Satellite broadcast system

Satellite broadcasting system

This application is a divisional application of the patent application with the application number 00102412.4, the filing date being February 23, 2000, and the invention titled "communication system, communication receiving device and communication terminal in the system".

Technical field

The present invention relates to a communication system, a communication transmitting and receiving device, and a communication terminal in the system, and particularly relates to a communication system suitable for artificial satellites, artificial satellite orbits and satellite orbit construction algorithms. The satellite orbit structure algorithm can be used for satellite communication and satellite broadcasting. , Satellite mobile communications and other communications and broadcasting fields, and can also be used to observe celestial bodies orbiting artificial satellites and other fields. This particularly involved communication system is also applicable to communication and broadcasting systems using artificial satellites, satellite communication transmitting and receiving devices, and communication terminals in the system.

(a) The prior art for setting the orbital parameters of artificial satellites (argument of perigee) is affected by the unevenness of the earths gravitational field, the gravitational force of the moon and the sun, and atmospheric resistance and sunlight when the artificial satellite orbits the earth as the center. Under the influence of pressure, the orbit of the artificial satellite is always changing. According to this point of view, the orbit of an artificial satellite running around the earth cannot be a circular orbit, but an elliptical orbit with an eccentricity in a broad sense.

Therefore, the "elliptical orbit here is defined as an "orbit with an eccentricity greater than 0 and less than 1. In order to achieve the desired purpose, in the process of setting the orbit parameters of the artificial satellite into the orbit, the eccentricity is not intended to be 0. "The Molniya satellite (with an orbital period of about 12 hours) used by Russia in the former Soviet Union is an example of an elliptical orbit satellite in practical use. Europe is proposing an artificial satellite with an elliptical orbit called Archimedes (with an orbital period of about 8 hours). In addition, a frigid orbit with an orbital period of about 24 hours is also proposed, but has not yet been put into practical use. A common view of these satellites is that all these satellites have an orbital inclination of about 63.4°.

Generally, due to the unevenness of the earth's gravitational field (the flatness of the shape of the earth), the perigee of the orbit of the artificial satellite will rotate on the orbital plane. However, using the mathematical mode to set the orbital inclination to 63.4°, calculate the time rate of change of the argument of perigee, and the product term is 0, making the time rate of change 0. Therefore, it can be considered that the rotation has stopped.

(b) The prior art on the method of the orbit structure of multiple artificial satellites. The communication system using multiple artificial satellites operating in inclined orbits has been practically applied and researched. Although several artificial satellites such as the Molniya satellite and the Archimedes satellite have been mentioned earlier, the detailed method of arranging the orbits is not described.

In recent years, although a communication system using multiple artificial satellites has been established, the detailed technology on the orbital structure method has not yet been disclosed. Therefore, detailed technology of the track structure is required.

On the other hand, Japanese Patent Application Publication No. 11-34996 proposes a method for controlling the orbit of an artificial satellite staying in the zenith direction for a long time in orbit, and a communication system and method using artificial satellite.

(c) With regard to the existing technology of mobile communication and broadcasting of moving objects. In the past, if you wanted to receive TV broadcasts on moving objects such as vehicles, there were problems: the image in areas far away from the broadcasting equipment of the TV station was poor, even if The screen of the area near the broadcasting equipment of the TV station also flickered, and the receivable channels differed due to movement. It is difficult to watch TV comfortably when receiving TV broadcasts from communication and broadcasting satellites on fixed orbits in mobile objects, because electromagnetic waves are frequently shielded by man-made buildings such as tall buildings, trees, and natural geographical features.

To transmit a large amount of data such as images from mobile objects such as ambulances, the existing ground communication infrastructure and communication satellites cannot be completed.

In order to solve the above-mentioned problems, the Japanese Patent Application Publication No. 11-34996 proposes a method for setting the orbital parameters of an artificial satellite that transmits a large amount of data to a moving object such as a vehicle. In addition, it also proposes the orbital parameter of the artificial satellite.

Corresponding to the above three items (a), (b) and (c), according to examples in the field, the problems of the prior art will be described as follows.

(a) Regarding the problem of setting the orbit parameter (perigee argument distance) of the artificial satellite, and the object of the present invention, in the above-mentioned Molniya satellite, Archimedes satellite, and Tundra orbits, the orbital inclination angles are all fixed at about 63.4°. The main purpose seems to be to eliminate the spin at the perigee on the orbital plane. On the other hand, because the above-mentioned artificial satellites are used in high latitude regions such as Europe and Russia, it is advantageous to use an orbital inclination of about 63.4°.

As for the geographical location of Japan, its territory extends from mid-latitude to low-latitude, with the northernmost island of Chotoru at approximately 45° north latitude, and the southernmost island of Okinotori at approximately 20° north latitude. Therefore, when the 63.4° orbital inclination is used as described above, unless the orbital height is high enough, the artificial satellite system is difficult to use in Japanese territory. Therefore, when considering the artificial satellite orbit commensurate with the Japanese territorial position, the orbital inclination has to be a value other than about 63.4°, so the value of the perigee of the orbital spin is also the same.

In order to control the rotation of the perigee, it is necessary to install a thruster to control the rotation on the artificial satellite. The analysis and simulation are performed when the orbital inclination is 40°. For example, the eccentricity of the orbit parameter proposed by the Japanese Patent Application Publication No. 11-34996 is 0.24. It turns out that many thrusters that control the argument of perigee are in a dominant position among the thrusters that all rely on setting orbital parameter conditions. This is because in this case, about 75% of the orbital control thrusters must be used to the maximum. The position argument is controlled to be close to 270°. Therefore, it is possible to reduce the devices installed on the artificial satellite, otherwise the in-orbit life of the artificial satellite will be shortened.

Summary of the invention

In order to solve the above-mentioned problems, the purpose of the present invention is to set the argument of perigee, which is one of the six orbital parameters of the orbit of the artificial satellite.

