determination of the local wind vector is based on a land-based vector of the steerable system. Furthermore, the ground tracking vector could be obtained from a GPS unit located in the steerable system. Preferably, the steerable system is a component of a platform lighter than free floating air floating at an altitude of about 18,288 to 42,672 km.

Another method is a method for determining the location of a device that transmits wireless signals with one or more platforms lighter than free floating air comprising taking signal path delay measurements from one or more lighter-than-air platforms floating free at different time intervals and determining the location of the device that transmits wireless signals based on signal path delay measurements, where one or more platforms lighter than air floating free have a speed in relation to the Earth's surface of less than 160.9 km / h and floating at an altitude of 18.288 to 42.672 km, where the method does not require an effect correction

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Doppler. Preferably, platforms lighter than free floating air have a platform lighter than free floating air. Also, one or more platforms lighter than free floating air could have two platforms lighter than free floating air.

Another embodiment is a system for locating and determining the use of a land-based vehicle comprising a housing, the housing comprising a GPS unit, a device that transmits wireless signals and a power source, the system further comprising one or more lighter than free floating air platforms comprising a device that receives wireless signals that receives signals from the device that transmits wireless signals. Preferably, one or more platforms lighter than air floating free have a speed in relation to the Earth's surface of less than 160.9 km / h and floating at an altitude of 18.288 to 42.672 km, where the system does not require a correction of Doppler effect.

BRIEF DESCRIPTION OF THE DRAWINGS

A better understanding of the invention can be had with reference to the attached Drawing Figures in relation to the Detailed Description below, in which equal numbers represent equal elements and in which:

Figure 1 schematically describes a flowchart of combined methods of a termination decision by a processor or controller, including termination criteria, detection of criteria by the detection of geographical position and speed and operating elements according to certain aspects of the invention;

Figures 2a and 2b schematically describe a

13/125 mechanism for the controlled release of ballast, in accordance with certain aspects of the present invention;

Figure 3 is a schematic partial front view of a narrowing of a platform that connects between a balloon and a payload with a line and describing the construction and method of releasing a balloon from the payload platform;

Figure 4 is a schematic partial front view of the narrowing of a platform that connects between a balloon and a payload, as in Figure 3, which further describes the release of the balloon from the payload platform;

Figure 5 is a schematic diagram of a battery discharge and narrowing release circuit;

Figures 6, 7 and 8 are front, side and end views, respectively, of a maple seed lowering mechanism affixed to the bottom of a platform, according to an embodiment of certain aspects of the invention;

Figure 9 is a schematic description of a landed finished platform (with or without a balloon) transmitting a locator signal to a floating platform transceiver that transmits the locator information to a land station, to facilitate recovery of the finished platform;

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14/125 Figure 12 is a schematic description of a plurality of aerial platforms representing a constellation of platforms across a contiguous geographical area, launching facilities and communication terminals, networked together with a network operations center over lines on land and, alternatively, through satellite communication signals in orbit;

Figure 13 is an enlarged description of a plurality of aerial platforms, a single mobile launch site and a communication terminal with a network connection with a network operation center for a plurality of ground terminals and personal communication devices;

Figure 14 is a schematic description of interplatform communications with subsequent transmission to land terminals and a network operation center (NOC);

Figure 15 is a schematic description of satellite platform communication links in space for the provision of a network interconnection with a network operation center (NOC);

Figure 16 is a schematic description of a connection center and lightning network communication link topography;

Figure 17 is a schematic description of a mesh network communication link topography;

Figure 18 is a schematic description of a contiguous geographic area, particularly the United States, with launch sites for an aerial SNS platform and showing

15/125 the initial coverage area SAS circles, overlaid on a map of the geographical area and showing the line of sight coverage areas for each SNS platform, so that substantially the entire geographical area is encompassed in the reception range one or more aerial platforms;

Figure 19 is a schematic description of an example of aerial platform migration after a period of regulated altitude free float from the aerial platforms and also describing additional space-filling launch locations, which can be provided by mobile launchers, for supplementation and completion of coverage continuity with additionally launched aerial communication platforms;

Figure 20 is a schematic side view of an aerial platform in which a gas envelope lighter than air, such as a balloon, is attached to a box that holds electronic controls, communications devices, sensors and a package accumulation of meteorological data;

Figure 21 is an enlarged partial cross section of an aerial platform, including the control and communications box attached to a lighter-than-air gas enclosure, or balloon, according to an embodiment of the present invention;

Figure 22 is a partial partial cross-sectional view of the aerial control and communications platform of Figure 17, according to one embodiment of the present invention;

Figure 23 is a side view in cross section

16/125 partial of an alternative modality of a control and communication platform, in which an alternative power source, including a hydrogen / oxygen powered fuel cell is used in place of the batteries of the modality of Figure 18;

Figure 24 is a schematic block diagram of an electronic circuit for control, detection and communications according to an embodiment of the invention;

Figure 25 shows a platform lighter than air LO in two-way communication with a ground-based transceiver;

Figure 26 shows an equal propagation delay ring from a platform lighter than air on the ground;

L5 to Figure 27 shows delay rings of equal propagation of two separate lighter-than-air platforms;

Figure 28 shows a weatherproof housing for affixing a semi-trailer wheel to the hub for purposes of measuring the use and location of the semi-trailer;

Figure 29 shows a ground tracking vector;

Figure 30 shows a ground tracking vector and a flight vector;

Figure 31 shows a 2 5 earth tracking vector, a flight vector and a calculated wind vector;

Figure 32 shows the full circle procedure under no wind for effective flight vector cancellation;

Figure 33 shows the full circle under wind procedure for effective cancellation of the flight vector.

DETAILED DESCRIPTION OF THE INVENTION

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The present invention eliminates the drawbacks of previous communication satellites by the use of small and relatively inexpensive microelectronics for the incorporation of most of the functions provided by the existing communication satellites in small communication platforms lighter than air. In particular, a plurality of balloons lighter than air is designed to carry microelectronic communication equipment to a layer in the Earth's atmosphere called the stratosphere. 0 The weight of these platforms is approximately 100 to 1000 times less than the microsatellites currently launched in non-geosynchronous orbits. For convenient reference, aerial communication platforms or balloons carrying a payload of electronic communication and control equipment have sometimes been referred to here as stratospheric nanosatellites or SNS for short. In the metric system, the nano prefix means units 1000 times smaller than the micro prefix. The invention of SNS eliminates the need for a rocket to propel the satellite into orbit. The synchronized aerial launch of a plurality of SNS platforms in widely spaced geographic locations provides a low cost constellation of satellites. The SNS platforms rise after launch to an adjustable controlled altitude, where they migrate across the geographic area according to rising and stratospheric atmospheric conditions and, particularly, to the winds. SNS platforms can be raised or lowered in altitude by gas ventilation or ballast fall, in order to capture prevailing favorable winds for platform maintenance

18/125 of SNS evenly spaced. Platforms are brought down quickly when they are no longer needed.

The existing user equipment for terrestrial wireless communication can work with the SNS system of the present invention. This is not the case in the traditional communications satellite industry, since communications satellites are too far away from the user (more than 35405.6 km for geosynchronous satellites), making the signal too weak without specialized user equipment, or satellites travel at high speeds compared to users on land (more than about 57936.4 km / h for low orbit cross sections on Earth), causing phase errors at the receiver. The SNS platform, at most, is about 2 80 km from the user on land, depending on the altitude and the radial coverage range of the platform in particular among the plurality of platforms covering the geographical area. Furthermore, aerial platforms move at speeds approaching the speed of a car (between about zero and 96.6 km / h at their floating altitude). Compatibility with existing wireless communication systems is a significant advantage, because when employing a new communications system, investment in user equipment is always the largest total investment required.

In contrast to the large employment costs and new equipment for orbiting satellite systems, the present invention provides a low cost alternative that does not require new subscriber equipment. Thus, a benefit of the SNS System is an advanced message sending SNS network that is compatible with

19/125 one-way and two-way radio calls already in place and already in use with tower-based transceiver networks. Even without considering the use of the SNS system, market analysts predict that 35 million users will be carrying a standardized two-way radio call equipment compatible in 2003. For example, at $ 100 / unit, this represents an investment by $ 3.5 billion users. These users can receive the improved coverage of the inventive SNS platform network as an extension of their present service by simply choosing to pay usage fees monthly and in increments. There are no upfront costs for new user equipment or training and no need to change user habits and overload them with the transport of more than one radio call equipment or other communication device, as is the case with radio equipment. current satellite radio calls.

Furthermore, the inventive SNS system, when performing an advanced message sending, uses a communication protocol or radio call equipment being used. adopted internationally. International opportunities for the new system are at least equal to the potential in the United States. The SNS System can use other popular radio call sending protocols as well. The system also uses radio call sending in addition to personnel for other communications, remote, image formation, infrared scanning, frame reaction monitoring and weather data collection.

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It will also be beneficial for the National Weather Service (NWS) to consider using the current SNS invention as a replacement system capable of providing the NWS with the information required during the rise of SNS platforms. The GPS information available from the SNS platform could provide the desired wind information that the NWS needs, but which it is unable to afford. The existing NWS launch facilities could even be used as launching, monitoring and SNS communication sites. After the rise and transmission of climatic data to the NWS, the platform would then be controlled to float at a regulated altitude and provide other commercial communications services. The NWS probes could be removably attached and dropped as ballast after the ascent is complete and the desired information from there has been transmitted to the NWS. The radiosondes affixed could use exactly the same sensors used in the current radiosondes in order to keep the data consistent with the current radiosonde data.

The inventive SNS network is only designed to cover large areas and to use dedicated frequencies on a national basis and, ideally, on an international basis, between border countries. It is beneficial to allocate dedicated frequencies nationally or, ideally, internationally to the SNS system, due to the large coverage circles of each of the SNS aerial platforms. 0 overlapping use of the same frequency without multiplexing the time signals would most likely cause interference at the receiver. The shape system

21/125 optimal would work in a range of frequencies designated in the spectrum of Narrowband Personal Communications Services or NPCS. Furthermore, the entire NPCS industry in the United States generally agreed on the standardized two-way wrap protocol called REFLEX. REFLEX is a protocol that uses time division multiple access (TDMA). 0 REFLEX protocol is an extension of the FLEX protocol designed by Motorola and is a synchronous protocol in which there are 12 8 frames in a four-minute cycle. The beginning and end of each frame are nationally coordinated using GPS technology for timing. This will allow a single frequency to be shared between the SNS network of the present invention and the existing terrestrial satellite networks by simply allocating a certain number of frames to each network during each four-minute cycle. Thus, the shown SNS system can operate on its own dedicated frequencies or interoperate with terrestrial systems on the same channel and never transmit one on top of the other. This is unique to REFLEX and is preferably incorporated into the new SNS system. The SNS can also work using other protocols that use code division multiple access (CDMA) in the same way.

In contrast to most voice and radio broadcasting networks in which many different protocols are used over a wide range of frequencies, the NPCS contains an almost contiguous set of national frequencies on which national narrowband PCS licensees have adopted The Protocol FLEX / REFLEX.

The SNS system of the present invention benefits from

22/125 a national consistency of frequencies and protocols, so that it can operate relatively easily through all the NPCS channels owned by any and all of the national utilities, if necessary. Minimum government regulation of the NPCS bands also allows the new SNS system, which was unknown when the NPCS regulations were written, to operate on the NPCS bands without violating current regulations. Since NPCS licensees essentially own frequencies purchased at auction, and the inventive SNS system can use the same frequencies in a compatible manner with the buyer's permission, additional FCC licenses may not be necessary. This unique feature also saves two to three years in the start-up time that can sometimes take to obtain separate licenses.

As briefly discussed above, in addition to minimizing regulatory obstacles, the new SNS network has an enormous advantage in that it does not require new and specialized user equipment. It is expected that there may be as many as between 6 and 15 million units of compatible user equipment operating on existing terrestrial satellite networks. They can be added simply to the new SNS system using inexpensive system programming and thereby receive expanded and more complete coverage of the contiguous geographic area provided by the constellation of floating communication platforms in accordance with the present invention. For the NPCS concessionaire, the new system can provide complete communication coverage, particularly a

23/125 coverage in remote non-metropolitan areas.

Since the owners and users of existing radio call equipment can purchase the expanded coverage provided by the present invention through their existing dealership, the decision to expand the coverage can be as simple as checking a box on your monthly bill. They could keep their radio call system company current and simply add the remote area coverage benefit provided by the SNS. No new equipment is needed and no start-up time is required to learn new features of new electronic equipment. There is simply an improved coverage for the user, without changing equipment. A very important benefit of the inventive SNS network is the significant improvement in geographic coverage of a complete remote area. Currently, wireless data coverage is a patchwork of covered high-density population areas, primarily around metropolitan areas. The SNS network works cooperatively with the existing coverage areas and fills the entire low density population and, thus, the areas of low communication traffic, all using the same subscriber device. Government regulations governing NPCS systems require minimal system builds for all licensees. For example, around 1999, a licensee providing NPCS must serve at least 37.5% of the United States population or 750,000 km² and by the year 2004, an NPCS licensee is expected to serve at least 75% of the United States population or 150,000 km². Since the population is very concentrated, it was required that

24/125 previous systems built towers for coverage for a very small percentage of the total land area. In fact, the minimum area requirement for 1999 and for population service limits in 2004 corresponds to approximately 8% and 16% of the total land area in the United States, respectively. Due to the high population density in cities in the United States, for example, a coverage of 90% of the population requires that a concessionaire build only about 20% area coverage of the country's total land extension. Services in sparsely populated areas are more expensive for previous systems, since tower transmitters / transceivers have a short range, so more equipment is needed by the potential consumer. Thus, very few previous concessionaires have systems that cover more than 90% of the population, because of diminishing returns. Many established wireless data utilities are built for only about 70% a year.

80%.

The present invention is designed to provide substantially 100% coverage and can be combined in a manner compatible with existing high density wireless utility systems and networks, so that the high density construction by previous radio call system utilities deal with high population density geographic areas and low population density or remote area, wherever they are located in the contiguous geographical area, captured and handled by the inventive SNS system. The SNS system is complementary to radio call systems

25/125 high density tower. Thus, although the SNS system has a lower total signal handling capacity, when compared to high population density tower systems, it provides complete geographical coverage, so that subscribers in or traveling through remote areas are provided with the additional coverage of the SNS system. Subscribers are always in the range of radio call services or other compatible communication services using a single device. The SNS system can also reallocate capacity on a regional basis by launching more SNS platforms or by reallocating frequency usage dynamically among neighboring platforms.

The SNS system also uses radio-dispatching in addition to personnel for other communications, voice, remote imaging, infrared scanning, equipment tracking and weather data collection. The broadband PCS (BPCS) phones that hit the market last year all offer a message sending service called Short Message Sending Service (SMS). The SNS system could make a radio call to a subscriber's phone, when the phone was outside the BPCS service area. The BPCS voice service may also be possible with an SNS system. Another potential application for SNS technology is the remote imaging market. Governments, city administrators, farmers, environmentalists, surveyors and property developers all rely on aerial or satellite photos. Across the world, this market is more than

1.4 billion dollars. Since the SNS is more than twenty times closer to the individual than a satellite, the

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SNS can achieve a resolution of one meter with a 1.9 cm lens. Climatic data from the extended stay in the stratosphere can be collected and reported by the SNS platform as the current radiosonde does not have the capacity to maintain a floating altitude.

