Communications system with suborbital platform carrying a communication device

[0001] This application claims priority to US patent provisional application, serial number 60 / 196,058, filed April 10, 2000, which is incorporated herein by reference. [0002] [Technical field to which the invention belongs] The present invention relates to a wireless communication system, and more particularly to a wireless communication system using an aircraft. [0003] [Background of invention] With the rapid development of the Internet and multimedia applications, the challenges of providing high bandwidth (bandwidth), last mile connectivity to end users are increasing. Communication signals can be sent to such users through various different types of communication systems. Wired terrestrial systems generally provide high-speed communication for wide-bandwidth (bandwidth) communication. However, facilities for such systems are expensive and time consuming to build, maintain and renew, and do not by themselves help mobile communications. Radio systems that use transmission towers provide reasonably high-speed communications due to the fairly limited bandwidth per service area. [0004] Geostationary orbit (GEO) satellites (approximately 36,000 kilometers above sea level) can also provide wireless communications to end users, but are used in densely populated areas due to their limitations in terms of bandwidth efficiency. ing. Medium Earth orbit and Low Earth orbit (MEO and LEO) satellites (10,000 km and 700-1500 km, respectively) are of a nature because end users are required to have equipment to track the relative motion of the satellite. It's complicated above. In addition, the GEO satellite must be in equatorial orbit, so its practical use is limited to the equatorial land region. Geostationary satellites also require complex continuous tuning, directional antennas, both in the air and on land, and with secondary systems that are generally adapted to switch communication signals from one passing satellite to the next. And. Of course, none of the above satellites can be easily recovered due to maintenance and other reasons. [0005] Aircraft are used in a variety of applications, including passenger transport, freight transport, firefighting, reconnaissance, and combat. Various aircraft have been designed to satisfy the many functional roles defined by these applications. These aircraft include conventional balloons, airships, fixed-wing aircraft, flying wings and helicopters. [0006] To satisfy that, one of the functional roles that aircraft have not previously been generally designed for is a long-range, secondary orbit (eg, stratosphere), high-altitude communication platform. .. A high altitude platform is an aircraft that stays at high altitude with a relatively fixed position. Aircraft that are lighter than air, such as balloons and airships, and helicopters both lack the ability to maintain selected stations under altitude limits and strong winds, thus limiting their functionality as high-altitude platforms. Aircraft that generally sail at high speeds, reach high altitudes, and maintain them are limited because they lack the ability to maintain a selection station in the absence of wind. In addition, helicopters, certain lighter aircraft and most aircraft are unable to maintain high altitude stations for more than a day, let alone a fairly long period of time, such as a week or more or a month. [0007] Many developmental aircraft have the potential to maintain continuous day and night flight as solar-powered aircraft as long as they are exposed to heavy sunlight during the day. Three such aircraft actually built, well known as Pathfinder, Centurion and Helios aircraft, set numerous flight records. The underlying basic design of these aircraft is discussed in detail in US Pat. No. 5,810,284 and aims at a non-backward flying wing with extremely high aspect ratios and relatively steady chords and wings. [0008] It has been proposed to use long-duration, high-altitude platforms, such as Pathfinder, Centurion, and Helios aircraft, which operate at altitudes in sub-orbits, for various functions. As an example, a high altitude platform equipped with a microwave communication device can provide a communication relay service between remote locations. Other types of aircraft are not most suitable for this role due to their heavy weight, high cost, and limited amount of fuel used rapidly. In general, these other types of aircraft cannot stay in the desired position for a considerable period of time, so their utility is limited in fulfilling these roles. [0009] [Problems to be Solved by the Invention] It is desirable to develop a communication system that provides high bandwidth (bandwidth) signals to both fixed position and mobile receivers. The various examples of the present invention can meet some or all of these needs and provide additional related advantages. [0010] [Means for solving problems] The present invention solves the above need by providing an aircraft-based communication system that is inexpensive to manufacture and can remain in the air for extended periods of time. These systems can be deployed rapidly, are flexible with respect to the market and market size, and can be maintained and updated using new technologies. These systems, which are wireless in nature, can be developed for use by portable and / or mobile users. [0011] The present invention inevitably uses a platform in sub-orbit that can be used to convert radio signals from ground stations into optical signals destined for satellites or other spacecraft above altitude in sub-orbit. Accompanied by the target. Similarly, aircraft can be combined with multiple ground stations to create broadband and / or wireless networks. However, the aircraft is not only much cheaper than producing satellite or earth last mile