(b) Regarding the problem of the orbit construction method of multiple artificial satellites and the object of the present invention, many communication systems as described above adopt an elliptical orbit with an argument of perigee of about 270° and an orbit period of about 8 hours. The apogee of these systems appears in Europe, North America and Japan, and their purpose is to provide communication services with 3 or 6 artificial satellites. It can be inferred that the number of 3 or 6 satellites is intuitively and naturally determined, so that the 3 artificial satellites are located above the three regions at all times. They do not describe the use of different numbers of artificial satellites. In addition, as for the method of setting the orbital parameters, most of them do not describe specific values except for the 20,270km semi-major axis that is mathematically calculated from the 8-hour orbital period and the 63.4° orbital inclination that is considered stable by orbital dynamics. There is also no description of the method of obtaining the value.

When surveying the orbit of an artificial satellite on the ground, there are only four orbital parameters that can be represented geometrically and visually, namely, the semi-major axis or period of the orbit, the eccentricity, the inclination of the orbit, and the argument of perigee. Therefore, in the preliminary conceptual design period, it is sufficient to set these 4 parameters. This is considered to be one of the reasons why the orbital parameters are not clearly described and the calculation method is not given.

The Japanese Patent Application Publication No. 11-34996 proposes a method for setting the orbital parameters of an artificial satellite whose orbital period is about 12 hours or 24 hours. In addition, the satellite orbit parameter values are described, and the number of satellites required when Japan is the service target area and is greater than 70°. However, the values of orbital parameters and the number of satellites other than the above-mentioned orbit period are not proposed. The previous description is the setting method of the orbit parameters of the artificial satellite that stays in the zenith direction of the designated area for a long time in an elliptical orbit, and this method cannot be used for setting the orbit parameters of the artificial satellite in all cases.

In addition, the following will describe a system using a number of artificial satellites that are being planned or developed. In the mobile communication satellite system, the service object is the whole world, and the satellite runs on a circular orbit (with an eccentricity of 0) with a constant semi-major axis and orbital inclination, but other orbital parameters and their calculation methods are not disclosed. The reason may be that they believe that this skill belongs to the inventor who proposed the system using artificial satellites. In order to measure the entire earth, the geodetic satellite system developed is a consortium of satellites operating in subtropical sun-synchronous orbits. On the other hand, in the case of centralized and continuous satellite services or surveillance of designated areas, geostationary satellites are used.

When using any number of artificial satellites to provide centralized and continuous communication or broadcasting services to designated areas where satellites orbiting celestial bodies, or when performing centralized and continuous observations of the designated areas of satellites orbiting celestial bodies or the weather conditions in that area, The purpose of the present invention is to provide a method that can be universally applied to the setting of orbital parameters of artificial satellites, especially for setting the orbital semi-major axis, eccentricity, orbital inclination, perigee distance, and elevation of any number of artificial satellites. For the right ascension of the intersection and the true anomaly, the present invention also provides detailed values of the orbital parameters obtained from the orbit design according to the method.

(c) With regard to mobile communication and broadcasting of mobile objects, and the purpose of the present invention is clear, the existing communication infrastructure, such as ordinary wired phones, cellular phones and personal hand-held phones, cannot cope with the demand for large amounts of communication with mobile objects .

Due to the influence of man-made buildings and natural geographical features, the geostationary satellite communication system is likely to cause communication interruption, and therefore cannot cope with the demand for a large number of communications with moving objects.

Obviously, satellite communication systems using low-to-medium altitude orbits, such as the Iridium currently under development, cannot solve the demand for large amounts of communication with moving objects, because the duration of visible satellites at high elevation angles is only a few minutes.

The above-mentioned various communication systems cannot fully meet the needs of communicating with mobile objects, but their applicability to mobile objects for digital television broadcasting and digital sound broadcasting is negative.

In the use of artificial satellites to broadcast services to moving objects, the artificial satellite must be stable and visible for a long time at a high elevation angle in the service target area.

In this article, "artificial satellite is visible" is determined as "artificial satellite stays in a space area. In this case, artificial satellite tracking and controlling ground station, various satellite communication transmitting and receiving equipment, and communication between artificial satellites are available. Optical electromagnetic waves." In order to achieve the above-mentioned purpose, it is generally considered that the elliptical orbit of the apogee over the service target area is more preferable. However, no one has exactly proposed the setting except for the Japanese Patent Application Publication No. 11-34996. Appropriate methods and algorithms for orbital parameters.

Among the orbit parameters proposed in Japanese Patent Application Publication No. 11-34996, the minimum value of the eccentricity is 0.24. Even if the eccentricity value is adopted, the distance between the ground and the satellite is always greater than the distance between it and the stationary satellite. Therefore, there are the following problems to be solved.

(1) The waste of free space for electromagnetic wave transmission becomes larger, which requires communication/broadcasting equipment installed on artificial satellites to have higher transmitting and receiving performance. To be more specific, an artificial satellite must have a longer antenna, that is, a transmitter with higher output power, and a receiver with higher receiving performance. On the ground, the transmitting and receiving equipment used for satellite communications also requires a longer antenna, that is, a transmitter with greater output power, and a receiver with higher receiving performance.

(2) As the distance from the ground becomes longer, the communication delay becomes longer. In addition, because the eccentricity is somewhat large, the distance between one end of the service target area and the opposite end and the artificial satellite in use is different. Therefore, when changing the satellites in use, broadcasting failures may occur.

In order to solve the above problems, the present invention improves the orbit parameters proposed by the Japanese Patent Application Publication No. 11-34996 from the viewpoint of "terrestrial communication". The purpose of the present invention is to set a more effective range of orbital parameters in a designated service area of Japanese territory.

Although the purpose of the present invention is to individually solve the problems described in (a), (b) and (c) above, it also solves the combined problems in (a), (b) and (c), or solves (a) , (B) and (c) all questions. Another purpose of the present invention is to solve the problems in (a), (b) and (c) together, and provide a method for estimating the orbital parameters of artificial satellites. Due to the use of multiple artificial satellites, mobile communications can be carried out in designated areas of Japan. And mobile broadcasting has become easier, and at the same time, the orbit parameters suitable for Japan's land can be clarified by limiting the scope.

In addition, a further object of the present invention is to create various systems using multiple artificial satellites after solving the problems described in (a), (b) and (c) above.

The description will be made with reference to (a), (b) and (c) above.

(a) Regarding a plan to use an artificial satellite by setting the argument of perigee, one of the orbital parameters, the operational duration of the artificial satellite is usually defined as the mission life. It is necessary to use a computer to accurately estimate how much the argument of perigee has changed from its initial value after the artificial satellite is launched into a predetermined orbit, so as to achieve the goal when the argument of perigee is not controlled at all.