One embodiment of the present invention is a constellation of small aerial communication platforms with a ground network for launching, monitoring and communication terminals. Although the entire system is described primarily in terms of communications that are in the form of a radio call system, other communications, such as voice communications, emergency road services, search and rescue, medical emergency, remote imaging, environmental monitoring , industrial and public utility monitoring, remote asset management, photo data, IR scanning, equipment tracking, box truck and container tracking, vehicle safety, personal safety, hazardous materials, customs and international shipping safety, child safety, wildlife tracking, personal message delivery, communications for the disabled, SCADA, road transport communications and shipping tracking, and many others adapted communications could easily be included. As used here, radio call sending includes a traditional one-way radio call, as well as newer advanced messaging services (such as two-way radio call and voice messaging). The aerial constellation of communications platforms and ground support system extends the limited coverage of radio call networks

Current 27/125 for the provision of complete communications coverage over an entire contiguous geographical area. For example, in the United States, it provides true national coverage. Land-based tower systems already in place provide coverage within buildings, needed in urban areas, while the SNS system provides coverage for low-density rural areas. Thus, a subscriber can have complete national coverage using the same portable radio call device. 0 The inventive system does this by providing a constellation of uniformly spaced high-altitude aerial communication platforms, for example, balloon-carried radio call transceivers, as opposed to traditional land-based communication tower systems covering only a limited area, or as opposed to high cost or low altitude orbiting satellite communications systems.

To form the constellation of aerial communications platforms, radio call transceivers are attached to carriers lighter than air, such as high altitude balloons similar to those used by the National Weather Service (NWS), although modified to provide a control adjustable height regulated using methods such as gas ventilation and ballast drop. 0 lighter than air or balloon carrier and attached communications devices were referred to in this application as stratospheric nanosatellite platforms (SNS platforms). To cover a contiguous geographical area consisting of the Continental United States, SNS platforms can be launched periodically at intervals

12/28 regular, or as needed, from approximately 50 to 100 locations across the United States. These launch sites can be selected for launching the balloon-carried transceiver for elevation to a regulated stratospheric altitude of approximately 18.288 to 42.672 km. A computer-controlled altitude control and computerized monitoring are used. SNS platforms are regulated to maintain a desired altitude in a predetermined altitude range, for example, in the stratosphere over the Earth, as they drift along with existing wind currents. New SNS platforms can be launched to fill any spaces that may occur on the roof, as the platforms drift at different speeds, as they lose buoyancy or as they occasionally explode or malfunction. New SNS platforms can also be launched to provide additional communications capacity, as the need arises. The newly launched SNS platforms can collect, record and transmit meteorological data during the ascent to the regulated altitude. New data could be beneficially communicated via radio to land for use by the National Weather Service (NWS). The process of modeling and thereby predicting the coverage of the SNS platform network on an ongoing basis is a complex task due to the constantly changing weather conditions. This task is also facilitated by the use of weather data recorded and / or transmitted to land to predict the movement of individual platforms in relation to each other and in

12/29 regarding the launch terminals and ground monitoring. This data can also be used to control the altitude of the individual SNS to capture favorable prevailing winds to assist in filling gaps in the roof. Each satellite floating at a stratospheric altitude will have a line of sight radio communication coverage over a radius of approximately 280 km in all directions from the antenna suspended below and forming a part of the communications platform.

The land-based support for the plurality of SNS platforms that form the constellation comprises at least one network operation center (NOC) and a plurality of launch and tracking terminals. The NOC is preferably a high speed, high volume, computing, communications and operations center for the SNS system. The NOC may be in charge of all controllable aspects of each flight and operation of the communications platform. These controls include platform launches, fluctuation altitudes, tracking, all

0 radio call communications and control signal transmissions and communications with partner radio call companies. Typically, SNS ground terminals include launching facilities, monitoring and communications equipment and communication antennas. Co-located launch facilities and land terminals can also advantageously correspond to the existing locations of the nearly seventy NWS balloon launch facilities that are designed for monitoring climatic conditions nationally. Similar weather stations also exist and are maintained by treaties

12/30 essentially all over the world. These ground terminals can be automated. Portable or mobile ground and launch terminals can also be used, when necessary, to fill anticipated coverage spaces that may develop between the overlapping circular coverage patterns of floating platforms. These portable or mobile ground and launch terminals can be moved seasonally to provide additional launch sites as stratospheric winds change on a seasonal basis. These would most likely be positioned along the shoreline or the edges of the coverage area. Land terminals can advantageously accompany several SNS platforms floating close to their location and can provide an uplink or a downlink of all communications, including radio call and control data, for each platform in the terminal strip. The radio signals from a subscriber radio company can be sent to the SNS system through the NOC. The NOC determines which SNS platform is currently on top of the addressed radio call equipment and sends the receptacle message to the ground terminal that is accompanying the SNS platform. The ground terminal receives the radio call message from the NOC and transmits it to the SNS platform. The SNS platform then transmits the radio call message down to the individual radio call equipment. Any message sent by a two-way radio call equipment is received by the nearest SNS platform and transmitted to the ground terminal. 0

12/31 ground terminal sends the message to the NOC, which transmits the message to the appropriate subscriber radio call concessionaire. The NOC also keeps track of all taxation information and subscriber location information. The SNS system is advantageously designed to be fully FLEX compliant

<td>(equipment</td><td>radio call</td><td>an</td><td>via) and</td><td>also REFLEX</td>

<td>(equipment</td><td>radio call</td><td>in</td><td>two</td><td>routes) without</td>

<td>modification</td><td>on equipment</td><td>in</td><td colspan="2">radio call. At</td>

Launch facilities, co-located with NWS launch facilities or separately located at other selected land locations, may consist of a fully automated launcher and land terminal. A land-based terminal can control multiple SNS platforms at once. Ground lines, satellite links, or other high signal capacity network communications coupling one land location to another can be used to connect the plurality of launch sites and land terminals to each other or to the NOC.

An embodiment of this modality is a system comprising a free floating platform and a communication device that is separate from the platform, the platform comprising a gas shell lighter than air and a payload, the payload comprising a processor and a transceiver , where the processor is able to make a decision to end a flight from the platform, the transceiver is able to receive a signal from the communication device, and the communication device is capable of transferring the signal to another transceiver on another free floating platform. The payload could still comprise a

32/125 altitude, a position sensor and a power source. Typically, the payload is 152.4 meters from the gas enclosure lighter than air.

The decision is based in part on (a) whether the platform is determined to be outside specific geographic boundaries; (b) if the platform is outside a specific toggle range; (c) whether the platform has a lateral or vertical speed outside a specific range; (d) if the processor fails; (e) if a power source fails; (f) if a command and control link fails.

The decision could be to release a ballast, to stop a signal to a discharge circuit to prevent the battery from discharging, to release the payload platform or a combination of them.

Another embodiment of this invention is a method of terminating a flight from a free floating platform, where the platform comprises a transceiver capable of receiving a signal from a communication device that is separate from the platform, the method comprising determining a geographical position and / or a platform speed, make a decision with a processor on the platform to end the flight of the platform, transfer the signal to another transceiver on another free floating platform and end the flight of the platform.

Yet another modality is a system for ascending or decelerating the descent of a free floating platform, which comprises a gas envelope lighter than air and a ballast comprising reagents that form a gas that is lighter than air when the reagents are

33/125 mixed. The gas could be hydrogen and the reagents could comprise water and a Ca or Na hydride. At least one of the reagents must be heavier than air. For example, at least one of the reagents could be a hydrocarbon. The system could also comprise a catalyst for reforming at least one of the reagents.

Another embodiment of this invention is a method for ascending or decelerating the descent of a free floating platform, the method comprising the reaction of reagents stored on the platform to form spent reagents and a gas that is lighter than air, the introduction of gas in a gas envelope lighter than air and the drop in spent reagents.

Another embodiment of this invention is a system for terminating a flight of a free floating platform, which comprises a gas enclosure lighter than air, a payload and an element, where the element is able to separate the gas enclosure from the useful load. The element could comprise a line and a component capable of breaking the line. The system could also comprise two axially aligned tubes connecting the payload to the gas enclosure. In a preferred embodiment, the element could be a pin.

Yet another embodiment of this invention is a method of terminating a flight from a free-floating platform comprising a gas envelope lighter than air, a payload and an element, where the method comprises separating the gas envelope lighter than the payload air by an element action. The method could still understand the current passing through the element.

34/125

Another modality of this invention is a power system that includes a battery, a processor and a discharge circuit, where the processor intermittently sends a signal to the discharge circuit, to prevent the battery from discharging. Preferably, the processor stops sending the signal when the power system lands on the ground or in the water.

Yet another embodiment of this invention is a method of retrieving a free floating platform that comprises landing the platform on land or in water and sending a platform position to a transceiver located on another free floating platform. The method could further comprise transmitting the position of the transceiver located on another free floating platform to a transceiver located on a ground station.

Another embodiment of this invention is a system for terminating a flight from a free floating platform, which comprises a gas casing lighter than air, a payload and a means for releasing the gas casing from the payload. The means for releasing the gas casing is one of those shown in the specification and equivalent thereof.

It has been discovered that the greatest prior use of unmanned balloons lighter than air has been by the world's climatological services. For the purpose of acquiring climatological data, small latex climate balloons carry packages of instruments called radiosondes for the accumulation of climatic data. These climate balloons are launched from a network of locations around the world

35/125 noon and midnight Greenwich Mean Time each day. Weather service radiosondes collect data on temperature, humidity, pressure and wind as they rise from the Earth's surface to approximately 30.48 km during a two-hour flight. At approximately 3 0.48 km, the weather balloons explode and the payload of the radiosonde falls to Earth in a parachute. These data acquired during the ascent are introduced in atmospheric models run on supercomputers, to facilitate climate forecasting. The input data is limited, as it represents only a snapshot of the climatological data taken during the ascent of the balloon every 12 hours. Ascension and descent are rapid, especially landing at the borders of the country of origin, so short-lived radio transmissions and a physical border crossing are not important issues. Also, most countries in the world are bound by a treaty to launch radiosondes carried in balloons from designated locations and share data with other countries.

There are currently around 800,000 radiosondes launched each year around the world. There are also a small number of research balloons launched for research purposes. The research balloon can be quite large and flights are typically made using special frequencies and with international or individual country permission to cross the border. 0 total number of balloon flights per year primarily comprises 997 global weather stations launching two radiosondes per day, 3,665 days per year (727,000) plus a small number of radiosondes launched

36/125 for research purposes. Only about 18% of radiosondes are recovered, reconditioned and regenerated, resulting in a new production of about 650,000 radiosondes for accumulating climate data per year.

The Federal Cominunications Commission (FCC) prohibits uncontrolled transmitters, as they can cause interference with users on the same frequency or others on nearby frequencies. FCC spectrum licenses generally prohibit a transmitter licensed in the United States from transmitting when it leaves the United States border.

It has been found that most platforms that are lighter than air that maintain an altitude must drop ballast in order to maintain an altitude, as the elevation gas is lost through the balloon membrane and as the sun's heating effect is lost as the night approaches. Section 101.7 of the Federal Aviation Administration (FAA) regulations states that unmanned balloons are prohibited from dropping objects or an operation so that a risk can occur.

Section 101.7 Risk Operations.

(a) No person may operate any moored balloon, kite, unmanned rocket or unmanned balloon in a manner that creates a risk to other people, or to their property.

<td>(B)</td><td>None</td><td>person</td><td>operating any</td><td>balloon</td><td>with</td>

<td>mooring</td><td>, Kite,</td><td>rocket</td><td>unmanned or</td><td>balloon</td><td>not</td>

<td>manned</td><td colspan="4">can allow an object to be left</td><td>fall</td>

<td>from there, if</td><td>such action</td><td>create one</td><td>risk to others</td><td>people</td><td>, or</td>

37/125 for your property.

(Section 6 (c), Department of Transportation Act (49 USC 1665 (c))) [Doc. No. 12800, Amdt. 101-4, 39 FR 22252, June 21, 1974]

An important factor influencing the size and cost of a platform lighter than air is the weight of the payload. For small balloons, such as weather balloons, they may become exempt from certain FAA reporting, lighting and launch displays, if the total payload weight is kept below 2.72 kg and a specific weight of less than 85.048 g per 6.45 cm² on the smaller side.

Sec. 101.1 (4) Applicability.

This part prescribes rules governing the operation in the United States of the following:

(4) Except as provided in Sec. 101.7, any unmanned free balloon that (i) carries a payload package that weighs more than 1.814 kg and has a weight / size ratio of more than 85.048 g by 6.45 cm² on any surface of the package, determined by dividing the total weight in ounces (1 oz = 28.34 g) of the payload package by the area in square inches (1 in² = 6.45 cm²) of its smaller surface;

(ii) carry a payload package that weighs more than 1.814 kg;

[Doc. No. 1580, 28 FR 6721, 29 June 1963, as amended by Amdt. 101-1, 29 FR 46, January 3, 1964, Amdt. 101-3, 35 FR 8213, May 26, 1970] single use of a light and low payload

38/125 density also significantly reduces the costs associated with launching and allows a launch to take place in all weather conditions. The amount of ballast required to maintain a platform in a regulated altitude range for a period of 24 hours is typically around 15% of the total weight of the system. This is a significant percentage of the total weight for a floating platform, especially for balloon missions that can last for multiple days. For example, it has been found that a three-day flight may require 38% of the weight of the platform system to be ballast. This results in a significant increase in the size of the balloon or a decrease in the weight available for the payload.

The two sections of the FAA regulations above show the FAA's concern with the increased payload weights and densities. This concern seems to focus on reducing the. potential for damage to an aircraft in a collision. The density and total weight of the payload can also be considered to be significant factors in general security regarding the return of the payload to Earth. It is generally believed that payloads of lower weight and density reduce the chances of causing physical damage and, as a beneficial result, can also be easier and less expensive to insure as well.

The FAA also prohibits uncontrolled air drift balloons lighter than air. Again, there may be a concern that uncontrolled flight may pose a risk to aircraft. For example, in 1998, the Canadian Space Agency lost control of a large scientific balloon. This prompted the redirection of flights from

39/125 passengers from across the Atlantic for 10 days, as the balloon drifted from its launch site in Canada until the end, .also land in Finland. The uncontrolled balloon also resulted in aviation concerns in Russia and Nonuega. Significant resources were spent, including the use of fighters to try to bring the uncontrolled balloon down.

So far, balloons lighter than unmanned free drift air have been restricted to short flights, as is the case with the 50,000 NWS weather balloons launched each year, or very few large, long-term and expensive scientific flights. NWS climate balloons have an extremely limited life (approximately 2 hours) and their transmitters and batteries have limited power. Long-term cytological balloons typically have long lives and extended missions. These infrequent balloon flights are expensive and generally require frequency and safety coordination with each country they fly over. They can obtain authorization to use government or scientific frequencies for short periods of time that are not available to commercial users.

Applicants, as shown in the co-pending application, have discovered and developed new and commercially viable uses for small free-floating platforms with long-term capabilities. These small, long-lasting balloons or free-floating platforms have long flight lives similar to much larger scientific balloons and the ability to travel long distances. The present inventive methods and devices also facilitate the reduction of autoimmune diseases massive reporting requirements

40/125 and coordination of the larger balloons. Free floating platforms may be operating on commercial frequencies that have specific laws regarding the use of frequencies in each country. Innovative new methods facilitate the maintenance of legal transmitter operations, particularly at borders, they provide platform flight termination for invasive, uncontrolled or malfunctioning platforms, they provide an environmentally acceptable descent and they improve the opportunity for recovery and reuse of these devices. All of these methods are especially useful when referring to regional and international borders. The present invention uses specific criteria and elements of operation or sets of criteria and elements of operation that taken as a whole form a safe method for reducing or preventing illegal transmissions, for flight termination, for rapid descent from the platform to the ground, for an environmentally acceptable landing and for improved recovery. All methods are designed to improve safety and to comply with known regulations.