facilities, but it is also recoverable and can be used for the same or different roles. [0012] The present invention uses a station-strictly maintained stratospheric platform as a ground-immobilized communication hub for fixed-position users. This platform aerodynamically realizes station maintenance with electricity generated using a hybrid of solar energy and hydrogen fuel cells. They are environmentally friendly and do not generate pollutants in the stratosphere. The payload module maintains its position and uses a gimbal to separate it from the platform's roll-pitch-swing movement. The antennas of both the payload and the user terminal are designed to conform to platform station maintenance dynamics. [0013] The data can be processed through a ground-based gateway that broadcasts the data to the aircraft and receives the data from the aircraft. The platform is at an altitude of 20 KM. This is much closer than a geostationary satellite in orbit of 35,000 kilometers, so the delay latency it gives is equal to or better than the Earth network. [0014] Communication systems can use multiple spatially spaced aircraft with a variety of frequencies and polarizations, resulting in bandwidth efficiency of 222 MHZ / KM2 or higher for densely populated urban areas. Can bring. It can also allow competing systems to co-exist. [0015] Other features and advantages of the present invention will become apparent from the following detailed description of preferred embodiments taken up in the context of the accompanying drawings. Here, the principle of the present invention will be described with reference to an example. The detailed description of the particular preferred embodiments described below to enable the construction and use of the embodiments of the present invention is not intended to limit the claims listed and is a specific example of the claimed invention. It is intended to be useful as. [0016] BEST MODE FOR CARRYING OUT THE INVENTION The invention summarized above and defined by the enumeration claims will be better understood by reference to the following detailed description to be read in the context of the accompanying drawings. The following detailed description of specific preferred embodiments of a communication system described so that they can be constructed and used with respect to a particular embodiment of the present invention is not intended to limit the enumeration claims and is specific to them. It is intended to provide an example. [0017] [Suitable Aircraft for the Present Invention] The present invention preferably includes the use of aircraft with strict station maintenance requirements as a platform that is nearly immovable to the Earth. According to the present invention, suitable aircraft are of similar design to Pathfinder, Centurion and Helios aircraft, as described in the background of the invention. The design of a suitable aircraft is described below, with further details set forth in US Pat. No. 5,810,284 incorporated herein by reference. Nevertheless, it should be understood that another aircraft design for the present invention may differ significantly from the aircraft described. [0018] With reference to Figure 1-3, a preferred aircraft embodiment is a flying wing 10. That is, it has no fuselage or tail. Instead, it includes a non-retracting angle wing 12 with a blade shape and size that is nearly constant along the wingspan. It is preferred that 6, 8 or 14 motors 14 are located at various positions along the wingspan, with each motor driving a single propeller 16 to generate propulsion. It is preferable that two, four or five vertical blades 18a-18d, or pods, extend downward from the wing with a landing gear at the lower end. [0019] The preferred aircraft 10 is solar thermal power, includes a fuel cell, and stores energy for continuous day and night flight. This is therefore ideally suitable for missions of continuous unmanned flight over a week to 10 days (eg 200 hours) and more preferably over 3000 hours. Alternatively, some or all of that electricity can be fueled by hydrogen (such as liquid hydrogen used in either fuel cells or conventional motors), fossil fuels or other stored fuels, or solar energy during the day and non-renewable at night. Alternatively, it can be designed to be derived from a combination of fuel resources such as partially renewable storage fuel. [0020] Aircraft 10 is divided into 5 or 6 modular compartments, which are arranged longitudinally along the wingspan. These compartments range in length from 39 to 43 feet and have a chord length of approximately 8 feet. Thus, the aircraft is preferably about 8 feet long, preferably with wingspans of about 100, 120, 200 or 250 feet. Aircraft wing compartments support their own weight during flight to minimize inter-compartment load, thereby minimizing the required load-bearing structure. [0021] [0021] The blades (fins) 18a-18d extend downward from the wing 12 at the connection points between the compartments, and each blade is fitted with front and rear wheels 34, 36 of the landing gear. The blades are configured as pods for accommodating aircraft elements such as electronic circuits and / or various payloads. One of the pods, the "control pod," is used primarily to carry control electronic circuits for controlling motors and elevators, including autopilots implemented as software. In addition, the pod carries a sensor, including a global positioning system, as well as a communication device as described below. [0022] As a result of the above design, a preferred example of an aircraft is light weight (less than 1 pound per square foot of wing area), sailing at relatively slow aerial speeds (from 13 knots at low altitude to 100 knots at high altitude) and in the air. It requires a relatively small amount of power from the solar cell array. Performance on that station is such that