In order to achieve the above-mentioned objective, the initial value of the argument of perigee in the orbital parameters of the artificial satellite used in the present invention is set with the above-mentioned estimated value.

To achieve the above purpose, the artificial satellite used in the present invention is composed of the following parts: an attitude sensor that detects the attitude of the satellite itself, a computer that processes the detected attitude data, and a thruster or gas injection device that uses the computer to maintain or change the attitude of the satellite to change itself Orbital gas injection device, a communication device that uses electromagnetic waves to establish communication between artificial satellites and control stations. In the case of an artificial satellite orbiting the earth, the artificial satellite may also contain a device for receiving electromagnetic waves from the global positioning satellite system and calculating its own position and speed. The GPS satellite here is a generic term for the United States including the navigation satellites of the Global Positioning System (GPS), the Russian navigation satellites, and the Japanese multi-purpose transportation satellites.

(b) Regarding the orbital arrangement method of multiple satellites In order to achieve the above-mentioned purpose, the present invention uses 6 orbital parameters to describe in detail the orbit of the artificial satellite. These 6 orbital parameters are obtained under the following input conditions, namely, artificial The designated area served by the satellite, the number of artificial satellites, the service frequency of the artificial satellite to the service target area, the service duration of one of the artificial satellites to the service target area and the reference time for defining orbital parameters.

Explain the orbital parameters in more detail. The six orbital parameters are determined by the following processes, namely, the process of defining the number of artificial satellites, the process of defining the semi-major axis of the orbit, the process of setting the eccentricity, the inclination of the orbit, and the argument of perigee. The process of setting the right ascension of the ascending node, the process of setting the true anomaly, and the repeating process from the process of defining the number of artificial satellites to the process of setting the true anomaly.

To achieve the above object, the present invention can use an artificial satellite similar to the previous item (a).

(c) Regarding mobile communication and broadcasting of moving objects. To achieve the above-mentioned purpose, the present invention can use an artificial satellite similar to the previous item (a).

In addition, in order to achieve the above-mentioned purpose, the present invention adopts a group of artificial satellites composed of 3 or 4 artificial satellites, which operate in 3 or 4 elliptical orbits with a 24 hour orbit period, and the orbital inclination of each orbit is different. It is greater than 37° and less than 44°, the eccentricity is not greater than 0.24, or the orbital inclination is greater than 40° and less than 44°, and the eccentricity is greater than 0.24 and less than 0.35. An artificial satellite is arranged in each orbit. Here, regarding the 24-hour orbital period, this article defines 24 hours as a duration with an error of ±10 minutes from 23 hours and 56 minutes.

The following are methods commonly used in (a), (b) and (c) above.

In order to achieve the above-mentioned object, in the present invention, artificial satellites operating in an orbit consistent with the present invention are used in various satellite-using systems, such as orbit control systems for controlling the orbit of artificial satellites, and satellite communications for satellite communications through artificial satellites. System, a geodetic survey system using artificial satellites equipped with earth surveying devices, etc.

When using artificial satellites consistent with the present invention in the service target area, the satellite communication transmitting and receiving equipment of the satellite communication system is a device that uses artificial satellites for signal transmission and reception, including transmitting and receiving tools, and can be installed On moving objects in the service target area. In addition, the transmitting and receiving device can also be equipped with GPS equipment, which can be used to measure its own position by receiving electromagnetic waves from GPS satellites including the Global Positioning System. Or equipped with measuring tools to measure the consumption of materials related to public service charges such as electricity, city gas, and city water.

In addition, in order to achieve the above-mentioned object, in the present invention, the satellite communication system for satellite communication through artificial satellites includes at least: artificial satellites, satellite communication transmitting and receiving equipment for satellite communications through artificial satellites, and transmitting and receiving equipment through artificial satellites and satellite communications. The base station where the receiving device communicates. The artificial satellite moves in an elliptical orbit. Satellite communication transmitting and receiving equipment can be installed on moving objects and contain transmitting and receiving tools. When artificial satellites are used in the designated target service area, they can be used to transmit and receive signals from artificial satellites.

Furthermore, in order to achieve the above-mentioned object, in the present invention, the satellite communication system for satellite communication through artificial satellites at least includes: an artificial satellite, and a plurality of satellite communication transmitting and receiving devices for satellite communication through artificial satellites. The artificial satellite moves in an elliptical orbit. Each satellite communication transmitting and receiving device includes transmitting and receiving tools, which transmit and receive signals through artificial satellites and other satellite communication transmitting and receiving tools. Although other satellite communication transmitting and receiving devices are located outside the target service area, at least one satellite communication transmitting and receiving device is located in the target service area, and its location is capable of satellite communication through artificial satellites. According to the artificial satellite elevation angle of the artificial satellite visible from the target service area, select the relay method in the following range: the relay method between the satellite transmitting and receiving equipment placed in the target service area; the satellite transmitting and receiving located in the target service area The relay method between the equipment and the satellite transmitting and receiving equipment placed in other areas; the relay method between the satellite transmitting and receiving equipment placed outside the target service area.

Description of the drawings

Figure 1 shows the long-term changes in the orbit of an artificial satellite without orbit control and an orbit period of 24 hours, projected on a world map (Isometric projection of latitude and longitude measurement).

The flowchart of Fig. 2 shows a method of setting 6 track parameters according to the present invention.

The explanatory diagram of FIG. 3 shows the information flow of controlling the six orbital parameters of the artificial satellite. The six orbital parameters are set according to the algorithm of the present invention.

Fig. 4 is an explanatory diagram showing the work and information flow of the artificial satellite tracking and control device for controlling the orbit of the artificial satellite.

Fig. 5 is an explanatory diagram showing the processing and information flow of the artificial satellite to control its orbit.

The explanatory diagram of FIG. 6 shows the orbit of an artificial satellite around the earth. In this example, an orbit structure of three artificial satellites is adopted, which is obtained by the algorithm according to the present invention.

The explanatory diagram of FIG. 7 shows the orbit of an artificial satellite around the earth, and the orbit structure of this example is obtained by the algorithm according to the present invention.

Fig. 8 is a view showing an example of a satellite broadcasting system to which the present invention is applied.