Figure 1 schematically describes a flowchart of combined methods of a termination decision by a processor, including termination criteria, detection of criteria by detecting a geographical position and speed, and operating elements according to certain aspects of the invention. In combination with the on-board power source 12 and a GPS 14 (or another geographic locator or tracking system), a processor 10 is provided for receiving position information and a change of position information time (speed ) 14. The

41/125 position information is compared with criteria information stored or programmed in 16, 18, 20, 22, 24, 26, 28 and 30, to determine whether the termination of a radio transmission and / or the termination of a flight must be implemented.

The following criteria-based decisions are provided with processor 10:

Did the Platform move or drift out of a certain geographic area? (See Fig. 1 at 16).

The relevant boundaries may be frequency license boundaries regulated by the FCC, as dictated by a regional or national broadcast license. The FCC prohibits a transmitter operation outside these geographic boundaries. In addition, a neighboring country may have restrictions on the power transmitted to its country from a foreign transmitter. It has been found that on certain frequencies Mexico prohibits transmission power levels above -99 dBm in Mexico from the United States. These restrictions are not difficult for terrestrial towers to comply with as the towers can install and adjust directional antennas once during installation and do not have to adjust them again after that. This is quite different for a free-drift high altitude balloon containing a transmitter, as position and altitude may be constantly changing and may require the platform to stop transmitting while still within the United States, but in a protection number km from the United States - Mexico border. Long-term scientific balloons are not so concerned with this, as they typically work at frequencies

42/125 special or were coordinated with other countries that they can fly over.

Is the platform moving outside borders that would significantly reduce the likelihood of the platform recovering? (See Fig. 1 at 18).

As payload costs can be significant, from 50 to 150 dollars for a typical weather service radiosonde, up to hundreds of dollars for a transceiver platform, and up to many tens of thousands of dollars for a scientific payload, recovery is important for financial and environmental reasons. A platform may encounter strong winds, especially in the jet stream as it descends from high altitudes. In order to prevent the platform from drifting out of the country on the descent, artificial borders that take into account the winds during the descent can be used. Also, boundaries of large bodies of water, such as large lakes, seas and oceans whose crossing could delay or impede the recovery of the platform during a normal descent, can be taken into account for the purpose of flight termination.

Did the platform fall below or rise above a regulated altitude range? (See Fig. 1 in 20)

Most scientific and climatological balloons reach altitudes above 18,288 km and discourage a free-floating aircraft or an uncontrolled flying aircraft from wasting time especially on commercial airstrips, as they pose a risk to commercial airplanes. Current NWS weather balloons do not have the ability to end the flight if they begin to hover

43/125 below 18,288 km. Even large-scale scientific balloons can become wandering and drift free below 18,288 km (see the example of an invasive scientific balloon listed earlier).

Is the platform speed sufficient to create a large unacceptable Doppler effect on the transmission frequency? (See Fig. 1, at 22).

A balloon traveling in the jet stream can reach speeds of more than 289.7 km / h. This creates a Doppler effect on frequencies received on land. The FCC regulates the amount of total frequency drift allowed in transmissions. The Doppler effect contributes to this full frequency drift and, if large enough, can cause the transmitter to transmit outside its allowed band. These requirements have not been considered or accounted for in the past, as commercially free drift transmission platforms were not available. Therefore, the requirement that the payload be able to immediately stop transmitting after the speed at which the Doppler becomes too large is new.

Does the platform drop rate indicate a balloon explosion? (See Fig. 1 in 24).

A rapid drop rate indicates that the balloon has exploded and the aircraft is falling.

Is the lighter-than-air platform rising too slowly during an ascent? (See Fig. 1 in

26) .

This indicates that the balloon is underfilled or leaking. A slow elevation rate can pose a risk to an aircraft by wasting time excessively at an altitude

44/125 particularly at an altitude on designated airstrips.

Has the processor, position-finding equipment, or primary power failed? (See Fig. 1, at 28).

A failure of a GPS, star tracker or system power must initiate an onboard termination. The platform must be able to end without control or processor power.

Have command and control communications been lost?

(See Fig. 1, at 30).

Without command and control of the ground, the payload must cease the transmission and the flight must be terminated.

The present inventive system detects the preceding conditions by comparing the current position, speed and operating conditions with stored, programmed or calculated criteria, using an onboard processor or controller. The present invention uses a GPS unit and a processor to determine the current geographical coordinates and platform speeds. A GPS unit or a pressure sensor determines the altitude of the platform. The processor algorithms will implement the complete set of conditions listed above, causing the ballast to be released in 34, transmission to be interrupted in 38 and the flight to be terminated in 36, upon detection of stored, programmed or calculated termination criteria. Under conditions of power loss or processor failure, the transmitter will also be stopped at 38 and the flight will be terminated at 36. The methods and mechanisms for termination actions are described more fully below.

45/125

A separate termination controller 11, which may be under separate power 13, monitors the primary platform power at 32 and monitors the processor functions at 30 to determine whether processor 10 is functioning properly. Both the primary processor 10 and the separate termination controller 11 have the ability to terminate transmissions by discharging the primary platform batteries at 38 and ending the flight by releasing the balloon at 36. The separate power source 13 may advantageously comprise a very small environmentally acceptable battery, such as an alkaline clock battery.

The present invention addresses certain needs of the past. This invention describes a system, method and design for use with lighter-than-air platforms that eliminate certain safety inconveniences from lighter-than-unmanned air balloons. 0 processor reduces or eliminates the chance of the platform becoming an uncontrolled transmitter floating freely by monitoring the detected coordinates and platform speeds (GPS, star tracker, etc.) and by comparing the detected information with geographical or altitude-based boundaries (stored, programmed, calculated). If the processor determines that the platform is outside the appropriate boundaries, termination is initiated. If the GPS fails, the processor also initiates termination. If the processor function fails unacceptably or the primary power fails, termination and recovery is also automatically initiated with a secondary termination control circuit having its own source

46/125 small and environmentally acceptable power. This does not require power from the platform's primary power source.

Termination and recovery comprises several steps or actions, as follows:

Release of all ballast to reduce density and payload weight.

The following device allows the controlled release of ballast (and the generation of elevation gas) to reduce the rate of rise or decelerate the rate of descent. In a termination, the entire ballast is automatically released according to a mechanism, as described schematically in Figure 2. Ballast system and release mechanism.

Both reagent A in chamber A (100) and reagent B in chamber B (101) are measured in the reaction chamber (104), where a generation of hydrogen occurs. The relative size of each of the two chambers is determined by the molar ratio

<td colspan="2">of the reaction.</td><td>If water is</td><td>used as</td><td>one</td><td colspan="2">reagents and a</td>

<td>cell</td><td>in</td><td>fuel</td><td>is used</td><td>at</td><td>platform for</td><td>The</td>

<td>generation</td><td>in</td><td>power, the</td><td>by-product</td><td>in</td><td>reaction water</td><td>in</td>

fuel cell can be used for the reaction of the ballast system as one of the reagents. Different measurement rates would be required for each reagent, if the molar ratio of the reagents was not 1 to 1. This could be done with a double peristaltic pump (102), if the pipe diameters were adjusted to pump the appropriate amount for each reagent chamber. During the reaction, hydrogen is vented from the reaction chamber through a tube (107) into the flask. A one-way valve (106) on the tube for the balloon

47/125 prevents hydrogen from flowing back into the reaction chamber. After the reaction is complete, the by-product is dropped as ballast from the bottom of the reaction chamber (104) through an electrically actuated valve (105). The valve (105) is then closed. Upon a flight termination, the reagents will be reacted as quickly as possible safely in the reaction chamber (104) and the by-products dropped as ballast.

In a second configuration (not described), the ballast system comprises two wells, each containing one of the two reagents. The reagent in the top well is measured in the bottom well, where hydrogen generation occurs. Reaction by-products are only released as ballast when all original reagents are spent.

In a third configuration, a hydrogen chain is formed for the production of hydrogen. This requires a catalyst, such as platinum. Hydrocarbon reforming methods for hydrogen production are well known in the industry. The hydrogen is added to the lifting vessel and the remaining reacted reagents are dropped as ballast.

This method of generating hydrogen from the materials used for ballast effectively makes the payload lighter and therefore safer in the event of a collision with an aircraft or people and property on the ground. Although any acceptable ballast could be released, the new ballast system described above effectively reduces the actual ballast weight required by a system, thereby increasing the safety of the payload. In the new ballast system, the total amount of ballast ported to the

48/125 provision of a long-haul flight at an acceptable altitude is significantly reduced. Reducing the amount of ballast in most cases increases safety. In a specific example, the system uses water and sodium hydride or calcium hydride as the ballast. When an additional altitude is required, an amount of water is added to an amount of sodium hydride or calcium hydride. A large volume of hydrogen gas is generated. This hydrogen is added to the lift balloon and the by-products of the reaction are dropped as ballast. The platform becomes lighter due to the fall of the Ca (OH) by-product₂ or Na (0H)₂ and, at the same time, hydrogen is added to the balloon, increasing the lift. Only 73% (75% for sodium hydride) of an equivalent weight of an inert ballast, such as sand, is needed. A ballast can be a significant portion of the total initial weight, reducing the weight of the balloon significantly by reducing the total weight of the payload.

Release of the narrowing of the platform balloon to start a rapid descent.

This ensures that the platform quickly descends through the atmosphere, thereby reducing the potential time for the payload to pass through commercial airstrips. Small balloon systems, such as NWS weather balloons, are based on a balloon explosion due to expansion as it rises through the atmosphere. A hovering balloon does not experience this expansion and, therefore, must have a system for balloon explosion or physical separation of the balloon. Balloon ventilation is generally not acceptable, because of the risk of the balloon being inflated

49/125 partially drifting laterally into the ground increasing the chance of personal injury or property damage. Another problem would occur if hydrogen was used as the lift gas. This could create a possibility for hydrogen to remain in the balloon after landing and contact an ignition source. The explosion of the balloon is also generally undesirable, since the exploded balloon still attached to the payload can obstruct the descent mechanism causing an uncontrolled descent. In the invention, the balloon narrowing is released when power is lost or the processor fails, eliminating these potential problems.

A possible implementation of the nip release mechanism, as described schematically in Figures 3 and 4, comprises two concentric nip connection tubes (43) and (49). The top tube (43) is slid and attached to the balloon (41) with a strap (42) or a rubber band (42) and fits on the bottom tube (49), which is attached to the payload (51 ). 0 top tube (43) is restricted from sliding out of the bottom tube (49) by a piece of monofilament thread (47). While the top tube (43) and the bottom tube (49) are restricted to each other, a flexible seal (44) prevents gas in the tubes from leaking at the tube junction. Each end of the monofilament line (47) is passed through a small hole in a flange (46) and tied. The monofilament line (47) is passed around two buttons (52) and also through and in contact with an electrically resistive coil (48).

A second implementation of the nip release mechanism uses a tube that is attached to the

50/125 narrowing of the balloon, as in the first implementation. The tube is removably attached to the payload by one or

<td>more hitches</td><td>When</td><td>these</td><td>hitches</td><td>are</td><td>broken,</td><td>O</td>

<td>narrowing</td><td colspan="2">can separate</td><td>of the load</td><td>useful.</td><td></td><td></td>

<td>In a</td><td>third</td><td colspan="2">Implementation</td><td>of</td><td>mechanism</td><td>in</td>

<td>release of</td><td colspan="2">narrowing,</td><td>a tube</td><td>what</td><td>is posted</td><td>to</td>

narrowing of the balloon as in the first implementation is axially aligned and slides in or over the second tube that is attached to the payload. A release pin or pins pass through both tubes from the side, so that when the pin is removed, the tubes are free to separate from each other. See Figure 11.

When the flight termination is requested, the ballast is preferably released first and then a current is passed through the resistive coil (48). The coil (48) heats up and melts through the monofilament line (47). The payload weight (51) now pulls the bottom tube (49) from the top tube and the payload is released from the top tube (43) and thus the balloon (41). This ballast system advantageously allows ventilation of the lift gas directly into the payload, eliminating the need for wiring for remote valves.

Q battery discharge circuit and nip release.

The battery discharge and nip release circuit is described schematically in Figure 5. The processor must constantly supply a keep active signal to the battery discharge circuit, in order to prevent the battery from discharging. This keep active signal comprises a square wave. 0 discharge circuit

51/125 of battery detects transitions from low to high in the keep active signal and resets the timer (a HEF 4060) every time a transition is detected. The timer must be reset by the presence of a square wave to keep active or the timer will end its count and start the battery discharge. A high-power FET closes the circuit that discharges the batteries. In a discharge circuit implementation, the power of the discharge circuit comes from the main batteries themselves. Because the discharge circuit can operate up to extremely low battery voltages, the batteries are effectively discharged the moment the discharge circuit is unable to function.

An alternative implementation uses a separate, low-risk battery to operate the discharge circuit. This implementation ensures that the main batteries are completely discharged. The discharge circuit dissipates power through the resistive wire which, during a battery discharge, dissipates energy as heat. The resistive wire is wrapped around a piece of monofilament (fishing) line. When the battery power is dissipated through the resistive wire, the monofilament line is fused and the narrowing connecting the balloon to the platform is released from the payload. Another advantage of providing a separate power source for the discharge circuit is that the discharge circuit battery will supply the resistive element with power to cut the monofilament line, even if the main batteries are zeroed. As an alternative, the discharge circuit could dissipate power through a resistor

52/125 high power, if the nip release function was not used.

If the processor detects any of the conditions necessary to start the termination, it stops sending the keep active signal to the discharge circuit. If the processor goes down or the power fails, the keep active signal will also cease, causing a termination. The timer advances to a point where it starts to discharge the battery. The battery current flows through the resistive wire, discharging the batteries and fusing through the monofilament to release the balloon narrowing. The battery discharge continues until the main batteries are completely reset.

The main platform batteries are fully discharged during a descent to positively avoid another radio transmission. Once a discharge is initiated, the batteries are fully discharged. The processor can initiate battery discharge, as described above, or automatically when the processor's power or control is lost. It has been found that long-haul flight at high altitudes and cold temperatures requires special high-density batteries. Lithium batteries have been found to beneficially meet these requirements. Additionally, it was discovered that the Environmental Protection Agency (EPA) establishes that lithium-based batteries are considered hazardous waste, except for one type of cell and only when fully discharged. In particular, it has been found that sulfur dioxide and lithium (LiSO2) batteries, when fully discharged, form a

53/125 lithium, which is not considered dangerous by the EPA. The automatic discharge of LiSO2 batteries before they contact the ground not only prevents the transmitter from transmitting, but also makes the batteries non-hazardous.

maple seed descent device.

The use of a new, integral maple seed descent device for increased safety is described in Figures 6, 7 and 8. A single airfoil-shaped blade affixed to the bottom of the platform causes the payload and airfoil blade when rapidly descending. This replaces a conventional parachute with a highly reliable decelerator that is generally immune to obstruction and requires no mechanism of use and is also immune to obstructions with animals and property after descent. The maple seed decelerator can also be used for convenient antenna housing.

This auto-rotation occurs because of the asymmetric nature of the airfoil. The center of mass of the payload / airfoil combination is well shifted to the payload end, while its center of elevation is approximately halfway. This causes a circular rotation of the entire assembly around its center of mass. The rotation actually inscribes a cone around the geometric fall axis. The shape of the cone will vary, depending on the aerodynamic qualities of the airfoil. An airfoil with minimal lifting properties will inscribe a cone on a steep side, while an airfoil with strong elevation properties will inscribe a very flat cone.

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Platform Recovery.

A new platform recovery method is described in Figure 9. To assist with platform recovery, the landed platform transmits its last recorded position to an additional aerial platform. The platform could determine that it landed by comparing the sequential position readings and noting when it did not consistently indicate any change in position. The second platform transmits the current location of the landed platform to a land station, where the position of the landed platform is used to assist in the recovery of the landed platform. A GPS unit in the landed payload could determine the position of the landed platform. The transmission from the landed platform to the additional aerial platform could use any commercially available or customized transceiver.