it is virtually transparent to the rest of the communication system (ie, the rest of the communication system is unaffected by the flight of the aircraft as long as the aircraft maintains the station). is there. [0023] [Ground link system] 4A and 4B show the system concept of the first system in which the communication system of the present invention is implemented. The system includes one or more aircraft 10 acting as a strictly station-maintained stratospheric platform used as a hub, and communications equipment located both on and on the platform. [0024] Ground-based communications equipment includes one or more "gateways" 102 (ie, terrestrial communication hubs that broadcast and / or receive signals to one or more aircraft platforms). Ground-based communication devices also include one or more end-user terminals (ie, communication devices for one or more end users), each having a terminal antenna 104 at one or more end-user positions 106. Including. Each terminal antenna can broadcast and / or receive signals to one of the aircraft platforms. Multiple terminal antennas can be used to access signals from different aircraft for a single user, thus increasing bandwidth. [0025] Data communicated to or from the end user 106 at the user terminal is transmitted between the gateway 102 and the end user's user terminal via an aerial communication device. More specifically, end-user data is suitably processed and transmitted between one or more gate weights and one or more aircraft 10. [0026] Aircraft 10 remains nearly immobile with respect to the non-moving gateway 102 and end-user position 106. More specifically, these aircraft platforms are kept within the beamwidth of the terminal antenna 104. It is preferred that each platform maintain a position at an altitude of 20 KM above the selected communication area or cell. It is best to stay inside a vertical altitude of ± 30 meters with a turning radius of 600m over all environmental conditions. Compared to GEO satellites, this communication system will have a latency comparable to or slightly better than that of a terrestrial network. [0027] The aerial communication device is carried in one or more payload modules on the aircraft 10, preferably in pods 18 (see Figure 1-3). The device maintains its position and uses a gimbal to separate the platform from rolling, pitching, and swinging motions. Both the aerial communication device (payload) and the end-user terminal antenna are designed to conform to the station maintenance dynamics of the aircraft-platform. [0028] The aerial communication device is configured to aim at a plurality of different cells 110 of the user terminal antenna. These cells, which are preferably hexagonal, can be of various sizes that are well balanced with the bandwidth of the aerial communication device at an appropriate distance from the aircraft. [0029] An additional aircraft 10 with a similarly configured communication device is provided with additional bandwidth (bandwidth) for cell 110 and / or for additional cells serviced by the first aircraft. To do so. Each aircraft must be distanced from the other side so that it does not fly within the beamwidth range of each other's ground antennas. This spatial diversity also helps protect the aircraft from collisions with each other. [0030] The system uses spatial diversity (from various densely packed, two-dimensional platform positions, see Figure 4C), frequency diversity, and polarization diversity to a bandwidth as high as 222MHZ / KM2 ( Bandwidth) Density efficiency can be brought to densely populated urban areas. The tightly packed spatial diversity provides a much higher bandwidth than the one-dimensional system of orbital frames for GEO satellites. This spatial diversity also allows competing systems to coexist. [0031] The gateway uses 92-95GHz for the uplink to the platform and 81-84GHz for the downlink from the platform. The frequency band is the polarized light reused for each gateway. It is preferable that up to four spatially separated gateways with auto-tracking antennas process all the data from each platform. An overall reuse factor of 8 yields 24GHz bandwidth processing power per platform. Gateways process user data and route it either externally through the Earth and / or satellite networks (networks) or internally on platforms for destination users within range. Gateway communication links to aircraft are preferably cross-polarized offset to maintain link performance even in the worst case of rain. [0032] The communication payload on the platform is a simple repeater design for connecting the user to the gateway. The gateway antenna automatically tracks each other with the ground antenna. To obtain bandwidth density on the user link, multiple beams are placed in a conventional 4-cell reuse configuration. Cell size and terminal-to-terminal synchronous CDMA waveform design overcome the interference caused by platform motion in the worst case. [0033] End-user communication links (from aircraft to user terminals) can be designed for the Ka or Ku band. Figure 4D shows the design in which the GEO satellite Ka band is reversed, i.e. 19.7-20.2GHz is used for the uplink from the end user and 29.5-30.0GHz is used for the downlink to the end user. Divide the available 500MHZ bandwidth (bandwidth) into two 250MHZ in a 4-cell reuse plan. Using the entire 24GHz gateway bandwidth, the payload supports 96 user beams. It achieves a bandwidth density of 6MHZ / KM2 when the destination cell size is an 8KM hexagon. [0034] The user's terminal antenna must have sufficient beamwidth to adapt to the platform's station maintenance operation. At the same time, they must be narrow enough to allow multiple platforms to operate on the same coverage and to further increase bandwidth density as demand increases. To get closer to the link for legitimate E1 (2,048MBPS) data speeds, corresponding to the payload in Figure 4D, an antenna with a diameter of 30 cm is used for the cells directly under the platform, while 45 cm for the cells at the edge of the communication range. You will need an antenna. The sidelobe levels of these antennas in the Ka band allow hexagonal close-packed construction of 37 platforms with minimal mutual interference, as shown in Figure 6. This increases the bandwidth density in the overlapping regions to 222MHZ / KM2. Interference between GEO Ka band terminals and this system can be greatly mitigated using spatial separation. [0035] It is preferable that one or more operating centers 100 command and control the aircraft platform in flight (see Figure 4B). They also command additional aircraft platforms that can be used in place to ensure overall system availability with 99.9% reliability and to maintain the system while individual aircraft are maintained. And control. The operational center is preferably controlled by a fleet of aircraft platforms that can be simultaneously maintained in the appropriate stations for the area below. After the first aircraft has been replaced by the second, it is preferable that the second aircraft be able to head to a remote landing site to avoid harsh weather. Due to the division structure of the aircraft and the size of the division, the aircraft can be disassembled here and transported to the runway near the communication cell using ordinary trucks. [0036] The system can be completely resized and optimized in many ways when placed in various markets. The payload is preferably designed in 6 GHz processing power increments for a single gateway. The antenna beam is selectively distributed to cover the required cell 110. [0037] The payload (ie, aerial communication device) is updated and reconfigured when the platform is reclaimed for maintenance. The platform can be optimized to maintain the station more precisely with a small payload. On the other hand, in order to increase the bandwidth (bandwidth) density, the cell size may be reduced. Similarly, the total capacity of the system can also be maintained using multiple platforms covering the communication area. [0038] [Satellite downlink system] FIG. 5 shows the concept of a second communication system that implements the present invention. The aircraft 10 is used to set up a high-bandwidth (bandwidth) surface-to-air communication system for ground stations from spacecraft located above satellite orbit altitude, such as satellites. More specifically, the aircraft is particularly well adapted to work as part of a satellite downlink system that includes satellite 302, ground station 300, and communication devices that support signals moving between them. This type of system can be useful in the construction of a wide variety of communication systems. [0039] Generally, for communication between a ground station and a satellite, a certain type of radio signal such as a microwave signal capable of passing through various atmospheric phenomena such as clouds without interference is used. Some of these signals are multidirectional and some are directed at a given beamwidth to the target. However, due to the receiver sensitivity and the given level of background noise, the signal strength required to carry a particular bandwidth (bandwidth) is when the broadcast antenna has a relatively narrow beam width. Even if there is, it increases significantly with the distance between the ground station and the satellite. The receiver sensitivity can be increased by increasing the antenna size, but in a satellite system, it is expensive if it is heavy, so there is a trade-off with the antenna weight. [0040] In addition, with the limited exception of geostationary satellites, satellites reciprocate and follow a ground trajectory across the equator, which causes distance and direction fluctuations from ground stations to directional antennas (satellite-to-satellite). Requires large directional adjustment (such as regular switching to). Due to the ground trajectory of a satellite (or group of satellites), a ground station requires a huge amount of power to maintain a downlink with a long-range satellite. [0041] Therefore, signal strength is generally a limiting factor for the bandwidth available for downlinks, and for directional ground stations, generally directional antennas must have target tracking capability. It doesn't become. In addition, to the extent that the signal strength can be increased, the increase increases the geographic area that receives significant interference from the signal. This is especially noticeable when the signal has a wide beamwidth or is multidirectional (as used for cellular communications). In summary, the communication bandwidth (bandwidth) is the satellite altitude on the ground station, the maximum ground distance between the ground station and the satellite (ie, the latitude and longitude frequency difference), the receiver sensitivity (from antenna size, etc.). , Beam width, and power level. In addition, in at least some applications, the communication bandwidth is limited by background noise and limits on permissible interference with signals at other locations. In addition, the use of narrow-beam width ground station antennas to reduce power requirements imposes significant costs and may pose an extra risk of failure due to the accuracy of tracking requirements. [0042] Satellite-to-satellite communication signals, or satellite-to-non-orbital spacecraft uplink links, can achieve wide bandwidth over long distances with limited power using high frequency signals such as lasers and other optical signals. Therefore, they are not always bound by these types. These signals can deteriorate rapidly as they pass through atmospheric phenomena such as clouds. Therefore, such high frequency communication signals