Fig. 9 is an explanatory diagram showing an example of a base station of a satellite broadcasting system to which the present invention is applied.

Fig. 10 is an explanatory diagram showing an example of a satellite broadcasting terminal to which the satellite broadcasting system of the present invention is applied.

Fig. 11 is a view showing an example of a satellite broadcasting system to which the present invention is applied, which can also receive terrestrial broadcasting.

Fig. 12 is an explanatory diagram showing an example of a terrestrial broadcasting station to which the satellite broadcasting system of the present invention is applied.

Fig. 13 is an explanatory diagram showing another example of a satellite broadcasting terminal to which the satellite broadcasting system of the present invention is applied.

Fig. 14 is a view showing another example of a satellite broadcasting system to which the present invention is applied.

Fig. 15 is an explanatory diagram showing another example of a base station of a satellite broadcasting system to which the present invention is applied.

Fig. 16 is an explanatory diagram showing another example of a satellite broadcasting terminal to which the satellite broadcasting system of the present invention is applied.

Fig. 17 is a view showing an example of a satellite communication system to which the present invention is applied.

Fig. 18 is an explanatory diagram showing an example of a satellite communication system to which the present invention is applied.

Fig. 19 is an explanatory diagram showing an example of a satellite communication system to which the present invention is applied.

Fig. 20 is a view showing an example of a satellite communication system to which the present invention is applied.

Fig. 21 is an explanatory diagram showing an example of a satellite communication system to which the present invention is applied.

Fig. 22 is a view showing an example of a satellite communication system to which the present invention is applied.

Fig. 23 is an explanatory diagram showing an example of a satellite communication system to which the present invention is applied.

Fig. 24 is a view showing an example of a satellite communication system to which the present invention is applied.

Fig. 25 is an explanatory diagram showing an example of a satellite communication system to which the present invention is applied.

Fig. 26 is a view showing an example of a satellite communication system to which the present invention is applied.

Fig. 27 is an explanatory diagram showing an example of a satellite communication system to which the present invention is applied.

Fig. 28 is a view showing an example of a satellite communication system to which the present invention is applied.

Fig. 29 is an explanatory diagram showing an example of a satellite communication system to which the present invention is applied.

Fig. 30 is a view showing an example of a satellite communication system to which the present invention is applied.

Fig. 31 is an explanatory diagram showing an example of a satellite communication system to which the present invention is applied.

Fig. 32 is an explanatory diagram showing an example of a satellite communication system to which the present invention is applied.

Fig. 33 is a view showing an example of a satellite-satellite communication system to which the present invention is applied.

Fig. 34 is a view showing an example of a geodetic survey system to which the present invention is applied.

The typical graph in Figure 35 shows the maximum duration of visible satellites corresponding to each group of orbital inclination and eccentricity. This duration refers to the time during which an artificial satellite with an orbital period of 24 hours can be simultaneously seen from an elevation angle greater than 70° at the following locations, These cities are Nemuro, Sapporo, Sendai, Niigata, Tokyo, Nagoya, Kanazawa, Osaka, Hiroshima, Kochi, Fukuoka, Kagoshima, and Naha.

The typical detailed graph of Fig. 36 shows a part of Fig. 35, where the longest duration of visible satellites at the same time is greater than 6 hours and 45 minutes.

The graph of computer simulation results in Fig. 37 shows the changes in elevation angles of artificial satellites that are visible in orbit over time. The computer simulation results were executed in Nemuro, Sapporo, Sendai, Niigata, Tokyo, Nagoya, Kanazawa, In Osaka, Hiroshima, Kochi, Fukuoka, Kagoshima, and Naha, from an elevation angle greater than 70°, it can be seen that the orbital period is 24 hours and the orbital parameters of the artificial satellite with an orbital inclination of 42.5° and an eccentricity of 0.21 have the longest duration. .

The sky map in Fig. 38 shows the results of the computer simulation that are visible in Naha orbiting the satellites in orbit. The computer simulation results were executed in Nemuro, Sapporo, Sendai, Niigata, Tokyo, Nagoya, and Kanazawa. , Osaka, Hiroshima, Kochi, Fukuoka, Kagoshima, and Naha, from an elevation angle greater than 70°, at the same time it can be seen that the orbital period is 24 hours and the orbital parameters of the artificial satellite with an orbital inclination of 42.5° and an eccentricity of 0.21 have the longest duration. long.

The graph in Fig. 39 shows that when the argument of perigee varies with different combinations of eccentricity, the longest duration of the satellite can be seen while determining the combination of eccentricity and orbital inclination. The different combinations of eccentricity give each orbit The inclination angle and the orbital inclination angle in Fig. 35 and Fig. 36 also show the longest duration of the satellite.

Figure 40 shows the orbit of the artificial satellite projected on the world map. The orbital period of the artificial satellite in this orbit is 24 hours, the orbital inclination is 42.5°, the eccentricity is 0.21, and the argument of perigee is 210°. The figure is the latitude and Isometric projection of longitude measurement.

Figure 41 shows the orbit of an artificial satellite projected on a world map. The orbital period of the artificial satellite in this orbit is 24 hours, the orbital inclination is 42.5°, the eccentricity is 0.21, and the argument of perigee is 230°. The graph is the latitude and Isometric projection of longitude measurement.

Figure 42 shows the orbit of an artificial satellite projected on a world map. The orbital period of the artificial satellite in this orbit is 24 hours, the orbital inclination is 42.5°, the eccentricity is 0.21, and the argument of perigee is 250°. The figure is the latitude and Isometric projection of longitude measurement.

Figure 43 shows the orbit of an artificial satellite projected on a world map. The orbital period of the artificial satellite in this orbit is 24 hours, the orbital inclination is 42.5°, the eccentricity is 0.21, and the argument of perigee is 270°. The graph is the latitude and Isometric projection of longitude measurement.

Figure 44 shows the orbit of the artificial satellite projected on the world map. The orbital period of the artificial satellite in this orbit is 24 hours, the orbital inclination is 42.5°, the eccentricity is 0.21, and the argument of perigee is 290°. Isometric projection of longitude measurement.

Figure 45 shows the orbit of the artificial satellite projected on the world map. The orbital period of the artificial satellite in this orbit is 24 hours, the orbital inclination is 42.5°, the eccentricity is 0.21, and the argument of perigee is 310°. The figure is the latitude and Isometric projection of longitude measurement.