The transfer mechanism.

Figure 10 shows the transfer capacity, that is, the transfer of the signal between platforms by the communication devices. Figure 10 shows a schematic view of a portion of a constellation and a communication network system in which 12 (i), 12 (ii) and 12 (iii) are aerial platforms. Each aerial platform comprises a gas envelope lighter than air, such as a balloon, and a transceiver (processor). Strong and weak signals between platforms and the communication devices (user equipment) 22v-z, located on or above the ground, are shown by the continuous and dotted lines 120. The monitoring antennas 126 could be located on the ground terminal 124 or on a platform launcher, this

55/125 is, an SNS 46 launcher. Also, the SNS 46 launcher could be a 44 launcher. Lines 28 show the command and control link between the monitoring antennas 126 and the platforms.

In particular, Figure 10 shows the communication devices 22y and 22z communicating with platforms 12 (ii) and 12 (iii). The signal from platform 12 (iii) is stronger (as shown by the solid lines) than that from platform 12 (ii) (as shown by the dashed lines). When platforms 12 (ii) and 12 (iii) migrate from left to right, due to wind currents, as shown in Figure 10, communication devices 22y and 22z transfer communication with platform 12 (iii) to the spring 1221, as platform 12 (iii) moves out of the communication range and platform 12 (ii) moves to the previous position of the platform (iii). Generally, the processor (s) on board the platform (s) do not transfer the signal, it is the communication device that initiates the transfer.

The component signal transceiver comprises a circuit capable of communications using FDMA, TDMA, CDMA and ReFLEX protocols. All of these so-called protocols use handoff. For example, US Patent No. 5,649,000, issued July 15, 1997, shows a method and system for providing a different frequency transfer in a CDMA cell phone system. Devices using these protocols periodically scan a neighboring control channel in the background, without interrupting normal operations. If the device finds a better channel, in terms of

56/125 significantly better signal strength or higher priority, it can request a transfer. This is usually done using a make before brake transfer, a concept similar to the temporary transfer used in PCS phone networks, where an alignment with a new channel is completed before communication with the old channel is broken. This usually means that a device will always be aligned with the network, and capable of receiving messages. This allows communication devices to move quickly and efficiently through service areas with different control channels.

Another modality is a floating constellation communication system that comprises a plurality of platforms lighter than air, each including an altitude regulating device for controlling the fluctuation of said platforms in a predetermined altitude range, each platform carrying at least a communication signal transceiver; a plurality of geographically spaced platform launch sites, from which said plurality of platforms can be launched; a plurality of land terminals capable of accompanying one or more of said plurality of platforms, said land terminals capable of transmitting communication signals and capable of receiving communication signals from at least one of said plurality of signal transceivers; communication ported by said plurality of platforms; a network of communication links interconnecting said terminals on land to each other

57/125 others; and a plurality of communication devices encoded in a contiguous geographical area, said communication devices coded having communication capabilities compatible with the capabilities of said signal transceivers carried by said platforms.

Another modality is a floating constellation of communication platforms comprising a side wall decision unit lighter than air platforms that can be launched separately and capable of initially ascending into the Earth's atmosphere after being launched; each of said plurality of platforms still comprising an operatively connected altitude regulator for the regulation of each of said platforms for floating in a predetermined altitude range, after the initial ascent; and a communication signal transceiver carried by each of said plurality of platforms.

Another embodiment is a floating constellation communication system comprising a plurality of lighter-than-air platforms regulated to float in a predetermined altitude range, each platform carrying at least one communication signal transceiver; a plurality of geographically spaced platform launch sites, from which said plurality of platforms can be launched; a space satellite and a network of satellite communication links between a plurality of land terminals capable of said space satellite and said plurality of platforms, and capable of transmitting

58/125 communication for and receiving communication signals from said plurality of communication signal transceivers carried by said plurality of platforms; a network operations center (NOC) and a satellite communications link between said NOC and said space satellite, thereby interconnecting said NOC and said plurality of platforms; and a plurality of communication devices encoded in a contiguous geographical area having communication capabilities compatible with the capabilities of said communication signal transceivers carried by said plurality of platforms.

Another embodiment is a floating constellation of communication platforms comprising a first plurality of adjustable aerial platforms to ascend and float in the air for a period of time in a predetermined range of altitudes, said first plurality of aerial platforms ascending in a first time to from geographically spaced locations; a next plurality of adjustable aerial platforms to ascend and float in said predetermined range of altitudes, said next plurality of aerial platforms ascending in the next time from said geographically spaced locations; a rapid deflation system for removing said aerial platforms from the air due to a malfunction or improper location of said aerial platform; at least one platform communications signal transceiver attached to each of said aerial platforms; a plurality of transceivers in

59/125 geographically spaced land capable of communicating with said aerial platform; a network of communication links interconnecting said plurality of transceivers on land; and a plurality of encrypted devices having communication capabilities corresponding to the capabilities of said platforms and selectively addressable by communication signals from said platforms.

Yet another modality is a floating constellation of communication platforms comprising a plurality of adjustable aerial platforms to float in an adjustable altitude range and spaced to provide substantially ubiquitous line of sight coverage across a contiguous geographical area; said plurality of aerial platforms including a plurality of communication transceivers, at least one of said plurality of communication transceivers carried by each of said plurality of aerial platforms; a plurality of land terminals spaced by said contiguous geographical area for maintaining substantially ubiquitous line of sight signal communication between said communication devices of said plurality of aerial platforms and said land terminals; a network of communication links interconnecting said plurality of land terminals; and said plurality of encrypted devices capable of communicating with said plurality of communication transceivers and addressable from one or more of said plurality of communication transports carried on a platform.

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Another embodiment is an aerial constellation comprising a plurality of lighter-than-air platforms spaced above a contiguous geographical area, so that a substantially ubiquitous line of sight coverage of said geographical area is provided; each of said plurality of platforms comprising an enclosure maintaining a regulated volume of low density gas so that the total density of said platform is lower than atmospheric air to a predetermined altitude range; and each of said plurality of platforms further comprising a signal transmission device affixed to said enclosure by means of which signals from said platform can be transmitted to said contiguous geographical area.

Another embodiment is a communications platform that is lighter than air at a regulated altitude comprising a low density gas enclosure for maintaining a low density gas amount; a transceiver attached to said housing including an electronic circuit and an on-board electrical power source; and an altitude regulator attached to said platform for regulating the altitude of said platform in a predetermined altitude range, said altitude regulator comprising a mechanism. altitude determination; a controllable ventilation from said gas information and ventilation controls operatively coupled to said altitude ventilation gas for regulating the altitude of said platform; and a controllable ballast release affixed to said

61/125 platform and ballast controls coupled to the referred altitude determination mechanism for ballast release to regulate the altitude of said platform.

Another embodiment is a free floating constellation communications system comprising a plurality of lighter than air platforms comprising at least a first platform and a second platform, the first and second platforms comprising a communications signal transceiver and being free floating without any control of longitude and latitude position; and a plurality of communications devices in a contiguous geographical area, at least one of the communications devices having a communications capability with the communications signal transceiver; where at least one of the communications devices is capable of transferring communication from the first platform to the second platform, as the first platform moves out of a communication strip of at least one of the communications devices, and where the free floating constellation communications system provides wireless data line-of-sight coverage for a population on a contiguous land span and the plurality of lighter-than-air platforms is launched in such a way that, when in operating range of 18,288 to 42,672 km, there is substantially a relative distance between the plurality of platforms lighter than air. 0 free floating constellation communications system (CCS) could still comprise an altitude regulating device; a plurality of management launchpads spaced out from which the said management

62/125 plurality of platforms can be launched; a plurality of ground terminals, and a network of communications links interconnecting at least some of the ground terminals to each other. Preferably, the regulator is operatively connected to regulate the platform to float in the Earth's stratosphere. Preferably, a predetermined altitude range within which the plurality of platforms are regulated to float comprises a range of about 21.336 km to about 30.48 km. 0 The regulator regulates the floating of the platform in a range of predetermined altitude and comprises a quantity of gas contained having a density less than the density of the air in the range of predetermined altitude and a controllable ventilation through which a portion of the quantity of gas contained can be released to reduce the buoyancy of the platform. 0 The regulator comprises a quantity of high density material carried on board the platform and a release device by means of which a portion of the high density material can be released to increase the buoyancy of the platform. Preferably, the regulator comprises: a controllable gas vent; a controllable ballast release device; an altitude determination mechanism; and a control signal processor device connected with the transceiver, the altitude determination mechanism, the gas vent and the ballast release, so that the altitude can be adjusted.

Preferably, the communication system of the plurality of spaced ground terminals comprises a transceiver. The CCS could still comprise a device

63/125 tracking, where the tracking device would comprise: a directional antenna; and a mechanism for aiming the directional antenna in response to GPS coordinate data to selectively target the directional antenna on one or more of the plurality of platforms. 0 tracking device comprises: a directional antenna; and a directional antenna targeting and gain tracking mechanism to target the directional antenna on a selected platform according to a signal strength of the communication between the selected platform and the directional antenna. Preferably, at least one of the land terminals comprises a network operation center.

CCS could still comprise a network operation center (NOC) connected to the communications link network. The different variations in the NOC connections are as follows. The NOC is connected to at least some of the plurality of ground terminals with a connection center and communications link radius arrangement. The NOC is connected to at least some of the plurality of ground terminals with a communications link mesh arrangement.

Other variations are as follows. The network of communications links interconnecting the terminals on land comprises connections for land lines. The network of communications links interconnecting the land terminals comprises communications connections by space satellite. The network of communications links comprises component connections from platform to platform.

Other variations include the following. The plurality of platforms comprises a device lighter than air

64/125 selected from the group consisting of a balloon, a small airship balloon, an airship, a zeppelin, an aircraft, an airship, a climate balloon, a spherical balloon made of a metallized polyester film, an air balloon hot air, a sound balloon and a weather balloon and combinations thereof. The plurality of platforms comprise rubber balloons. The platforms have zero pressure balloons, balloons with internal air blades, adjustable volume balloons or balloons filled with hydrogen.

Other variations include the following. Communications devices include radio call equipment, advanced message sending devices, cordless phones, telemetry devices and equipment tracking units.

Still other variations include the following. The platform comprises a rapid descent mechanism; and the platform is disposable. The platform comprises a balloon; the platform comprises a rapid lowering mechanism; and the balloon is replaceable for transceiver recovery and reuse.

Still other variations include the following: the communications signal transceiver comprises a circuit capable of communications using a Frequency Division Multiple Access Protocol (FDMA), a Time Division Multiple Access Protocol (TDMA), an Access protocol Code Division Multiple (CDMA), ReFLEX protocol, Flex protocol, POCSAG radio call protocol or ERMES radio call protocol.

The CCS could still understand a mechanism for

65/125 altitude determination; a source of meteorological data; and controls for adjusting the altitude of a platform at a speed and wind direction determined according to weather data.

The CCS could still comprise an altitude sensor on board at least one of the plurality of platforms; and a steerable antenna coupled to at least one of the communications signal transceivers and attached to at least one of the plurality of platforms, the steerable antenna having stabilization controls for stabilizing the steerable antenna in one direction from the platform providing consistent ground coverage across the geographical area and a crosshair control operatively associated with the steerable antenna and the altitude sensor for selective change of area position antenna coverage to facilitate the filling of coverage spaces by the geographic area.

The CCS could still comprise an unmanned free balloon; and a payload box having a total weight of

<td>less than 2,721</td><td>kg</td><td>and</td><td>surfaces</td><td>external</td><td>with areas</td>

<td>predetermined and</td><td>what</td><td>has</td><td>a relationship</td><td>of weight</td><td>for size</td>

<td>of no more than</td><td>what</td><td> 85,</td><td>048 g for 6</td><td>.5 cm²</td><td>in any</td>

package surface, determined by dividing the total weight in ounces (1 oz = 28.34 g) of the payload box by the area in square inches (1 in² = 6.45 cm²) of its smallest external surface.

Other variations include the following. At least one of the plurality of platforms still comprises an altitude regulator operatively connected to the platform to float in a predetermined altitude range after ascension

Initial 66/125; where the altitude regulator still comprises: a quantity of high density material; a device for determining the platform altitude, where the device for determining the platform altitude comprises a global positioning system (GPS) receiver; and a material release mechanism for releasing a portion of the amount of high density material.

The CCS could still comprise a hydrogen gas envelope for maintaining an amount of hydrogen; an on-board electrical power source on at least one of the platforms, where the on-board electrical power source comprises a fuel cell interconnected with the hydrogen gas envelope for receiving hydrogen as a fuel component for the fuel cell; and an altitude regulator affixed to the platform to adjust the height of the platform in a predetermined altitude range, the altitude regulator comprising: an altitude determination mechanism; controllable ventilation from the gas enclosure and ventilation controls operatively coupled to the altitude determination mechanism for hydrogen gas ventilation to regulate the platform's altitude; and a controllable ballast release attached to the platform for ballast release to regulate the platform's altitude. In variations of the same, the controllable ventilation and ventilation controls are operatively coupled to this, still comprising at least one Nickel - Titanium (NiTi) element mechanically coupled to the control ventilation and operatively connected to the power source

67/125 electrical to selectively receive and not receive electrical power to thereby selectively change the length of the NiTi element for opening and closing controllable ventilation. The CCS could still comprise a weather package connected to the platform through a fiber optic connection to the transceiver, thereby substantially avoiding an electrical arc formation between the weather package, transceiver when the platform moves through electrically charged clouds and a tracking system capable of tracking one or more of the plurality of platforms.

Other variations include the following. The network operation center comprises a circuit for controlling a predetermined operation of the platform.

The CCS could also comprise a rapid deflation system for removing a platform from the air due to a malfunction or improper location of the platform.

Another embodiment is a floating constellation communications system comprising a plurality of lighter than air platforms comprising at least a first platform and a second platform, each of the first and second platforms comprising a communications signal transceiver and being free floating. without any control of longitude and latitude position; and a plurality of communications devices in a contiguous geographical area, at least one of the communications devices having a communications capability with the communications signal transceivers;

68/125 where at least one of the communications devices is capable of receiving communications from the first platform's communications signal transceiver and the second platform's communications signal transceiver, but listening to communications only from a communications signal transceiver and the plurality of lighter-than-air platforms is launched in such a way that, when in an operating range of 18.288 to 42.672 km, there is substantially a relative distance between the plurality of platforms lighter than air.

Yet another embodiment is a free floating constellation communications system comprising a plurality of lighter than air platforms comprising at least a first platform and a second platform, each of the first and second platforms comprising a communications signal transceiver and being floating free without any control of longitude and latitude position; and a plurality of communications devices in a contiguous geographical area, at least one of the communications devices having a communications capability with the communications signal transceivers; where the first and second platforms dynamically assign new frames in which they transmit a communication signal from the communications signal transceiver, as the platforms derive, so that a communications device receives communications signals from only one communications signal transceiver on a particular frame and the plurality of lighter-than-air platforms is launched in such a way that, when in a

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18,288 to 42,672 km, there is substantially a relative distance between the plurality of platforms lighter than air.

Yet another modality is a method of communication using a free floating constellation communication system comprising the provision of a communication device for communication with platforms lighter than air; communication with at least one platform lighter than air when the communication device is in a communication range with the first platform lighter than air, communication with a second platform lighter than air when the communication device is move out of the communication lane with the first platform lighter than air, where each of the first and second lighter-than-air platforms comprises an altitude regulating device and a communications signal transceiver, and where the first and second lighter-than-air platforms are free-floating, without any control of position of longitude and latitude, and the plurality of platforms lighter than air is launched in such a way that, when in an operating range of 18.288 to 42.672 km, there is substantially a relative distance between the plurality of platforms lighter than air.