are generally limited to intersatellite communication or communication between satellites and ground locations that are unlikely to face atmospheric phenomena such as clouds. [0043] In a preferred embodiment of the present invention, a radio signal from a ground station 300 such as a microwave signal is transformed into an optical signal directed to a satellite or another spacecraft. It can give a significant increase in communication bandwidth (bandwidth). The communication link can be directed in any direction, but the communication link is preferably bidirectional. [0044] Because of this function, a suitable platform on the secondary orbit, the aircraft 10 of the present invention, is a microwave transmitter / receiver 310 with a downward directional antenna that communicates with a microwave transmitter / receiver 312 with an upward directional antenna on the ground station. , And an optical transmitter / receiver 314 with an upward directional antenna that communicates with an optical transmitter / receiver 316 with a downward directional antenna on the satellite. Aircraft are preferably elevated above general altitudes due to significant atmospheric light interference such as cloud 318 and other atmospheric humidity, maximizing the signal bandwidth between the ground station and the aircraft. It is preferably low enough to make it. The aircraft preferably has a plurality of antennas for the ground station, each preferably capable of aiming at the ground. [0045] Aircraft are most preferably operated between altitudes of 50,000 feet and 70,000 feet for at least 200 hours (and preferably at least 300 hours). Communication systems built using this aircraft work at ground station microwave power levels that interfere with wide-ranging communications (ie, wide bandwidth communications) beyond the distance between the ground and low earth orbit altitudes. Is preferable. [0046] The aircraft is preferably kept relatively stationary with respect to the ground to limit or eliminate the need for the ground station to track the aircraft. More specifically, the aircraft is preferably a circle with a diameter of 7,000 feet and operates over an altitude range of 1000 feet, and even more preferably within or near a circle approximately 4000 feet in diameter. In addition, aircraft preferably operate within or near a vertical range of 1000 feet, more preferably within or near a vertical range of 100 feet. [0047] Since the radio signal 306 from the ground station 300 is relayed to the satellite 302 using the optical signal 308, the aircraft acting as a platform in the sub-orbit offers many advantages and can carry out various missions. For example, such an aircraft can be replaced quickly in the event of a mechanical failure. Similarly, such aircraft can operate within relatively close distances to each other, using frequencies that may interfere with each other at high power levels (due to wide bandwidth (bandwidth) or bidirectional signals). You can. This is because the radio signal for each aircraft has a power level that is significantly lower than the power level required to provide a similar bandwidth to the satellites in orbit. It can further discuss closed-loop signal strength control systems for minimizing power usage to the required level for various signals. [0048] Power usage can be further reduced by using upward-pointing terrestrial antennas and / or downward-pointing satellite antennas with localized beamwidths. Each of these aimable antennas defines the boundaries of the airspace in which the aircraft must stay. When using both upward-pointing ground antennas and downward-pointing satellite antennas, aiming must be made to separate the range of airspace in which the aircraft can maintain a station-maintained flight pattern from each other. [0049] The aircraft is preferably a low speed aircraft in order to maintain the station in a well-bounded airspace. The flight pattern is generally a nearly circular tablet with a certain amount of permissible vertical variation. However, it should be understood that under strong wind conditions, an airplane may change its preferred flight pattern from a zigzag pattern that generally changes its course back and forth in the upwind direction to a straight upwind flight. is there. [0050] Aircraft work to facilitate communication between a single ground station and a single spacecraft, such as Earth stationary (or other Earth-synchronized) satellites, or, as shown in Figure 5, aircraft optical communications. It can communicate with a series of low earth orbit satellites that pass through the range of. Aircraft designed to switch between satellites preferably include two optical communication devices 314, 320 to capture the communication link with the second satellite 322 before breaking the communication link with the first satellite 302. .. [0051] As shown in FIG. 6, in another embodiment embodying the present invention, the aircraft 10 is mounted northward or southward, where constant and direct access to a communications satellite cannot be easily obtained by another method. Can be used at latitude. By keeping the aircraft at an altitude in the appropriate sub-orbit (preferably in the stratosphere), the aircraft establishes communication with satellite 324, which will be closer to the equator at latitudes more than 80 degrees. Can be done. [0052] In a related perspective, aircraft can take advantage of most non-equatorial stations by using directional signals that reuse wavelengths directed at equatorial satellites. More specifically, a particular ground station can broadcast two different signals using the same wavelength, one to the geostationary satellite and the other to the aircraft. Unlike non-equatorial satellites, aircraft do not have to cross the equator, so ground stations do not have to switch to new broadcast directions