The graph in Fig. 46 shows the argument of perigee corresponding to the eccentricity of each elliptical orbit when the elliptical orbit with an orbital period of 24 hours intersects the stationary orbit.

Figure 47 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 220° and 3 artificial satellites (42.5°, 0.21) provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 48 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 230° and 3 satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 49 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 250° and 3 artificial satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 50 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 270° and 3 artificial satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 51 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 290° and three artificial satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 52 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 310° and 3 artificial satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 53 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 220° and 4 satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 54 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 230° and 4 artificial satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 55 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 250° and 4 artificial satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 56 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 270° and 4 artificial satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 57 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 290° and 4 satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

Figure 58 is the simulation result expressed by the time ratio contour (%). When the argument of perigee is 310° and 4 satellites (42.5°, 0.21) are used to provide services 24 hours a day, any one of them is artificial The satellite is visible from an elevation angle greater than 70°.

The graph in Fig. 59 shows the change of eccentricity. The change of eccentricity is based on 0:00:000 (UTC) on October 1, 2001. The combination of orbital inclination and eccentricity is (42.5°, 0.21), Obtained after more than 3 years of long-term orbit forecast simulation under the condition of complete orbit control.

The graph in Fig. 60 shows the change of the orbital inclination angle. The orbital inclination angle is changed at 0:00:000 (UTC) on October 1, 2001. The combination of orbital inclination and eccentricity is (42.5°, 0.21). Obtained after more than 3 years of long-term orbit forecast simulation under the condition of complete orbit control.

The graph in Fig. 61 shows the change of the argument of perigee. The eccentricity change is based on October 1, 2001 0:00:000 (UTC). The combination of orbital inclination and eccentricity is (42.5°, 0.21) , Under the condition of complete orbit control, obtained after more than 3 years of long-term orbit forecast simulation.

The graph in Fig. 62 shows the change in right ascension of the ascending node. The change in right ascension of the ascending node is based on 0:00:000 (UTC) on October 1, 2001. The combination of orbital inclination and eccentricity is (42.5° , 0.21), obtained after more than 3 years of long-term orbit forecast simulation under the condition of complete orbit control.

Figure 63 is a simulation diagram illustrating satellite services in England.

Figure 64 is a simulation diagram illustrating satellite services in England.

Figure 65 is a simulation diagram illustrating satellite services in major European countries.

Figure 66 is a simulation diagram illustrating the satellite service in New Zealand.

detailed description

DETAILED DESCRIPTION OF THE BEST EMBODIMENTS The following will describe embodiments according to the present invention.

Methods for setting orbital parameters (arithmetic rules) Examples of orbital parameter setting values and orbital structure derived from the algorithm Methods for realizing and controlling the set orbital parameters Using the artificial satellite operating in orbit according to the present invention (1) The method of setting the orbital parameters (arithmetic law) of the system below corresponds to the above three items (a), (b) and (c), explaining the methods for items (a) and (b). As for the problem in (c), the setting of the argument of perigee is solved by (a), and the method of arranging multiple artificial satellites is solved by (b). Therefore, first, the numerical range of orbital parameters suitable for mobile communication and broadcasting using the artificial satellite group will be explained here.

According to 13 cities such as Nemuro, Sapporo, Sendai, Niigata, Tokyo, Nagoya, Kanazawa, Osaka, Hiroshima, Kochi, Fukuoka, Kagoshima, and Naha, artificial man-made orbits can be seen at the same time from an elevation angle greater than 70°. The duration of the satellite is used as an evaluation index to study the orbital parameter combination of orbits with an orbital period of 24 hours.

By giving the position and speed of the artificial satellite at a certain time, the orbit of the artificial satellite can be uniquely determined. Therefore, by giving 6 orbital parameters at a certain time, the orbit of the artificial satellite can be uniquely determined. Here, Kepler orbit parameters are used as a method to explain orbit parameters. The Kepler orbit parameter is composed of 6 orbital parameters, that is, the semi-major axis of the ellipse, the eccentricity of the oblateness of the ellipse, the orbital inclination of the inclination of the orbital plane, and the ascension of the ascending node (right ascending angle) refers to the satellite The orbit from south to north passes through the angle corresponding to the line between the ascending node and the vernal equinox of the equatorial plane. The perigee (magnitude) angle refers to the angle between the ascending node and the perigee, as well as the true anomaly, which measures the artificial satellite in the orbit. The position relative to the center of the earth at a certain time. The average anomaly or deviated anomaly can be used instead of the true anomaly.

Since the orbital period is 24 hours, the orbital semi-major axis, which is one of the orbital parameters, is given by the orbital period. Secondly, the argument of perigee, one of the orbital parameters, is determined to be 270°. With the orbital semi-major axis and the argument of perigee, the combination of the orbital inclination and eccentricity of the two orbital parameters can be considered. In this way, the shape of the orbit projected on the ground is uniquely determined. If the other two orbital parameters ascending node right ascension and true anomaly are determined according to a certain datum, then the longitude and azimuth of the orbit projected on the ground is determined. At this time, it is possible to calculate the duration of simultaneous visible satellites in the 13 cities mentioned above from an elevation angle greater than 70°. Therefore, by successively changing the combination of the two orbital parameters of the orbit inclination and the eccentricity, the orbit projected on the ground moves in the longitude direction. In this way, based on the combination of the two orbital parameters, the orbital inclination angle and the eccentricity, it is possible to continuously calculate the duration of visible satellites in the above-mentioned 13 cities from an elevation angle greater than 70°. By comparing these results, it is possible to finally calculate the maximum value of the duration of visible satellites in the above 13 cities from an elevation angle greater than 70°.

Figure 35 shows the maximum duration of visible satellites obtained from the combination of orbital inclination and eccentricity according to the above procedure, where the orbital inclination varies from 35° to 44°, and the eccentricity varies from 0.0 to 0.35. For example, it can be seen from Figure 35 that when the orbital inclination is 35° and the eccentricity is 0.2, the maximum duration of the visible satellite is about 6 hours.

Figure 36 shows the details of a part of the above figure, where the longest duration of visible satellites at the same time is greater than 6 hours and 45 minutes, and the eccentricity ranges from 0.09 to 0.25.