Yet another modality is a method of communication that uses a free floating constellation communication system comprising the provision of a plurality of lighter than air platforms comprising at least one first platform and a second platform, each of the first and second platforms comprising a

70/125 communications signal transceiver and being free to float without any longitude and latitude position control; and communicating with a communication device that has communication capabilities with the communications signal transceiver, where the first and second platforms dynamically assign new frames in which they transmit a communication signal from the communications signal transceiver, as the platforms derive, so that a communications device receives communications signals from only one communications signal transceiver in a particular frame and the plurality of lighter-than-air platforms is launched in such a way that when in an operating range of 18,288 at 42,672 km, there is substantially a relative distance between the plurality of platforms that are lighter than air.

Another modality is a method for the provision of a communication service that comprises the provision of a first platform that is lighter than air; the provision of a second lighter-than-air platform, where the first and second lighter-than-air platforms each comprise an altitude regulating device and a communications signal transceiver, where the first and second lighter platforms that the air is free floating without any control of longitude and latitude position; the provision of a plurality of communication devices in a contiguous geographical area, at least one of the communications devices having a communications capability with the communications signal transceiver, where at least one of the communications devices is capable of transferring communication with the first platform for

71/125 the second platform, as the first platform moves out of a communication strip with at least one of the communications devices, and where the free floating constellation communications system provides wireless data line of sight coverage for a population on a contiguous land extension and the plurality of platforms lighter than air is launched in such a way that, when in a range, operating from 18.288 to 42.672 km, there is substantially a relative distance between the plurality of platforms lighter than air.

The variations include the following. The communication device comprises radio call equipment, an advanced message sending device, or a cordless telephone. The altitude regulator device regulates the platform's altitude within a predetermined altitude range between about 18,288 and about 42,672 km. The altitude regulating device is operatively connected to regulate the platform to float in the Earth's stratosphere. 0 altitude regulator regulates the floating of the platform in a predetermined altitude range and comprises an amount of gas contained having a density less than the density of the air in the predetermined altitude range and a controllable ventilation through which a portion of the amount of gas contained can be released, to reduce the buoyancy of the platform. 0 The altitude regulator comprises a quantity of high density gas material carried on board the platform and a release device, through which a portion of the high density material can be released to increase the buoyancy of the platform. 0 device

72/125 altitude regulator is operatively connected to regulate the platform to float in the Earth's stratosphere. 0 altitude regulator regulates the floating of the platform in a predetermined altitude range and comprises an amount of gas contained having a density less than the density of the air in the predetermined altitude range and a controllable ventilation through which a portion of the amount of gas contained can be released, to reduce the buoyancy of the platform. The altitude regulator comprises a quantity of high density gas material carried on board the platform and a release device, through which a portion of the high density material can be released to increase the buoyancy of the platform. 0 The altitude regulator comprises a quantity of high density material carried on board the platform and a release device, through which a portion of the high density material can be released to increase the buoyancy of the platform.

Figure 12 depicts a schematic view of a portion of the constellation and communication network system 10 according to the present invention, in which aerial platforms 12 (a) to (g) have reached a desired altitude in a range of altitudes, such as as in the stratosphere. An aerial platform 12 (h) is also described in the ascension process to a desired altitude. Each aerial platform comprises a lighter-than-air gas enclosure 14 (a) to (h), a platform and communicator control device 16 (a) to (h) and an antenna 18 (a) to (h). Platform-to-ground communication signals are schematically represented in

73/125.

(a) to 20 (u) correspondingly in communication with a plurality of ground communication devices, such as radio signal receivers, transceivers, transmitters or radio call equipment 22 (a) to 22 (u). There are a plurality of launch and tracking terminals 24 (a) to (d), each having a plurality of tracking antennas 26 (a) to (o). The ground terminals transmit message and control data between the SNS platforms and the NOC. Preferably, the ground terminals can operate without assistance, requiring only electrical power and communications signals. Ground terminals consist of a set of transmitters and receivers and their controller, tracking antennas and a tracking controller, redundant communication links to the NOC, and a reserve power supply. To accommodate the potential of various platforms in the range at any given time, four to six separate transmitters, receivers and monitoring antennas are currently contemplated. Genera and Motorola offer appropriate commercially available transmitters, transmitter controllers and receivers for SNS ground terminals although some modifications are required. The accompanying antennas 26 are shown schematically in communication with the various platforms via ground signals for platform 28 (a) to (g). A ground communication network 30, having interconnection segments 30 (a) to (d) is described in communication between the launch and monitoring stations 24 (a) to (d) and a network operation center

40. The network operation center 40 can also be

74/125 communicating with a plurality of launch and tracking terminals 24 via an orbiting satellite 32 and launch site satellite antennas 38 (a) to (d) and a network operating center satellite antenna 42.

For illustration purposes, the launch and tracking terminal 24 (c) is co-located with an aerial platform launcher 44, similar to the same balloon launcher from the National Weather Service. An aspect of the invention also contemplates a launcher and mobile tracking terminal

LO 46, such as, for example, an independent unit mounted on a truck trailer. The mobile launcher can be transported to a desired launch site, parked there and additional SNS platforms can be launched. The monitoring and communication terminals 24 can be connected to the network via ground connections 30 (c) and 30 (d), as well as other launch stations and the network operation center 40. The mobile launcher and terminal can be periodically moved from one location to another location for launching and / or monitoring additional SNS communication platforms 12 (a), as needed, to fill coverage spaces, as they may arise due to climate conditions.

Figure 13 is an enlarged schematic description of the mobile SNS launcher 46 of Figure 12, shown schematically in relation to platforms 12 (f), 12 (g) and (e) that form a portion of the platform constellation. The mobile SNS launcher is in communication with the network operation center 40. A range of desired altitudes 50 defined by a minimum desired altitude 48 and a maximum desired altitude 52, is described in Figure 12.

75/125 altitude measured in relation to sea level 54. In a preferred mode, a minimum desired altitude of about 18,288 km and a maximum desired altitude of about 42,672 km define a predetermined range of altitudes. These altitudes generally correspond to the stratosphere or a range of stratospheric altitudes 50. A cover space 56 between spaced platforms 12 (g) and 12 (e) is also described in Figure 12 schematically represented as a spaced distance 56 which is significantly greater than the desired spaced distance 58 between platforms 12 (f) and 12 (g). In another preferred mode, it is anticipated that the platforms will be regulated to float in a range of predetermined altitude between about 21.33 6 km and about 3 0.48 km, will have a coverage radius measuring about 280 km, will be above commercially regulated airspace and will be below altitudes at which platform survival is less certain. When the distance between two adjacent platforms in any direction is greater than about one and a half times the coverage radius, a gap in the coverage may begin to occur. In such cases, a mobile launch unit 46 can be moved on the ground to a location substantially between the two spaced platforms 12 (g) and 12 (e), so that an additional supplementary platform 12 (h) can be launched for rapid ascent. up to the desired altitude range 50. Computer modeling based on tracking all platforms 12 in a constellation 10 of aerial platforms can be used to predict the development of significant spaces 56 on the roof and quickly employ launch units

76/125 furniture to fill the spaces. In the event that a stationary launch and tracking terminal is already at the location for launching a supplementary SNS platform, no mobile units would be required.

Figure 14 is a schematic description of interplatform communications with subsequent transmission to land terminals and a network operation center (NOC).

Figure 15 is a schematic description of platform satellite communication links for the provision of network interconnection with a network operation center (NOC).

Figure 16 is a schematic description of a connection center and lightning network communication link topography. This is advantageous because there are generally fewer lines of communication in total and equipment generally less expensive than the provision of a ring topology.

Figure 17 is a schematic description of a mesh network communication link topography. The ring topology essentially links all the ground stations together in a large ring of communications links by Daisy chains. This ring is generally considered to be sturdy. If one or two points fall on the ring, this could isolate the ground terminals otherwise in operation.

Figure 18 schematically describes a contiguous geographical area 100 and, in particular, by way of example, a geographical area corresponding to the United States of America. Overlap in the geographical area 100

77/125 selected standardized launch sites represented by Xs 101 to 170. Coverage areas 201 to 270 are still described schematically representing the position and coverage of each of platforms 101 to L70, as they reach a desired regulated altitude, preferably in the stratosphere. Each platform is very small, compared to existing synchronous orbiting satellites, so they were referred to and designed to float at an altitude

L0 regulated in the stratosphere, so that they were designated as stratospheric nanosatellites (SNS). Coverage areas 201 to 270 are described in Figure 14 assuming a relatively vertical rise from launch sites 101 to 170. Coverage areas 201 to 270 will migrate over a period of time, due to wind and weather conditions in a location in particular. However, the ascent to the desired stratospheric altitudes usually takes about one to two hours, so that it drifts to normal air velocities

0 less than about 16.1 to 32.2 km / h and even passing through a jet stream, if present, produce relatively small drifts of 16.1 to 12 8.7 km in any direction during the ascent. Thus, in relation to approximately 280 km, the coverage radius for an area

5 of circular coverage having a diameter of 560 km, migration over a short period of time with standardized wind conditions from 16.1 to 64.4 km indicates that the launch site is an approximately reasonable one for the initial high altitude location in the end of the ascent.

0 The balloon platform 12 is provided with mechanisms

78/125 altitude control, including low density gas ventilation and high density ballast drop mechanisms, allowing the balloon to be controlled to maintain a desired altitude in a range of desired altitudes. Altitudes can be maintained for between 12 and 24 hours corresponding to the current NWS balloon launch schedule of two launches per day. If the NWS launch schedule is not used, balloon altitudes can be maintained for more than 100 hours, depending on the lift gas, power and ballast remaining in balloon 12. In the case of NWS balloons, balloons today self-destruct from overexpansion as they reach and exceed altitudes of more than 30.48 km and weather data is accumulated and transmitted to the ground during the ascent. In the case of balloons acting as carriers for communication platforms, the platforms will be maintained at an altitude of preferably less than 42.672 km. And, more preferably, less than 30.48 km and will continue to migrate, due to stratospheric wind conditions. 0 NOC can command SNS platforms to quickly deflate or explode, in the event of a balloon 12, when the platform is no longer needed, falls below 18,288 km and no ballast remains, it drifts over an unwanted area or it malfunctions. The platform can initiate this if any of these conditions are met and the platform has lost communication with the ground terminals. Advantageously, the wind conditions will have been detected during the ascent and will continue to be monitored by monitoring the stations in

79/125 earth. This will facilitate the prediction of the development of any roof spaces that could be expected, and particularly the location of these spaces and the number of ground communication devices or radio call equipment that might need to be served in the space area.

Figure 19 is a schematic description of geographic area 100 after a given period of migration during which significant spaces may begin to occur. The mobile units can be positioned at temporary launch sites 171 and 172 to fill development spaces 56 (b) and 56 (c). Also, where a space is predicted to develop in close proximity to a standard launch site, as, for example, in 105, an additional platform can be launched from launch site 105 in advance of the launch time. normally regular release. Thus, space 56 (c). In a similar way, a plurality of mobile launch sites typically located regionally can be used to fill spaces as they arise. In the case of a space development pattern if detected, then additional permanent launch locations 173 and 174 may be added, to help compensate for repeated developments of spaces 56 (d) and 56 (e), for example. Temporary launch locations can be moved seasonally to fill spaces along the coastline along the direction that the wind is blowing through the season, for example, the west coast during the winter season.

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Figure 20 shows a schematic side elevation view of a platform 12 in a modality in which the low density gas casing 70 is preferably a latex balloon 70. A Totex 100 balloon filled with hydrogen and internally coated to reduce the diffusion of hydrogen adequately provides elevation for the SNS communications platform. The Totex balloon is released with a diameter of about 1.6 m and expands to about 7.3 m through the altitude of 42.672 km. It will be noted that other lighter-than-air wrappers, such as small airship balloons, aerostats, zeppelins, aircraft, airships, weather balloons, spherical balloons made of a metallized polyester film, hot air balloons, sound balloons or weather balloons, also could

L5 be used in place of the proposed latex climate balloon 70 described schematically in Figure 6. Also, the diameter of balloon 70 in Figure 6 is not to scale and a total platform weight, including payload box 300, is expected , the altitude control ventilation mechanism

0 72, weather package 82, antenna 76 and weather cable connection 84. Preferably, cable 84 is a fiber optic cable having a length of approximately 25 meters, so that the meteorological data collection package 82 is sufficiently distanced from the balloon

70 to reduce to a minimum the turbulence effect caused by the balloon on the meteorological data by the meteorological package 82. The fiber optic cable 84 is used for the transmission of meteorological data from the meteorological package 82 to the communications unit 74. 0 fiber cable optics is used, since a wire would arch due to the

81/125 high potential electric field when passing through thunderclouds.

There are numerous types of low density gas casing devices and, in particular, balloons, which could be considered useful for the present invention. Among the potentially preferred types of balloons are rubber pressure balloons, zero pressure balloons, inner air foil balloons, adjustable volume balloons and overpressure balloons. Each type of these balloons has different advantages and disadvantages and, for the purposes of the present invention, it has been found that the rubber pressure balloon is the most preferred and the zero pressure balloon is also considered a preferred alternative.

Rubber pressure balloons have a distensible rubber membrane containing the lift gas, which allows the balloon to increase in size as the external air pressure decreases as the balloon rises. This is the most common type of climate balloon and is also consistent with party balloons. The primary advantage is the low cost and common accessibility, so that high quality balloons of this type, such as climate balloons, are available at a low cost. These balloons are a little fragile and they have delicate handling requirements and also low extended reliability. In addition, the use of these balloons requires ventilation of the elevation gas, to avoid an explosion when reaching maximum altitudes.

Zero pressure balloons consist of an initially loose bag, usually made of a plastic, such as polyethylene or Mylar. As the pressure of the outside air decreases, the bag increases in volume. Once the bag

82/125 reaches its full volume, the gas must be vented or the balloon will explode, as the material in the bag does not stretch. Although this type of balloon is more reliable than rubber balloons and provides less diffusion of lift gas, it is of average cost, more expensive than rubber balloons, currently between about four and ten times more expensive. Thus, although the rubber balloon could be more preferred for low cost platform purposes, the zero pressure balloon also provides a useful casing for lifting the platform and has certain advantages over rubber pressure balloons.

The inner-air balloon balloons consist of a flexible balloon containing air enclosed in a fixed volume balloon containing a lift gas. The air is pumped into the internal flexible balloon, which compresses the elevation gas trapped in the fixed volume balloon, thereby decreasing the overall elevation. Air is let out of the internal flexible balloon to increase the elevation. Small airships adjust elevation using this principle. This type of balloon has certain advantages, as there is no lift gas lost when reducing the lift and it is potentially more reliable than rubber balloons, although it is more expensive due to the extra balloon, pump and power extra operation required to increase and decrease the lifting mechanism.

Adjustable volume balloons consist of a fixed volume containing the lifting gas and a mechanical way of reducing the volume of the balloon. By decreasing the volume, the elevation gas is compressed and the elevation decreases. The volume can be reduced in several ways, including a line

83/125 adjustable inside the balloon from the top of the balloon volume decrease. This has less diffusion of the lift gas, theoretically, the lift gas is not lost when reducing the lift, and can be more reliable than rubber balloons. However, it has a more significant cost, due to the mechanical volume reduction mechanism, and still requires extra power to operate a mechanical volume reduction mechanism like this.