on a regular basis (as it happens when ground stations have to switch satellites). As a corollary, for a given aircraft position, some ground stations cannot broadcast on the same frequency as they broadcast to satellites. This is because the two directional signals overlap. For example, if the aircraft is slightly north of the equator and the ground station is far north of the equator, the signals will overlap. However, because of the ground station far from the equator, it would be possible to keep the aircraft far below the satellite on the equator. This aspect of the invention relates to a first embodiment of the invention in which a deployed ground station increases bandwidth by broadcasting to two spatially separated aircraft. Should be noted. [0053] As depicted in FIG. 7, one embodiment of a communication system can be used to bypass mountain 325 and other obstacles. This feature can be used to connect a ground station to a satellite and similarly to a ground station. This is a particularly effective use of this system, as neither ground stations nor satellites are generally relocatable without enormous effort and / or cost. One of the applications that may be effective for such systems is to overcome the effects of obstacles on widely broadcast signals such as television signals. The source of these television signals may be a ground station, satellite or even another aircraft. Another application that may be effective is frequency reuse in broadcasting to a large number of geographically separated ground stations that use the same frequency. This is advantageous in that the satellites are so far apart that they require a narrow beamwidth to communicate separately with two ground stations that use the same frequency. [0054] Another embodiment of the invention is used to act as a regional hub that relays communication between an end user placed in a spot beam and a communication network (line network). The communication network (line network) may be earth-based, which is accessed via a terrestrial antenna, or space-based, which is accessed via an optical or ultra-high frequency microwave link. [0055] One such relay system depicted in FIG. 8 uses aircraft 10 as a communication hub for simultaneous communication between ground station 326 and multiple satellites 328. In this mission, the aircraft will require a large number of optical transmitters and receivers and will need to generate additional power to operate the transmitters and receivers. As an alternative, two coverage areas with one aircraft with coverage coverage are shown, as depicted in Figures 9 and 10. More specifically, one or more such aircraft 10 can all communicate with a single satellite 330, allowing one or more ground stations to connect to a single satellite acting as a communication hub. This provides frequency reuse by each aircraft (ie, the same set of available frequencies can be used by each aircraft) and the bandwidth available between the satellite and the ground (ie). Bandwidth) may be increased. [0056] This scenario can increase the bandwidth given between a densely populated area and a satellite (see Figure 10) or between a satellite and two distant locations (see Figure 9). The former scenario provides a very large amount of data transfer between satellites and cities. It provides different routes for reusing low frequencies near the ground and for reusing optical or ultra-high frequency microwave links for communication between aircraft and satellites. This satellite then acts as a hub, communicating with one or more satellites 334, which can also use platforms in sub-orbit for terrestrial communications. In addition, aircraft-to-aircraft direct communication can also be used. As these examples show, aircraft can serve as part of various communication system structures. [0057] Although microwaves and optical signals were used in the preferred embodiments described above, it should be understood that this system can work with a variety of different signals. More specifically, air humidity may significantly interfere with radio wavelengths below about 1 mm (ie, high frequency signals above 20 GHz), but not so much over long wavelengths (ie, low frequency signals below 20 GHz). Are known. Therefore, the system can work well with ground station-to-aircraft radio signals with wavelengths greater than 1 millimeter and aircraft-to-satellite radio waves with wavelengths less than 1 millimeter. In addition, the aircraft of the invention described above may be used for signal redirection and / or amplification to allow the aircraft-to-satellite portion of the system to transmit signals that pass through atmospheric disturbances, such as the same signals used in the ground station-to-aircraft portion of the system. Power can be saved even when it is used and operated. [0058] [0058] [Wide area placement system] Referring to FIG. 11A, the communication system according to the first embodiment of the present invention is part of a wireless local loop, broadband and / or other communication network (line network). [0059] Various forms of communication, such as mobile and residential voice telephones, mobile and residential Internet access, and broadband data access, have different transmission requirements. For example, voice phones require relatively low levels of bandwidth (bandwidth) (4 to 64 KBps, etc.) for long periods of time (2 to 30 minutes, etc.), and Internet access requires large bandwidth (bandwidth) (64 to 64 KBps, etc.). It requires a very limited amount of time (such as 2000KBps) and broadband access is based on a large bandwidth (bandwidth) (such as 1Mbit or more) on an almost continuous basis. [0060] In order to give such communication requirements, various types of network structures have been generally developed, and various types of networks (line networks) have been