It can be seen from Figure 36 that when the orbital inclination is 42.5° and the eccentricity is 0.21, it can be seen that the value of the satellite duration is the largest and is greater than 8 hours. The graph in Fig. 37 shows the change in elevation angle with time when artificial satellites are visible in the above 13 cities. When the elevation angle is greater than 70°, Sapporo has the latest time, and when the elevation angle is less than 70°, the time of Nemuro is the earliest, so the time difference between the two places is more than 8 hours.

As shown in Figure 37, the elevation angle of Naha changes in such a way that the elevation angle rises, then falls, then rises again, and finally falls. The sky map in Fig. 38 shows the result of computer simulation which is the visible position of the artificial satellite in Naha. Figure 38 can also be regarded as a star map. The center of the concentric circles is the zenith, the top is north, the right is west, the bottom is a guide, and the left is east. Concentric circles are elevation angles separated by 20°. Plotted points indicate the azimuth of the artificial satellite in the sky, with an interval of 1 hour, and the line of the plotting points is the orbit in the sky.

It can be seen from Fig. 38 that the visible azimuth of the artificial satellite is moving from the zenith to the horizon at the north end, which can explain the change in elevation angle with time in Fig. 37. The changes in elevation angles of other cities in Figure 37 over time can be explained by similar star charts. When the orbital inclination angle is 44° in Fig. 35 and Fig. 36, the reason why the longest duration of the visible satellite is shortened is that the visible azimuth of Naha's artificial satellite moves too far to the horizon, so that the elevation angle is again less than 70°, and then it returns to greater than 70° elevation angle direction. Therefore, the maximum duration of the visible satellite is shortened at the same time.

In the case of using three artificial satellites for 24-hour service, the combination of the orbital inclination and the eccentricity with the longest duration of more than 8 hours of visible satellites at the same time is more preferable. In the case of using 4 artificial satellites for 24-hour service, it is more preferable to combine the orbital inclination and eccentricity of the satellite with the longest duration of more than 6 hours at the same time. Refer to Figure 35 and Figure 36 for the combination of orbital inclination and eccentricity.

When multiple artificial satellites in an elliptical orbit are used for broadcasting services, the artificial satellites for broadcasting services need to be continuously switched. When using the above method for mobile broadcasting and communication, it is important to see artificial satellites in multiple cities at the same time from high elevation angles.

(a) Method of setting the argument of perigee Here, it is assumed that other orbital parameters such as semi-major axis, eccentricity, and orbital inclination have been set according to the method (b) described later.

In the case of a certain designated area, such as the territory of Japan, as the service area, when setting the right ascension of the ascending node at a certain datum, the argument of perigee in a certain range is obtained so that the artificial satellite can operate over the service area.

Using orbital parameters and reference time as input conditions, computer simulation is used to set the argument of perigee.

As a known example, when the orbital inclination is 40°, the eccentricity is 0.24, and the orbital period is 24 hours, Table 1 shows the computer simulation results of the changes in orbital parameters for more than 10 years. The 10-year duration is determined by the total mission life span of the above-mentioned 10 years. The simulation result is based on the condition that the orbit correction control has not been carried out in the past 10 years, that is, the gas injection device installed on the artificial satellite has not been launched in the past 10 years.

Table I

Figure 1 shows the orbit projected on the ground when the orbit parameters shown in Table 1 are used. The calculation of each orbit projected on the ground for more than one day is based on the initial value of the orbit parameter in Table 1, the orbit parameter value after 1095 days, the orbit parameter value after 2190 days, and the orbit parameter value after 3650 days.

The following can be understood from the trajectory projected on the ground from the initial value to the value after 3650 days. Number 1 in the figure is an orbit projected on the ground for more than 1 day from the reference time, number 2 is an orbit projected on the ground for more than 1 day from 1095 days to 1096 days, and number 3 is an orbit projected on the ground from 2190 days to 2191 days. 1 Orbits above sky, number 4 is the orbit projected on the ground for more than one day from 3650 days later to 3651 days later.

The orbit projected on the ground before 2190 days moves to the west with time, and then moves to the east with time, until 3650 days later.

The orbit projected on the ground before 2190 days tilted with time, and the north end became sharp.

The reach of the orbit projected on the ground in the latitude direction narrows with time.

As for the movement of the orbit to the west, by adjusting the true anomaly to match the ascension of the ascending node, and moving the orbit projected on the ground back to the east, the orbit projected on the ground can be moved to the sky over Japan. This orbit correction method is the same as the method of geostationary satellite orbit longitude control. Therefore, this control can be performed by launching satellite gas injection devices at the three positions of perigee, apogee, and finally back to perigee. At this time, the semi-major axis, eccentricity, and true anomaly can be corrected. Through the correction control of the eccentricity, the sharp north end of the orbit projected on the ground described in the second question above can be corrected and restored to its original state.

The narrowing of the latitude reach of the orbit projected on the ground mentioned in the third question above is caused by reducing the orbital inclination. The correction method is similar to the latitude control method of the geostationary satellite orbit. Specifically, when the artificial satellite passes the intersection of the orbital plane and the equatorial plane, the gas injection device launches the thruster in a direction perpendicular to the orbital plane.

The above two control methods can be performed periodically, for example, once every 30 days or every 60 days. Through periodic control, the semi-major axis, eccentricity and orbital inclination can be controlled to the nominal value or close to the orbital parameter setting value.

The second problem is that the orbit projected on the ground tilts over time. This phenomenon is caused by the change of the argument of perigee, which is not observed in the orbit of a geostationary satellite.

As shown in Table 1, according to the above computer simulation results, the argument of perigee has changed by about 90° from its initial value of 270°, and it will become 357.4° after nearly 10 years. In the case that the gas injection device that does not allow the argument of perigee to change and controls the argument of perigee is launched using a method similar to the above-mentioned orbital control, the control is carried out in such a way that the artificial satellite passes through or before the ascending node of the equatorial plane and the orbital plane. After descending the intersection point, the gas injection device is launched in a direction parallel to the orbital plane, but it consumes a lot of thrusters. Table 2 shows the simulation results of the orbit control acceleration required for periodic orbit control when 4 artificial satellites are arranged on 4 orbits with 90° apart ascending node right ascension. This is the amount of acceleration required for a year.