Overpressure balloons have a fixed volume. They are called overpressure balloons because they do not expand to match the decreasing external pressure. They are built strong enough to maintain internal pressure. Balloons can achieve extremely long float positions because they do not need to vent gas to prevent an explosion and typically they have a very low membrane gas diffusion. This type of balloon is the most expensive, although one of the most reliable, with little loss of lift gas. The extremely high cost and difficulty of manufacture and the lack of technology developed with reference to these balloons indicate that other alternatives are currently more attractive.

A signal transmitting antenna 76 extends from the communication device 74, preferably vertically downward from the communication device 74 and, preferably, a collinear arrangement with approximately 6 downward tilt cranes configured to provide a uniform transmission and reception coverage over the entire circular coverage area. Antenna 77 can advantageously be provided with a

84/125 support loop 86, to facilitate stabilization between the antenna and the meteorological connection cable 84. Also described in Figure 6 is a balloon destruction mechanism 78 and a parachute 80 for retrieving the communication device 74, when the balloon is destroyed by the controlled destruction mechanism 78 or otherwise by natural causes.

Figure 21 describes a partial partial cross-sectional front view of a modality of a communication device 74 according to the present invention. There is a payload box 300, including an inner container 302 and an external Styrofoam insulation 304 surrounding the inner container 302. In container 302 there is a circuit board 306 to which various electronic components are attached and interconnected for the provision of signal communication and remote control of the platform, as desired. The electronic section consists of the RF section, antennas, GPS receiver, processor and power regulators. The RF section is based on the low-cost transmitter and receiver section of current two-way radio call equipment. The transmitter power is increased to approximately 7 Watts. A single 900 MHz collinear dipole array antenna serves both transmission and reception functions. Additional antennas can be added for door RF connections to the ground terminals, if additional frequencies become available. Possible frequencies include the 1680 MHz band assigned to meteorological instruments. If the SNS system also collects weather data for the NWS and this data is transmitted in the weather aid band, it can

85/125 it is possible to send additional port traffic with weather data. A twelve-channel GPS receiver in conjunction with the processor provides position information for the NWS during an ascent and for the SNS NOC for the entire flight. The NOC uses the information for the location of the SNS platforms, for determining holes or cover spaces, and for making rudimentary position adjustments by varying the altitude at favorable wind speeds and directions.

The embodiment described in Figure 21 and a. partial lateral cross-section thereof, as described in Figure 22, shows the power for the communication device 74 being provided by a plurality of light weight high-power batteries 308 (a), (b), (c) and (d) . The predetermined platform requires between 13 and 18 Watts of power, depending on the message traffic and the platform configuration. Sulfur dioxide and lithium batteries (LiSO₂) are cost and weight effective and have decent operating characteristics in a low temperature environment, as found at high altitudes. Batteries are positioned in alternate spaced positions so that a maximum unit volume density is maintained below the maximum unit volume density requirements for federal aviation safety standards. The low unit volume density and low total payload weight prevent the launch of balloons from being restricted by FAA regulations. There is a bottom opening 310 through which the weather connection cable 84 connects in a release cable connector 312 to the circuit board 306 inside the container

86/125

302. Also, antenna 76 is attached to an antenna connection 314 located in the bottom opening 310, so that signals can be received or transmitted via antenna 76 to and from circuit board 306. The weather cable data fiber optic 84 can be received and processed into circuit board components 306 or can be transmitted directly to ground terminal 24 via antenna 76. Active antenna stabilizers 316 are provided for reducing and damping the movement of the antenna 76, so that a consistent container and signal transmission are performed. To facilitate the adjustment of the altitude of the aerial platform 12 and the attached communication unit 74, the payload box 300 includes a ballast storage chamber 320 in which the ballast 318 is carried. Ballast 318 preferably is easily movable lead shot, metal BBs or spherical glass beads that can be released in a controllable manner as with a ballast drop gate, such as a plug, which moves alternately between the

<td>opening</td><td>to the</td><td colspan="2">camera of</td><td>ballast</td><td> 320</td><td>and then for the</td>

<td>hole</td><td>about to leave</td><td>in</td><td>ballast</td><td>324, of</td><td>mode</td><td>that the ballast can</td>

<td>fall from</td><td colspan="2">opening</td><td>in</td><td>bottom</td><td> 310,</td><td>as described</td>

schematically at 326. For convenience and to avoid power depletion during storage or transport, a 328 manual circuit activation switch is provided.

At the top of the payload box 300 is a balloon connection shaft 334 which has a distal narrowing top 3 32 on which the flexible balloon connection narrowing 330 is affixed. The narrowing of the balloon connection

87/125

0 it is sized for adaptation on the shaft and is extended and moved downwards to a stop ferrule 336, so that it is secured in position with one or more heavy rubber bands 338. For convenience, a rubber band storage channel 340 is provided below the stop ferrule. A rubber band is stored and is in position for fixing a lighter casing than fresh air or balloon 70. Preferably, balloon 70 will be filled with helium (He), hydrogen or natural gas through a light gas filling valve 344, which is preferably positioned above rain hood 342, which isolates the payload box and certain components from the rain and another fallout. The light gas fill valve 344 provides a convenient connection to a light gas supply tank, such as a helium or hydrogen supply cup, so that an expandable balloon is affixed in its nip 330 to the 334 axis and a gas filler can then be supplied in a desired amount to the affixed wrapper or balloon. A 346 gas pressure sensor tube communicates between the inside of the spindle for transmitting the gas pressure from the internal balloon of sensor 348 connected to the circuit board electronics. A gas temperature sensor 350 is attached and, desirably, is positioned at or above the narrowing top 332. A temperature sensor wire 352 communicates a signal representing the temperature for an appropriate circuit on circuit board 306. An ambient air temperature sensor 354 is also desirably provided, as well as an ambient air pressure sensor 356, both of which are connected for air communication.

88/125 ambient air temperature detected and ambient air pressure detected for the circuit board. A battery temperature sensor 358, a payload temperature sensor 360 and an altitude sensor 362 can all be connected to circuit board 306 for, desirably, the provision of information and an input for remote control and for maintenance of the aerial platform 12 functions using circuit 306. The data collected from the gas temperature sensor 350, the ambient air temperature sensor 3 54, the gas pressure sensor tube inlet 346 and the ambient air pressure sensor 3 56 are used, in part, to determine if the balloon is approaching an explosion condition. A heater and cooler device 364 is attached to control the internal temperature of the payload box. As the aerial platform rises to high altitudes, the ambient temperature drops dramatically and the interior of the box will desirably be heated by the heat generated by the batteries or, alternatively, by the heater 364. If the heat from the batteries were significant and were combined, for example, with bright sunlight, the internal temperature could rise above the desired operating temperatures, then the cooler portion of the 364 heating and cooling device could be activated for maintenance of a desired operating temperature range. The heating and cooling device can be a thermoelectric cell.

For the purpose of regulating the altitude of the balloon and, in particular, to prevent continuous rise above the desired maximum high altitude, a gas relief valve

Light 89/125 366 is provided. A spring 368 keeps the relief valve 366 normally closed. An actuator stem 369 is attached to valve 366 and to a valve actuator wire 370, for opening the valve against spring loading. A nickel - titanium (NiTi) wire can be used as the 370 actuator wire. The light gas relief valve 366 opens against spring charging when a small amount of current is passed through the NiTi wire causing it to retract or shorten a predetermined amount so that the relief valve is pulled out open, thereby allowing gases lighter than air to escape. The actuator stem can pass through the top of the container 302, preferably through a seal 371, so that the inside of the container is not directly exposed to the elements. The ballast shutter port 322 can be similarly activated with a ballast drop actuator wire 372, also made of nickel - titanium (NiTi). The similarly active antenna stabilizers 316 can be comprised of a NiTi wire.

A 374 weather drop control wire can also be NiTi and can be used to disconnect the weather probe after the weather data is no longer being obtained. Typically, weather balloons explode after passing through the stratosphere. Here, the balloon will vent some of the light gas to maintain a stratospheric altitude for a desired period of time. The destruction mechanism 74 can be remotely activated with the sharp end 378 of a pivoting destruction arm to cause the flow path to fall. The arm of

90/125 destruction 376 is spring loaded for rapid rotation for contact with the outside of the balloon, when a maintenance release pin 3 86 is pulled into a maintenance / release groove 384. The release pin 386 can advantageously be controlled with a control wire 388 also suitably activated via the circuit board by receiving remote signals via antenna 76 or the processor. A GPS 390 antenna connected to the circuit board is also provided inside the platform to receive position information from the GPS satellite system to facilitate the monitoring of the platform, as it migrates and floats over the contiguous geographical area of ​​coverage.

Figure 23 is a schematic partial lateral cross section of an alternative platform modality according to the present invention, in which the source of electrical power for the communication circuit and controls is a fuel cell 400. The fuel cell 400 advantageously it can be a proton exchange membrane (PEM) fuel cell of the type that uses hydrogen and oxygen for the provision of electrical power. This type of system requires a hydrogen tube 402 connecting from the hydrogen source, ie the balloon lighter than air 70 to fuel cell 400. A hydrogen inlet 404 is provided with a hydrogen circulator 406 , which can simply be a 406 fan. So, using the hydrogen tube, the hydrogen can be extracted from the balloon and introduced into the fuel cell 400. Also, there is a 408 hydrogen outlet that is recirculated back to the balloon. A pressure sensor

91/125 hydrogen tube 410 is provided for proper monitoring of the partial pressure of hydrogen in the fuel cell. A fuel cell of this type also requires an oxygen supply that can be provided by affixing an oxygen balloon 414 to an oxygen tube 412, so that the oxygen balloon is inside the hydrogen balloon envelope. The oxygen balloon is built to maintain oxygen at a significant internal pressure. This oxygen balloon 414 can be attached to tube 412 with a rubber band 416 and an oxygen pump 418 moves and additionally pressurizes oxygen from oxygen balloon 414 to the fuel cell through an oxygen inlet 420. Again , for regulating the process, an oxygen pressure sensor 422 is provided. The fuel cell reaction results in water as a by-product. The water is kept in a liquid state by the heat generated by the fuel cell and is desirably drained, before it can freeze at the high altitudes at which the platform operates.

Figure 24 is a schematic block diagram of the SNS platform hardware in payload box 300 and positioned on or interconnected with circuit board 306. A processor 430 receives an electrical signal input and provides an electrical signal output, interacting with a plurality of components to control fluctuation altitude, temperature, balloon destruction, ballast fall, etc. platform, and also for receiving, processing and transmitting communication signals received and transmitted to and from ground stations, personal communication devices or

92/125 other information communications. Initially, block 432 represents batteries 308 or fuel cell 400. Block 434 represents on / off switch 328 for activating the power supply for a power supply regulation circuit 436 with available output power 438. For clarity, the individual power connections for various operating and control devices have not been shown in all cases. The power is supplied to the supply voltage sensor in block 440 and current supply sensor block 442, which provide information for an analog to digital converter 444. The analog to digital converter also receives various information from the payload fuel cell temperature gauge and would hit block 446, both gas and ambient air temperature readings in block 448 and the gas pressure in block 450. Additional analog information signals are generally represented by block 452. The digitally converted information is variously provided to and received from a flash memory in block 454 and random access memory (RAM) in block 456. From converter A / D 444 and also from flash memory 454 and RAM memory 456, the processor has access to all the various input control data. During the rise of the SNS platform, the weather package represented by block 458 receives appropriate climatic information, including ambient temperature 460, ambient pressure at 462 and ambient humidity at 464. Antenna stabilization 316 represented by block 496 can be based on altitude sensor information that is

93/125 part of the SNS platform control system at 466 to stabilize the antenna 76. The information detected or accumulated by the weather package 458 is transmitted. For example, infrared transceiver 468 via a fiber optic cable in block 470 corresponding to physical fiber optic cable 84 and a processor infrared transceiver 472 through which serial meteorological data is transferred to processor 430 for proper transmission to the land terminals during the ascent of the SNS platform with the weather package 458 affixed. A GPS antenna block 474 corresponding to the physical GPS antenna 3 90, communicates via a GPS receiver 476, indicated with a port, and additionally synchronized with the GPS clock or the second hand in block 478. Thus, the position at particular times is provided for the processor. This positioning information is coordinated with the other meteorological input for determining the direction of lateral wind views from any part of the ascent, thereby corresponding to those wind speeds at particular altitudes and geographical locations during the ascent.

Communications are controlled by the 430 processor, preferably using a 900 MHz transceiver and a 480 modem and a port 82 and modem transceiver signal 4 82 to and from the collinear array antenna with an interface through a dplexer control information 486 received at the collinear array antenna 484, therefore transferred through the diplexer and one of the appropriate frequency transceivers to the processor 43 0 with a

94/125 input information of the ground signals and also the input information of the on-board sensors, as provided through the A / D converter 444, the GPS information of 476, the GPS time information 478 and the sensor information At altitude 466, various functions of the SNS platform can be controlled, including the gas vent in block 488 corresponding to the gas vent actuator 370. Ballast drop is also controlled in block 490 corresponding to physical ballast drop actuator 372. The meteorological pack fall controlled schematically in block 492 corresponding to packet drop actuator 374. The balloon destruction control is described in block 494 corresponding to the destruction actuator 376. Antenna stabilization can be performed according to the controls in block 496 corresponding to the antenna stabilization mechanism 316. The payload temperature, heating and cooling controls can be controlled in block 498 corresponding to heaters and coolers 364. Additional functions as can be additionally included are provided with controls in block 500.

One embodiment of this invention relates to an elevation rate control system for LTA. A typical National Weather Service balloon system, as it is well known, consists of an extensible rubber balloon filled with a lift gas, a parachute tied to the balloon, a line that extends downward from the parachute and a radiosonde tied to the end of that line. The radiosonde collects and transmits weather-related data down to a station on land, according to the

95/125 balloon goes up through the atmosphere.

National Weather Service requires that weather balloons rise at a standard rate of 304.8 meters per minute. This is almost impossible to maintain throughout the balloon elevation, due to many factors, including the variance with the altitude of the pressure and temperature of both the elevation gas and the ambient air, the variance in the balloon material, the process of manufacture, and the physical change in the size of the balloon itself, as the balloon rises.

In addition, a significant number of NWS climate balloons do not reach the desired altitude of 30.48 km because, among other factors, the balloon expands significantly when it reaches high altitudes, becoming thin and often exploding in advance for the same reasons as listed above . If the amount of gas could be reduced at higher altitudes, the chance of the balloon exploding would be decreased.

The present invention utilizes an elevation rate control system for venting the elevation gas, as necessary, to slow the rise of the balloon to no more than 304.8 meters per minute. Additionally, due to the ventilation of the lift gas, the balloon size is reduced, increasing the probability of reaching the desired altitude of 30.48 km without exploding.

elevation rate control system consists of a ventilation mechanism attached to the balloon's narrowing, which can release the balloon's lifting gas, a ventilation actuator for opening and closing the ventilation mechanism, an altitude sensor for determining altitude and the rate of elevation of the system

96/125 balloon, and a comparison mechanism or circuit to control the ventilation actuator to cause ventilation to release some lift gas, when the desired lift rate is greater than the desired value.

In one embodiment, a GPS unit provides the processor with elevation rate information. The processor compares the current lift rate with the desired lift rate stored in the processor's memory. For National Weather Service systems, the desired elevation rate is 304.8 meters per minute. If the current lift rate is greater than the desired lift rate, the processor directs the actuator to open the vent until the desired lift rate is reached.

In addition, a ballast system containing a ballast container, ballast and ballast actuator could be added to the elevation rate control system. The processor compares the current lift rate with a minimum desired lift rate stored in the processor's memory. If the lift rate is slower than the desired minimum lift rate, the processor can activate the ballast actuator to drop the ballast until the lift rate increases to the desired value.