derived. Among them are land-based telephone networks (line networks), cellular networks (line networks), wireless local loops, and various stratospheric satellite base networks (line networks). [0061] In general, different devices are required to support each of these technologies. However, in some cases, such a network (line network) can perform one or more functions. For example, broadband technology can be brought to fixed-position end users by using ASDL (Asymmetric Digital Subscriber Line) technology, which is passed over terrestrial lines. Nevertheless, most of these different forms of networks (networks) generally require huge and expensive line facilities to interconnect with any user or cellular tower. [0062] When satellites are used for networks, it is generally difficult to provide multiple access to users in high density areas. Developing equipment that meets the stringent weight and power requirements for use in satellites is expensive. Furthermore, it is difficult to maintain operation because the frequency reuse and surplus power margin required for transmission to a location inferior to the ideal and where the mobile user can choose to go are limited. In addition, a significant band of frequencies cannot be used because it cannot penetrate atmospheric humidity or other disturbances. [0063] Cellular and PCS systems are superior in invading buildings and hard-to-reach areas through the use of excess power and significant frequency reuse. However, these systems require considerable broadband connectivity between the base station and / or the transmission tower. [0064] For the reasons mentioned above, it is difficult for telecommunications companies to deploy for the first time in areas where there are no existing facilities or where there are private facilities that cannot be used for use. The present invention provides an innovative network structure that addresses one or more of these concerns in various embodiments. [0065] As can be seen in FIG. 11A, this embodiment of the invention is preferably an aircraft (solar heat or conventional, manned or unmanned) because it provides wideband one-point to multipoint connectivity between fixed ground positions. ) Includes the use of one or more high altitude platforms. An alternative is to use near-earth orbit (NEO) satellites. This high altitude platform is preferably an aircraft that orbits or maintains position with respect to the ground above or near one station, as described above. [0066] The aircraft acts as a platform base station in sub-orbit and is generally in a fixed ground position for and between various ground stations 500, which may include the roofs of the subscriber's commercial building 502 and the subscriber's residential building 504. In addition, preferably, the wideband communication signal is maintained. At least some of the ground stations preferably configure their data or voice channels as base stations that pay out to one or more remote subscriber stations, generally local fixed or mobile users. .. Ground base stations can be incorporated into or mounted on street lights 506, signboards, independent towers 508 or other structures in addition to buildings. Subscriber base stations (both commercial and residential) are also preferably networked to the access ports of nearby subscribers via wired or wireless connections. Connection to other networks (line networks) such as PSTN (Public Switched Telephone Network), PLMN (Public Land Mobile Line Network) or the Internet is another ground station 510, satellite network (line network) 512, or subscriber base station. If an access link to such a network (line network) can be used, it can be provided by access through an existing subscriber base station. [0067] As depicted in FIG. 11B, a subscriber ground base station 500 is typically configured with an antenna 520 to maintain wideband or radio loop connectivity with the aircraft. Optionally, a solar array 522 can be used to minimize the power drawn by the subscriber base station through the power connection 524. Various forms of ground base stations can be configured to serve individual or multiple subscribers. Wireless local, though you can use a wired network to reach a fixed location to work for another subscriber, whether mobile or fixed within the local area of the ground base station. It is preferable to use a loop. To communicate with another remote subscriber, the subscriber base station preferably has an antenna 526 suitable for the radio standard chosen by the relevant remote subscriber station. As an example, a remote subscriber station may be a cordless telephone owned by a subscriber base station, its associated subscribers, and a subscriber unrelated to the residential building. [0068] Various communication standards, including wireless local loops, can be used to connect subscriber base stations (or other ground base stations) to subscribers with remote subscriber stations. Compatible wireless communication standards include AMPS (Latest Mobile Phone Service), TACS (All Access Communication System), NMT (Scandinavian Mobile Phone System), IS-95 (Code Split Multiple Access US Digital Cellular Standard), IS- 54 / IS-136 (US Cellular Standard, also called D-AMPS), B-CDMA (Broadband Code Split Multiple Access), W-CDMA (Wideband Code Split Multiple Access), UMTS (Universal Mobile Telecommunications Service) or Others 3G, PHS (Simplified Mobile Phone), DECT (Digital Enhanced Cordless Telecommunications), PACS (Latest Personal Communication System), PDC (Personal Digital Cellular), CDPD (Cellular Digital Packet Data), Mobitex (Ericsson for Wireless Packet Network) Standard) and RD-LAP (Motorola Developed Wireless Packet Network). Therefore, various services including voice telephone, e-mail, Internet access, facsimile, video telephone, and video conferencing can be transmitted to these