Table 2 (Unit: m/s)

It can be seen from Table 2 that although the amount of acceleration required to control the argument of perigee depends on the position of the orbital arrangement, its maximum value is about 3/4 of the total amount of orbital control acceleration. Since the number of thrusters consumed by the gas injection device used for orbit control has increased significantly, the equipment installed on the artificial satellite must be reduced, otherwise the in-orbit life of the artificial satellite will inevitably be shortened.

Therefore, in the present invention, the argument of perigee is allowed to change in advance, and this value is a certain allowable range in the process of setting the argument of perigee.

If the 90° change is allowed in the above example, and the initial value of the argument of perigee is set to 235°, it can be predicted that the argument of perigee will become close to 325° after the mission life is 10 years. If the nominal value at that time is assumed to be 270°, the uncontrolled argument of perigee can be maintained within the nominal value of ±45°, and the orbit projected on the ground can be maintained to maintain the visibility of the artificial satellite.

Setting the orbital parameters without controlling the argument of perigee can fully reduce the number of thrusters placed on the artificial satellite.

When the 90° change is not allowed, a method can be used to control the argument of perigee when the mission lifetime is 10 years. For example, the argument of perigee can be returned to the initial value 5 years after the mission starts. In the example described in Table 1, the argument of perigee after 5 years is nearly 312°, which is a change of nearly 42° from the initial value of 270°. At that time, if the initial value is set to 249°, it is estimated that the argument of perigee will be nearly 291° in 5 years. Assuming that the nominal value at that time is 270°, the uncontrolled argument of perigee can be maintained within the nominal value of ±21°, and the orbit projected on the ground can be maintained to maintain the visibility of the artificial satellite. In addition, it can also be considered that returning the argument of perigee to the initial value after 5 years has extended the mission life.

Although the time for correcting the argument of perigee in the above example is 5 years after starting the mission, according to the allowable range of the argument of perigee, the correction time can also be set to 1 year later, 3 years later, and so on.

In addition, when the mission life is 10 years, a control method can be adopted, that is, the initial value is set according to the allowable width of the argument of perigee, and when the limit value of the allowable width of the argument of perigee is reached, the argument of perigee returns to the initial value. For example, in the example in Table 1, the argument of perigee after 6 years is nearly 321°, which has changed by nearly 51° from the initial value. It can be considered that the initial value of the argument of perigee in this control method is set to 255°. After 6 years, the argument of perigee returns to its initial value so that it can remain within the nominal value of 270°±25°. At that time, during the remaining four years of mission life, the change in the argument of perigee was equivalent to the initial value after four years.

The following is a specific example.

(1) At the beginning of Article (1), the orbital parameters that are more preferable in the case of using multiple artificial satellites for broadcasting and communication services to mobile objects in Japan have been described in Fig. 35 and Fig. 36. In Figure 36, the combination of orbital inclination and eccentricity gives the longest duration of visible satellites in 13 cities at the same time, which can be obtained from each orbital inclination. Specifically, when the orbital inclination is 40°, it can be seen that the eccentricity corresponding to the longest duration of the satellite is 0.16.

When this combination is expressed as (40°, 0.16), the available combinations are (40°, 0.18), (42°, 0.20), (42.5°, 0.21), (43°, 0.22) and (43.5°, 0.24). When the argument of perigee becomes these combinations, artificial satellites can be simultaneously visible in the above 13 cities at an elevation angle greater than 70°. Figure 39 shows how the duration of the simultaneous visible satellites changes.

In the combination of (42.5°, 0.21), when the argument of perigee is in the range of about 223° to 270°, the longest duration of the visible satellite at the same time is more than 8 hours, but when the argument of perigee is greater than 270°, it is visible at the same time The maximum duration of the satellite will be reduced. It can be understood that when the lower limit value of the argument of perigee is set to 220° to 230° and the upper limit value is 270°, good service can be provided for a long time in other combinations. However, in the case of using four artificial satellites to provide 24-hour service, the set width is selected from the range of perigee angles where the longest duration of visible satellites at the same time exceeds 6 hours. Therefore, in this case, it is not necessary to set the lower limit of the argument of perigee to 220° to 230°.

For reference, for the combination of (42.5°, 0.21), Figure 40, Figure 41, Figure 42, Figure 43, Figure 44, and Figure 45 show the orbits projected on the ground, when the argument of perigee is 210°, At 230°, 250°, 270°, 290°, and 310°, the longest duration of visible satellites at the same time is obtained.

It should be noted here that the intersection of the artificial satellite orbit and the geostationary satellite orbit may appear at a certain argument of perigee, because the orbit of the artificial satellite rotates in the orbital plane due to the change of the argument of perigee. The graph in Fig. 46 shows the argument of perigee corresponding to each eccentricity when an elliptical orbit with an orbital period of 24 hours intersects with a stationary orbit. As shown in Figure 46, when the perigee exists over the southern hemisphere, there are two situations: the orbit on the side of the ascending node intersects the orbit of the geostationary satellite, and the orbit on the side of the descending node intersects the orbit of the geostationary satellite. Similarly, when the perigee exists over the northern hemisphere, there are these two situations. When the combination of the argument of perigee is (42.5°, 0.21), since the eccentricity is 0.21, the argument of perigee at the intersection of the artificial satellite orbit and the geostationary satellite orbit is 257.9° and 282.1°, as shown in Figure 46. In the actual operation of the artificial satellite, the orbit control is performed to change the argument of perigee before the orbit of the geostationary satellite intersects, so as to avoid the orbit of the artificial satellite and the geostationary satellite orbit from intersecting.

For reference, when three artificial satellites (42.5°, 0.21) are used to provide services 24 hours a day, Figure 47 to Figure 52 are examples of simulation results expressed by time ratio contours (%), when the arguments of perigee are respectively At 220°, 230°, 250°, 270°, 290° and 310°, any one of the satellites is visible from an elevation angle greater than 70°. Similarly, when four (42.5°, 0.21) artificial satellites are used to provide services 24 hours a day, Figure 53 to Figure 58 are examples of simulation results represented by time ratio contour lines (%), when the argument of perigee is 210, respectively. At °, 230°, 250°, 270°, 290° and 310°, any one of the artificial satellites is visible from an elevation angle greater than 70°. The time ratio of the area surrounded by the contour "100" is 100%, and the time ratio of the area surrounded by the contour "90" is 90%. Setting the argument of perigee within the allowable range as described above can alleviate the aforementioned requirements for artificial satellite orbit control and provide satellite communications and broadcasting services to almost all areas of the Japanese territory with high elevation angles.