The processor can first process the elevation rate data from the GPS unit by filtering the elevation rate values. This filtration may be necessary as the GPS data may be noisy. In addition, erroneous data may be present, and must be removed from the GPS data. The need for filtering or removing erroneous data will vary with

97/125 different manufacturers and models of GPS units. Alternatively, mechanical means for determining the elevation rate can also be used, instead of using the elevation rate information

GPS.

Another modality performs a transmitter geolocation from an LTA platform. Having the ability to locate specific wireless devices can be extremely valuable. For example, locating a missing semi-trailer equipped with a wireless tracking device could save a road transport company many thousands of dollars. Locating a party calling wirelessly through an emergency could save the party's life by calling appropriate emergency services. Many wireless device manufacturers are incorporating GPS in their devices, but for many devices this is not yet appropriate due to cost, size, battery power demands, poor GPS signal penetration into the operating environment and other factors. Inheritance devices will continue to exist on the market that do not have the capacity to provide their own location.

This invention provides a method of geolocation of a signal received by using delay measurements of signal path taken from one or more platforms lighter than the free-flowing high-altitude air. The method has the following advantages: the invention does not require that the wireless device it is accompanying contains a positioning circuit, such as a GPS, for this purpose.

98/125 mode by reducing the size, cost, weight and power of the mobile transmitter. It works with the currently available wireless devices, such as cordless phones, two-way radio call equipment, advanced messaging devices, wireless Internet access devices, and almost any wireless information access device. adding localization capabilities, without requiring a modification. It has a higher accuracy than just using the knowledge of which tower or which towers are currently receiving the mobile transmitter signal even with the use of sectored antennas. It does not require specialized directional antennas. Extremely large coverage areas can be provided from a single receiver.

The present invention uses multiple signal path delay measurements by high altitude platforms of the signal received from a wireless device to determine the position of the wireless device. This method can be used to locate registered wireless devices on a network supplied by the high altitude platform or to provide or supplement the location capabilities of existing land-based wireless networks from registered wireless devices on your network. In the latter case, the high-altitude platform only needs to measure the signal path delay of the wireless device and does not need to decode traffic from the wireless device.

This invention works with wireless transmitters whose transmissions are synchronized over time to a standard. This pattern can be a GPS timing or the timing of the

99/125 network where the received wireless device is registered. In most situations, timing comes from direct channel transmission to the wireless device. In this case, all wireless devices on the platform network have their synchronization synchronized with the transmissions received from the platform. The wireless device then uses this timing for transmissions back to the platform. Because of this, the start of a signal received on the platform of a wireless device is delayed by twice the signal travel delay of the distance between the platform and the wireless device (Figure 25). The signal path delay is measured by the platform and later converted to a distance. The distance from the platform to the wireless device is approximately Distance in meters = 300,000,000 * signal travel delay measured in seconds / 2.

If the platform uses a non-directional antenna and the wireless device is on the ground, an approximate circle can be drawn on the Earth's surface with the platform as the center of the circle. The radius of the circle is the distance from the platform to the wireless device. The wireless device is located in this circle (Figure 26). Since the trace is the intersection of the Earth's surface with a measured distance from the platform (the calculated distance from the signal path delay), and the terrain on Earth is not spherical, the trace does not form an exact circle.

A platform in a different position above the Earth receiving the signal from the same wireless device also measures a signal path delay. This delay is also converted over a distance and can trace approximately

100/125 a circle drawn on the Earth's surface of the possible locations of the wireless device, as described above. Again, this does not form an exact circle due to the Earth's terrain. The intersections of these two approximate circles give the potential locations of the wireless device (Figure 27).

A third position on a platform receiving the signal from the same wireless device also measures a signal path delay. This delay is also converted into a distance and can roughly draw a circle drawn on the Earth's surface from the possible locations of the wireless device. Again, this does not form an exact circle, due to the shape of the Earth and the changing terrain. The intersection of this circle with one of the two points from the previous intersection finally determines the location of the wireless device.

The geolocation of a wireless device, as described above, requires three measurements of a platform or platforms. The primary requirement is that the platform position be different for each measurement to allow the circles to form points at the intersections. It is possible to use a single platform by taking measurements in three different positions as the platform moves. It is best if the three measurements are made as close in time as possible or practical to each other, to reduce the chance that the wireless device has moved between measurements. Measurements do not need to be taken simultaneously as with other geolocation methods.

Although the single platform taking three measurements

101/125 separate signal path delay has the potential to be the least accurate, due to the movement of the wireless device, this does not hinder the capabilities of other platforms for locating a wireless device. This is especially true when the wireless device is using a platform to supply its network. Therefore, the most preferred modality is that of single platform geolocation.

Although three separate measurements of signal path delay are mathematically necessary for determining the position of a wireless device on the Earth's surface, two measurements may be sufficient if the wireless device is known to be in an area on Earth that is small in relation to the distance between the two points acquired from the intersection of the first two signal path delay measurements. This wireless device location can be assumed to be the closest point to the usual or most recent known location of the wireless device.

Using sectored or directional antennas on one or more platforms performing measurements can reduce the number of measurements required by two. For example, if two separate measurements are made from a platform or platforms with a 3-sector antenna, the circles drawn on the Earth's surface are reduced to 120 degree arcs. In most cases, the two arcs will only intersect at one point, that point being the location of the wireless device.

Satellite and terrestrial systems also employ several forms of geolocation, although the methods are

102/125 different. Satellite systems generally have GPS units onboard the wireless device and do not need to geolocate the device, or they use Arrival Time Difference (TDOA) calculations to obtain the location of the wireless device. The difference in arrival time requires that more than one satellite receive the wireless signal simultaneously. Also, satellite systems employing geolocation techniques can be based on ephemeris data to calculate the satellite's location. This mathematical method of determining location is not available for free drift platforms and therefore an additional sensor, such as GPS, is required for determining the position of the platforms. Low Earth satellite systems travel at significant speeds with respect to Earth (generally more than 27358.8 km / h) and therefore should consider Doppler in their techniques. The present invention is moving at such a rate that Doppler adjustments are not necessary (below 160.9 km / h). Terrestrial systems, such as the various voice networks, do not need to detect the position of the receiver, since the towers used are fixed. Nor do terrestrial systems require the ability to update their terrain maps when calculating the position of the wireless device, as the terrain does not vary for that tower. The present invention must do both, since it drifts free with the wind. An advantage of the present advantage is that excessive signal filtering is generally not required on a free drift platform in order to perform a geolocation, since there are no predominant transmitters nearby, as there may be for

103/125 terrestrial receivers. Reducing the amount of filtration in the receiver can mean a significant reduction in the size and weight of the required hardware.

The geolocation system consists of a land network, one or more high altitude LTA platforms and wireless devices located on the ground. The ground network consists of a receiver capable of receiving signal path delay measurement information from a high-altitude wireless LTA platform, and at least one processor that can receive data from the receiver. 0 processor is able to calculate distance from multiple signal path delay measurements, calculate distance vectors on terrain maps for determining distance circles, and determine intersections of circles and points on a terrain map for determining the location of a wireless device.

The lightest high-altitude air platform consists of a receiver capable of receiving a signal from a wireless device, a GPS unit capable of providing position and timing information, and a processor capable of measuring the difference between a standard timing and the signal received from the wireless device, a wireless data link from the platform to a land network to allow the receiver to send information related to signal path delay and a platform position to the land network.

The wireless device synchronizes its timing with GPS, the direct channel received from the platform or terrestrial network where the wireless device is registered. The receiver on the platform receives frames transmitted from

104/125 wireless device. The processor compares the arrival time of the frame received from the receiver with a reference timing of the appropriate network or the GPS to obtain the signal path delay. The processor sends the calculated signal path delay and the current platform location over the wireless data link to the ground network. The ground network converts the signal travel delay into distance and calculates an approximate circle on the Earth's surface, using the calculated distance to the wireless device as the radius and the platform position as the center of the circle. This circle is of approximate shape due to the Earth's terrain. The location of the wireless device is somewhere in this circle. A platform in a second position performs the same operation on the same wireless device to calculate an approximate second circle on Earth. The intersection of these two circles forms two points on the Earth's surface. A platform in a third position, again, performs the same operation on the same wireless device to calculate an approximate third circle on Earth, which intercepts one of the two points from the previous intersection. That point is the location of the wireless device.

When the platform is locating a wireless device registered to a terrestrial network, the platform land network must have access to the synchronization pattern used by the terrestrial network, as well as the location of the tower with which the wireless device is communicating, in order to measure the signal path delay, as this delay includes the signal path delay of transmission from the network tower to the wireless device, as well as the delay

105/125 signal path from wireless device to platform. In this case, the approximate circular trace in which the wireless device is located becomes an ellipse with the platform, and the terrestrial towers as the focal points of the ellipse. As the platform is at a significant altitude and has a large coverage area in which it can receive signals, when there is a need to locate a wireless device that is aligned with a terrestrial network, it is desirable to have the terrestrial network running the device wireless to switch to a less used or dedicated frequency. This reduces or eliminates the number of received signals seen by the platform when signal path delay measurements are made.

Depending on the protocol and frame structure used by the wireless device, the best feature of the frame for making the timing measurement may vary. The resource can be the beginning of a bit or a phrase, frequency or even change in amplitude.

The main sources of error when using signal path delay measurements for geolocation come from the wireless devices themselves, particularly the wireless device's ability to accurately match the timing of its transmissions to the timing of the received network. Half-duplex devices have much more difficulty in accurately synchronizing their transmissions to the direct channel, since they must maintain the system's internal synchronism between reception and transmission. An additional significant source of error comes from the platform receiver's timing resolution. For example, if the

106/125 platform receiver is 100 ns, this translates into an error of up to 300,000,000 * 0.0000001 / 2 or 15 meters of distance error.

Preferably, the LTA platform system of this invention is free floating, moves at a speed of less than 160.9 km / h, more preferably less than 80.5 km / h, and floats at an altitude between 18.288 and 42.672 km above the Earth's surface. Also, the geolocation system of this invention does not require that LTA platforms do not need to consider the Doppler effect differently from low Earth orbit satellites.

More scientific, commercial and other balloon payloads are valuable for the additional cost of retrieving them. The biggest problem with recovery of payloads is in the knowledge of the actual hostel location. In most situations, contact with the payload is lost when the payload falls below the horizon of the ground station and line of sight communications are lost. The location of the payload can only be estimated. If communication with the payload is requested at a relatively high altitude, the payload can drift a significant distance as it descends and finding the location of the payload becomes difficult. Satellite telemetry devices have been put into payloads to solve this problem, but they remain an expensive option. Climate services around the world currently launch approximately 800,000 radiosondes each year. Only about 18% of these radiosondes are recovered, reconditioned and regenerated. The National Weather Service does not have a way

107/125 to locate them once they are on the ground. A method of locating these payloads would significantly reduce the number of unrecovered payloads escaping to the ground.

The present invention uses a low-cost transmitter to send the GPS position of a landed payload to a second balloon in flight for transmission to a ground station, to assist in the recovery or confirmation of the landing location. The electronics for such a system is much less complex and expensive than that of a satellite telemetry unit, as the project does not need to incorporate processing for large Doppler effects. Also, the second balloon is significantly closer to the landed payload than even a low Earth orbit satellite, and therefore the location transmission device on the landed payload requires less transmission power than is needed to communicate with a satellite.

The payload location transmission device consists of a GPS unit capable of supplying position data, a transmitter capable of transmitting data in a desired protocol, such as FLEX or POCSAG at a desired frequency, such as the NPCS frequencies, a processor capable of reading data from the GPS unit and sending data to the transmitter for transmission, and a power supply capable of supplying power to the GPS unit and the transmitter. The processor is connected to the GPS unit in order to receive position and timing data. The processor is connected to the transmitter to allow the processor to send wireless data to the second balloon in

108/125 flight. The power supply is connected to supply the transmitter and the GPS unit with power.

processor receives position data from the GPS unit. In order to determine whether the payload has landed or is about to land, the processor looks for at least two conditions. The first condition is that the payload is not changing position (including altitude). Filtering of GPS position and altitude data may be necessary to allow this determination. The amount of filtration required depends on the actual GPS unit used, as some units provide filtered position data. The second condition is that the altitude of the landed payload is determined to be below a stored value, such as 4572 meters. Since most balloon missions operate over 18,288 km, this prevents the location transmitting device from transmitting during normal operation. Other conditions can be added to ensure that the payload has landed before the transmission begins. When the processor has determined that the payload has landed, the processor reads the current GPS position and sends it to the transmitter for transmission to the second balloon in flight. The processor continues to send position data to the transmitter at regulated intervals, such as once every 30 minutes. 0 second balloon in flight receives the position transmission and transmits the information to its ground station to assist in the recovery or confirmation of the landing location, as shown in Figure 9.

In an alternative mode, the transmitter is replaced by a transceiver capable of operating in a

109/125 desired 2-way protocol, such as ReFLEX, GSM, CDMA or iDEN or a desired frequency, such as the NPCS or BPSC frequencies. When the ground station wishes to determine the position of the landed payload and a second balloon in flight is in the communication range of the landed payload, the ground station sends a request to the location transmitting device transceiver through the second balloon in flight. 0 processor receives the request, queries the GPS for the position, and sends the position data to the transceiver for transmission to the second balloon in flight for transmission to its ground station to assist in retrieving or confirming the landing location, as is shown in Figure 9.

Alternatively, the transmitter could use a low-power unlicensed frequency.

A device such as the CreataLink 2XT by SmartSynch, Inc., has an integrated processor with a ReFLEX transceiver. This device could be used in place of a separate transceiver and processor.

If the mission of the second balloon in flight is to provide service as a wireless network for wireless devices, such as ReFLEX telemetry units or digital phones (using iDEN, CDMA, GSM, or other digital protocols used for voice services), the landed payload can operate with another wireless device on the balloon wireless network. This allows the landed load to perform its function of reporting its location to the ground station by simply acting as another wireless device in the system. The landed payload could then send a message or make a call to the ground station to

110/125 the provision of its location as another wireless device operating in the balloon service.

To reduce cost and complexity, an existing processor already in the payload that is performing other functions during the flight, but is inactive now that the flight has ended could perform the processing functions described above in order to save costs. The power needs of the location transmission device could also be met by the existing power supply of payload.

Another preferred application of the geolocation system and method of this invention is to monitor usage and determine the location of land-based vehicles, particularly semi-trailers. Knowledge of the location and movement of semi-trailers can significantly reduce their search costs when they are stolen or simply lost. It is also important to know when trailers require periodic maintenance. The road transport industry used mechanical tire rotation counters mounted on the trailer hubs to measure the distance traveled by the trailers primarily for maintenance purposes, but these must be manually read. The invention provides a low cost wireless medium for remote monitoring of location information and use of semi-trailers.

The present invention uses a GPS unit, a processor, a wireless transceiver, a power source,

<td>and a sensor</td><td>rotation</td><td>in</td><td>tire mounted in a housing</td>

<td>proof of time</td><td>posted</td><td>to</td><td>hub of a semi-trailer wheel</td>

<td>for the purpose of</td><td>measurement</td><td>gives</td><td>current speed, distance</td>

111/125 traveled, location and other values ​​related to the use of the semi-trailer and wireless transmission of this information back to a central office via a wireless network automatically or upon request.

In their preferred mode, a tire rotation sensor, a transceiver, a power source, a processor and a GPS unit are located in a weatherproof housing that is rotatably attached to the hub of a vehicle wheel ( Figure 28). The climate-proof housing does not rotate with the wheel, as it is rotatably attached to the wheel and is weighed to maintain an upright position at all times.