subscribers. [0069] As depicted in Figure 11C, the subscriber remote station 530 would preferably include an antenna 532 that conforms to the radio standards used by the associated ground base station of the subscriber remote station. These subscriber remote stations will have a wired or wireless network connection 534 to the subscriber's individual device. [0070] As can be seen from the above description of this distribution system, this aspect of the invention provides an information distribution system without the installation of expensive facilities. Instead, the system provides communication to and between individual subscriber base stations located with the subscriber or other ground stations, and ground stations, preferably at high altitude, on a secondary orbit. Requires only one or more platforms. [0071] Further supporting the examples described above, some preferred parameters include: [0072] -Aircraft operate in the 60,000-70,000 ft region, where maximum strong winds are much slower than low jet stream regions, above normal routes and stormy weather. [0073] -Aircraft are powered by any suitable means, such as solar thermal power, storage batteries, or fuel cells, fuel cells, internal combustion engines, or fuel that is burned to generate mechanical power through a turbine. [0074] -Aircraft are capable of meeting both relatively low speed flight, long lasting flight and maneuverability requirements for strict station maintenance. [0075] -Multiple antennas on an aerial stable platform (stable in direction and orientation) send and receive signals from patterns in the ground region. The beam has a moderate width, such as 10 ° -20 °. [0076] -More ground antennas for transmission and reception use narrow beams such as 2 ° -4 °. [0077] -The terrestrial antenna beams are fixed in direction and elevation so that they all point to the center of the station-maintained flight trajectory volume. The station maintenance aircraft stays in the beam. [0078] -An additional beam can be sent between the aircraft and the central ground control station via a fixed terrestrial antenna. [0079] -The directivity of the aerial and terrestrial antenna systems allows frequency reuse to provide broadband services to many customers. [0080] [0080] Although the specific forms of the invention have been illustrated and described, it will be clear that various modifications can be made without departing from the spirit and scope of the invention. For example, the features of the various embodiments described may be combined to create another embodiment of the present invention. Thus, although the invention has been described in detail with reference only to preferred embodiments, one of ordinary skill in the art will appreciate that various modifications can be made without leaving the invention. Therefore, the present invention is not intended to be limited by the above description and is defined in the context of the following claims. [Simple explanation of drawings] FIG. 1 is a three-dimensional view of a preferred embodiment of an aircraft embodying the present invention in a zero stress posture. FIG. 2 is a plan view of the aircraft described in FIG. FIG. 3 is a perspective view of the aircraft described in FIG. 1 at a fixed position typical of loading under flight conditions. FIG. 4A is an explanatory diagram of an aircraft described in FIG. 1 that acts as a high altitude platform in a communication system and passes signals between ground station signals and multiple end users. FIG. 4B is a conceptual diagram of multiple aircraft, such as those depicted in Figure 1, that act as high-altitude platforms in communication systems and pass signals between multiple ground stations and multiple end users in multiple cells. Is. FIG. 4C is a conceptual diagram of a two-dimensional spatial distribution of bondage stations that can be maintained by an aircraft under the concept depicted in Figure 4B. FIG. 4D illustrates an aircraft communication payload design concept that uses the GEO satellite Ka band in reverse. FIG. 5 is an explanatory diagram of an aircraft drawn in FIG. 1, which acts as a high-altitude platform in a communication system and transfers signals between a plurality of ground stations using radio waves and satellites using optical signals. Figure 5 also shows the transfer of communications from one satellite to a second satellite. FIG. 6 is an explanatory diagram of a communication system similar to that of FIG. 5 when the satellite is at a latitude significantly different from that of the ground station. FIG. 7 is an explanatory diagram of a communication system similar to that of FIG. 5 when an aircraft communicates with a large number of ground stations and satellites are shielded from one or more ground stations by mountains. FIG. 8 is an explanatory diagram of a communication system similar to that of FIG. 5 when an aircraft communicates with three different satellites at the same time. FIG. 9 is an explanatory diagram of a communication system similar to that of FIG. 5 when a satellite communicates with two aircraft and one ground station at the same time. FIG. 10 is an explanatory diagram of a communication system similar to that of FIG. 5 when a large number of aircraft, each of which acts as a base station for communicating with a plurality of ground stations, communicates with one satellite. FIG. 11A is an explanatory diagram of an aircraft depicted in FIG. 1 that acts as a platform base station on a high degree sub-orbit in a wideband, wireless local loop, or other communication system with a subscriber base station and a subscriber remote station. Is. FIG. 11B is a diagram of a subscriber base station for use with the communication system shown in FIG. 17A. FIG. 11C is a diagram of a subscriber remote station for use with the communication system shown in FIG. 17A.