The processor is connected to the tire rotation sensor output and can communicate with the GPS unit for the purpose of receiving position, speed, direction and timing information from the GPS unit. The processor is also connected to the transceiver in order to exchange data and wireless control over the network with the central office. The power supply provides power to the GPS, the processor and the tire rotation sensor. The power supply can be batteries, solar cells mounted in the weatherproof housing so that they are visible externally, a generator that uses the rotation of the wheel with respect to the housing for generating electricity or, more likely, a combination of the three . If solar cells or a generator are used, the batteries must be rechargeable. If rechargeable batteries are used, a charging circuit receives power from the generator or solar cells, and charges the

112/125 rechargeable batteries with this power appropriately. The generator is mounted in the weatherproof housing and attached to the hub, so that when the vehicle is moving, the generator axis is rotated. Solar cells when sunlight is available and the internal generator when the vehicle is moving provide power for charging the internal rechargeable batteries through the charging circuit. The processor removes power from the GPS or brings power to the GPS in a low power mode when the GPS is not in use, to reduce power consumption. The processor can also put itself in a low power mode that wakes up when the tire rotation sensor detects movement, a query comes from the central office via the transceiver or a synchronized interval has elapsed.

In operation, the processor monitors the tire rotation sensor to determine vehicle speed and distance traveled. The processor consults the GPS unit to determine the vehicle's position, if significant tire rotations have occurred, or when consulted by the central office. Values ​​such as the maximum speed of the semi-trailer, the total distance traveled, and the total travel time are stored in the processor's non-volatile memory for transmission. Alternatively, the tire rotation sensor can be removed and the speed and distance can be computed by the processor using GPS data, such as magnetic direction, speed and position.

Upon request from the central office, at scheduled intervals, or at specific events, such as

113/125 when the vehicle starts moving or when the vehicle leaves a specific geographic area, the processor sends the required values ​​to the wireless transceiver for transmission to the central office. The transceiver communicates with the central office over a ReFLEX, CDPD, GSM, CDMA, TDMA, iDEN ™ network, or through another selected network. The transceiver can be replaced by a transmitter, if the network used does not require a device to have a receiver in order to operate on the network. The FLEX and POCSAG networks are examples of this.

Yet another embodiment of this invention is a targetable retrieval system that is applicable for autonomous GPS-guided parachutes and gliders. Steerable parachutes and gliders are important for recovering expensive payloads, safely avoiding crowded areas during a descent and for specific target shipping applications. Generally, the control systems for these targetable recovery systems are not designed for low cost, as the payloads themselves are very expensive and the control system is a fraction of the total cost. Recent, high-volume, low-cost balloon applications have made a simplified, lower cost control system more important. This invention reduces the overall cost of an autonomous addressable recovery system by using new algorithms that allow operation without the need for a compass and an airspeed indicator.

Steerable retrieval systems require five entries: (1) the current position of the steerable body;

(2) the target position in which the target body must land;

114/125 (3) the ground tracking vector; (4) the local wind vector; and (5) the flight vector. The three different vectors are used to control an autonomous targeting recovery system, the ground tracking vector, which is the direction in which and the speed with which the recovery system is moving with respect to the Earth's surface, the local wind vector which is the direction and speed of the wind in the recovery system with respect to the terrain, and the flight vector which is the direction and speed of the recovery system with respect to the local air in the recovery system. Typical autonomous GPS-guided recovery systems use GPS for the provision of the ground tracking vector. A compass on board supplies the flight vector direction, and the flight vector speed is provided by a Pitot tube or by estimating the forward course of the glider ratio and the current drop rate. With these two vectors, the local wind vector can be determined, since the ground monitoring vector is the sum of the winds acting in the recovery system (local wind vector) and the speed and direction in the local air of the recovery system. (flight vector).

This invention regarding steerable retrieval systems can be summarized as follows with reference to Figures 29 to 33. A GPS supplies the current position and the ground tracking vector of the retrieval system. The ground tracking vector is measured before the turn starts, so that it is measured on a flight without turning (Figure 29). In the present systems, a compass is used to determine the direction of the vector of

115/125 flight and the speed of the flight vector is calculated from the rate of descent and the glider ratio estimated from the recovery system or by the use of an air speed sensor (Figure 30). The measured flight vector is one of two components that add up to the formation of the tracking vector in. earth (Figure 31). The second component, the local wind vector, is determined by subtracting the measured flight vector from the ground tracking vector. In the present invention, the local wind vector is determined by the effective cancellation of the flight vector and by calculating the new ground-based vector for the period of time in which the flight vector is canceled. In order to cancel the flight vector, the recovery system is positioned in a constant rotation for a complete revolution. If no local wind is present (local vector equal to zero), the path of the recovery system with respect to the terrain is a circle (Figure 32). For the total turnaround time, the effective ground tracking vector is zero, since the recovery system ended at the same latitude and longitude position where it started. Since the ground tracking vector was measured to be zero during the turn, winds are calculated to be zero, since the ground tracking vector is equivalent to the sum of the local wind vector and the flight vector and the flight vector was canceled by turning in a circle for the turning period. If local winds are present, the path of the recovery system is a circle displaced by local winds. In the following example, the local wind vector is from the west (magnetic direction 90 degrees) (Figure 33). The route

116/125 of the recovery system during the full circle is pushed eastward by the local wind vector. The path of the recovery system (above) shows how the start and end positions of the circle are displaced by local winds. By measuring the start and end positions during the spin and by dividing the time it took to complete the full circle, the local wind vector is determined. Subtracting the local wind vector from the ground tracking vector taken on the level flight (before the start of the turn), the flight vector is determined. By the steering method of this invention, the payload of the steerable recovery system does not need to have a compass and an airspeed indicator, which are required in conventional systems for determining the flight vector.

A GPS is unable to provide the flight vector direction, because the GPS position and ground tracking vectors are relative to the Earth's surface and do not give information about the recovery system's flight through the air around it. . The flight direction of the recovery system is in reference to the local air. For example, if the recovery system faces west with an air speed of 64.4 km / h and the wind speed is 96.55 km / h in an easterly direction, the GPS will provide a ground tracking vector of east at 32.2 km / h, although the steerable system is actually facing west. That is why a compass is needed to provide the actual direction the recovery system is facing and not the direction the recovery system is moving with respect to the terrain. For the same reasons given above, the speed of the flight vector also

117/125 must be determined from sources other than GPS, since the speed of the flight vector is the air speed and not the ground tracking vector. Therefore, it is necessary to have an airspeed sensor in the recovery system or to estimate the speed of the flight vector in the glider ratio of the recovery system.

Since the ground monitoring vector is the sum of the local wind vector and the flight vector, if the flight vector can be removed or canceled, then the local wind vector becomes the current ground monitoring vector. . This invention cancels both the direction and speed of the recovery system through local air (the flight vector) by flying the recovery system in a full circle and by measuring the ground tracking vector at the interval. Since there is no compass on board the recovery system, a complete lap is determined by monitoring the direction of the ground tracking vector. When the vector matches the one recorded at the beginning of the spin, a complete loop is completed. For the period of time it takes to make the full circle, any component of the flight vector is removed as it is weighted to zero. Therefore, the only lateral force in the recovery system is the wind. By taking the change in position for the total time for the loop, the local wind vector is determined. The flight vector can then be determined by subtracting the local wind vector from ground monitoring in level flight. The calculations involved in determining the local wind vector (direction and speed), as well as the flight direction vector follow.

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Make the following measurements during the flight, in order to cancel the contributions of the flight vector:

Place the parachute or steerable glider at a constant rate of rotation. The speed of the turn is not critical, although the rate should be chosen in order to minimize the change in altitude during the complete turn. This minimizes the error due to changes in the wind vector with altitude. It is important that the turnover rate is as constant as possible.

Record the land vector, position and time.

Start ground vector direction (degrees) Start ground vector speed (m / s) Start latitude (decimal)

Start longitude (decimal)

Start time (GPS seconds)

Continue the turn until the land vector direction matches the one recorded at the beginning of the turn.

Record the current shore position and time. End latitude (decimal)

End longitude (decimal)

End time (GPS seconds)

Calculate the local wind vector and the flight vector using the method and formulas below.

To return to the original direction, exit the rotation and adjust the direction to maintain the initial direction of the ground accompaniment vector.

To continue to rotate to a new flight vector direction, continue the rotation for the number of seconds calculated below, before exiting the rotation.

Additional number of degrees of rotation desired *

119/125 (End_Time-Start_Time) / 360

Alternatively, the appropriate ground accompaniment vector direction can be calculated from the newly calculated local and flight wind vectors.

Taking the final measurements exactly when passing through the exact magnetic direction such as that of the beginning measurements allows the measurement period to be that of a complete lap. By flying the recovery system in a constant full circle, any component of the flight vector is removed from the ground tracking vector for the period from the start time to the end time. The only lateral force in the recovery system is the local wind. By taking a position for the total time to complete a complete lap, the local wind vector is determined.

The change in latitude and longitude during a complete lap due to local winds is calculated as follows:

Latitude_change (radians) = [Start_Latitude_ (decimal) End_latitude_ (decimal)] * pi / l80

Longitude_change (radians) = [Start_Longitude_ (decimal) End_longitude_ (decimal)] * pi / 180

Conversion of the change in latitude and longitude during a complete turn to the north and east components of local wind in meters per second requires that the non-spherical Earth model converts the change in latitude and longitude into actual distances and rates. The formulas can be summarized as follows:

Earth radius at latitude (Rn) = Ravg / (1 - Eccent * (sen (latitude_change_ (radians))^THE2) )

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Where Ravg is the average radius of the Earth = 6378137 meters and Eccent is the eccentricity of the Earth = 0.00669437999014138

Local_Winds_North_ (m / s) = Rn *

Latitude_change (radians) / (End_Time - Start_Time)

Local_Winds_East_ (m / s) = Rn * cos ((Start_Latitude_ (decimal) + End_Latitude_ (decimal) / 2) * pi / 180 * (Longitude_change_ (radians) / (End_Time

Start_Time)

Convert the local wind components into a vector (local wind vector).

Local_winds_direction (degrees)

ArcTAN (Local_winds_North_ (m / s) / Local_Winds_East_ (m / s))

If the local wind direction is negative, add 360 degrees.

Local_winds_speed_ (m / s) =

SQRT ((Local_winds_North_ (m / s))^THE2 + (Local_Winds_East_ (m / s)) ^THE2)

From the GPS ground tracking vector and the local wind vector, the flight vector can be determined. It is easier to subtract the local wind vector from the ground tracking vector when both vectors are converted to the north and east components first:

Convert the ground tracking vector to its northern and eastern components.

Ground_Track_North_ (m / s) cos (Start_Ground_Vector_Direction_ (degrees) * Pi / 180 * Start_ Ground_Vector_Speed_ (m / s)

Ground_Track_East_ (m / s) sen (Start_Ground_Vector_Direction_ (degrees)

Pi / 180 * Start

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Ground_Vector_Speed_ (m / s)

Subtract the local wind components from the ground monitoring components to arrive at the flight components.

Fligh_North_ (m / s) = Ground_Track_North_ (m / s)

Local_winds_North_ (m / s)

Fligh_East_ (m / s) = Ground_Track_East_ (m / s)

Local_winds_East_ (m / s)

Convert the flight components to a vector (the flight vector).

ArcTAN vector direction (Flight_North_ (m / s) / Flight_East

If the flight direction is negative (degrees) (m / s)), add

360 degrees.

Flight vector speed (m / s)

SQRT ((Flight_East_ (m / s)) ^THE2 + (Flight_East_ (m / s)) ^THE2)

Now, the flight vector and the local wind vector have been separated from the ground tracking vector and the direction control algorithms can use their components.

The software functions above can be implemented in the control system of an autonomous recovery system, such as a parachute or steerable glider, guided by autonomous GPS. A typical system consists of at least one parachute or steerable glider, one or more steering actuators, a GPS unit for position data, ground and time tracking, a processor for carrying out the algorithms described above, and a source of power for the processor and actuators. No airspeed sensor or compass is required.

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A steerable parachute includes direction control lines that are pulled or released to rotate the recovery system. A steering actuator such as a winch could rotate unidirectionally to pull the right-hand steering control line and rotate the other way to pull the left-hand steering control line. The processor controls the actuator to direct in any direction. 0 The processor receives the ground tracking vector, the position data, and the time from the GPS unit. The processor starts a full circle as described above, receives information from the GPS and applies the algorithms described above to the current flight and local wind electrode. The processor then controls the actuators appropriately to terminate or continue the spin based on its steering algorithm, in order to negotiate with the target landing position.

A single control line can also be used for parachute steering. This allows the parachute to rotate primarily in one direction (direction A). The parachute would either be rotating in the A direction or adjusted for a straight flight by the actuator under processor control (by maintaining a constant ground-tracking direction). The steerable parachute would be designed to have a natural inclination to turn slightly in direction A (direction B), when the direction line was completely loose. A slight adjustment (pull) on the control line would cause the parachute to fly straight, as indicated to the processor by a constant ground tracking direction. An additional pull on the control line would cause the parachute to rotate in the

123/125 according to ο different, occasionally local to and from recalculated wind direction A. This ability to align the parachute for a straight flight is generally necessary for the correction of individual differences in parachutes.

Due to the fact that local winds can change the recovery system down to winds, the flight vectors will need to be taken into account by the new local winds and the change in the flight vector due to changes in air density and other factors. There may be an additional error due to different winds between those at the start measurements and those at the end measurements. The full circle procedure described above should be performed as often as necessary for the desired accuracy of the flight vector. The biggest drawback of performing the full circle procedure more often is that the effective forward movement of the recovery system is not available while in the full circle procedure.

An example of the inventive method being used to determine the local and flight wind vectors without using a compass or an airspeed indicator is shown in Table 1.

Other changes and modifications of the invention in the same way will be evident to those of ordinary knowledge in the art, upon reading this exhibition, and it is intended that the scope of the invention shown here is limited only by the broadest interpretation of the appended claims, which inventors are legally authorized.

EXAMPLE OF DIRECTIONAL RECOVERY SYSTEM

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LEGEND Black on white values ​​are supplied by the GPS unit

Black on gray values ​​are calculated by the processor using formulas

Start ground vector direction (degrees) 61 Start ground vector speed (m / s) 12 Start latitude (decimal) 33.11

Start longitude (decimal) 111,858

Start time (GPS seconds) 908311

End latitude (decimal) 33.09

End longitude (decimal) 111.87

End time (GPS seconds) 908406

Number of additional degrees of turn desired 21 The change in latitude and longitude per second due to local winds:

Latitude_change (radians)

Longitude change (radians)

-0,0003491

-0,0002094

The conversion of winds from latitude and longitude to meters per second North and meters per second East requires the non-spherical model of Earth. The formulas can be summarized as follows:

Ravg 6378137 meters

Eccent

Earth radius at latitude (Rn)

Local_Winds_North_ (m / s)

Local Winds East (m / s)

0,00669438

6378137

23,44

4.23 meters

190,24

23,82

Calculate the local wind vector direction and speed from the north and east wind components.

Local_winds_direction (degrees)

Local_winds_speed_ (m / s)

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5,82

10,50

From the local wind vector and the GPS ground monitoring vector, the flight vector can be determined, as follows:

Convert the ground tracking vector to its north and east components.

Ground_Track_North_ (m / s)

Ground_Track_East_ (m / s)

Subtract the north and east local wind components from the north and east land tracking components to obtain the flight components. This is done because the ground tracking vector is the sum of the local wind vector and the flight vector.

Fligh_North_ (m / s)

Fligh_East_ (m / s)

Convert the north and east flight components into a vector.

29,25

14,73

<img file="BRPI0414906A_D0002.tif" />

Flight vector direction (degrees)

Flight vector speed (m / s)

To calculate a change in the initial magnetic direction

Continue to rotate to a new flight vector direction, continue to rotate the number of seconds calculated below, before exiting the rotation.

Continue to rotate at the same angle of lateral tilt for seconds

5,5

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