Figure 59 to Figure 62 show the long-term orbit forecast for more than 3 years under the condition that the artificial satellite (42.5°, 0.21) is fully orbit controlled with October 1, 2001 0:00:000 (UTC) as the reference time The simulation results obtained. The initial values of the orbital parameters are: the orbital period is 24 hours, the orbital inclination is 42.5°, the eccentricity is 0.21, and the argument of perigee is 270°. Fig. 59 shows the long-term change of eccentricity. Figure 60 shows the long-term changes in orbital inclination. Figure 61 shows the long-term changes in the argument of perigee. Figure 62 shows the long-term changes in the ascension of the ascending node. The abscissa in the figure represents the initial value of the ascension of the ascending node. It can be seen that the change of orbital parameters depends on the change of the initial value of ascending node right ascension. Since the change of the argument of perigee depends on the change of the initial value of ascending node right ascension, the initial value of the argument of perigee should take into account the change of the initial value of ascending node right ascension. For example, when the initial value of the ascension of the ascending node is around 190°, almost no change in the argument of perigee has been observed for a long period of time. Therefore, by setting the initial value of the ascending node right ascension to 190°, the orbit control can be simplified.

(b) Orbital arrangement method of multiple satellites Here, the method of setting orbital parameters according to the present invention will be described. Fig. 2 is a flowchart showing a setting method.

In the case of using multiple artificial satellites to provide services to a designated area intensively and continuously, the orbits projected by the individual artificial satellites on the ground must be consistent with each other. To meet this condition, the semi-major axis, eccentricity, orbital inclination angle and argument of perigee are almost equal in the orbital parameters of these orbits. Therefore, in the following process, the semi-major axis, eccentricity, orbital inclination angle, and argument of perigee are set together as the orbital parameters of all artificial satellites, and the ascension and argument of perigee of the ascending node at a certain reference time are individually set for each satellite set up.

() The setting of the reference time (No. 5) defines the reference time (time point) of the six orbital parameters of the artificial satellite.

() Setting of the number of artificial satellites n (No. 6) Set the number of artificial satellites n (n is a positive integer).

() Setting of provisional value of argument of perigee ω (No. 7) gives an arbitrary argument of perigee ω as a provisional value.

When the service target area is a designated area in the northern hemisphere, when communicating and broadcasting services, it is more preferable to place the apogee of the artificial satellite orbit over the designated service area. Then the nominal value of the argument of perigee is set to 270°. favorable. When observing the central celestial body orbiting by artificial satellites, it is more preferable to place the artificial satellite orbit perigee above the designated service area, and it is usually more advantageous to set the nominal value of the argument of perigee to 90°. When the service target area is a designated area in the southern hemisphere, on the contrary, in the former case, it is usually more advantageous to set the nominal value of the argument of perigee to 90°. In the latter case, it is usually more advantageous to set the nominal value of the argument of perigee to 270°.

In addition, as described in (a), the setting value of the argument of perigee can be set within the allowable range.

() Setting of the temporary value of semi-major axis a (No. 8) In the case where multiple artificial satellites are used to concentrate and continuously serve the designated area, the orbits projected by the individual artificial satellites on the ground must be consistent with each other. In addition, every artificial satellite must operate over the same place on the ground every day. That is, no matter how time passes, the orbit projected on the ground must be fixed for a long time. In order to meet this requirement, when the artificial satellite orbits the central celestial body rotates once, the artificial satellite must orbit the celestial body an integer number of times. When the central celestial body is the earth, the range of the number of operations m satisfies the relational formula 1 m 16 (m is an integer). The present invention can be applied to a system using multiple artificial satellites. The orbital periods of these artificial satellites are shown in Table 3.

According to the number of operations m, when the central celestial body is the earth, the orbit period p (unit: hour) of the artificial satellite can be calculated by the following equation.

P=23.93/m According to the orbit period p, the semi-major axis a of the artificial satellite orbit can be determined as shown in Table 3. When setting the following orbital parameters, you can select from the semi-major axis in Table 3. However, when selecting, if the central celestial body is the earth, unless at least the relational expression p×n 23.93 is satisfied, the service cannot be continuously provided to the designated area 24 hours a day.

table 3

(v) Setting a provisional value of eccentricity e (No. 9) gives an arbitrary eccentricity e as a provisional value.

For example, suppose that the service duration required by an artificial satellite in a designated area is Ts (unit: second). Assuming that the time required for an artificial satellite to travel from a perigee to its orbit to start a service point is Ti, the off-anchor angle of the start service point is Ei (unit: radians), and the true anomaly angle is θi (unit: radians). The following equation is obtained.

Ti=(Ei-e×sinEi)×p/(2×π)CosEi=(e+cosθi)/(1+e×cosθi)

Therefore, assuming that the stop service point on the track is symmetrical to the start service point of the track's semi-major axis, the following relationship can be obtained.

Ts p-Ti×2 (p-Ti×2)-Ts 0 Since it is necessary to consider the rotation of the artificial satellite orbiting the celestial body, when considering the combination of the anomalous angle Ei and the eccentricity e of the starting point of service, satisfy The eccentricity of the above relationship is given as the initial value. When considering this combination, it is convenient for the minimum anomaly angle to be π/2 and the maximum value to be π.

() Set the temporary value of the orbital inclination angle (No. 10) to give an arbitrary orbital inclination angle i as a temporary value.

At this time, a more convenient method is to first obtain the maximum and minimum longitude of the designated service target area, and then use the average value as the initial value of the orbital inclination.

(vii) Setting of temporary value of true anomaly angle When satellite 1 is at perigee, the true anomaly angle θk (unit: radians) of satellite k (1kn, k is an integer) is given by the following equation. Since the deviated anomaly angle corresponds to the true anomaly, first the eccentricity anomaly angle is calculated, and then the true anomaly angle is calculated.

-23.93×(k-1)/n×3600=(Ek-e×sinEk)×P/(2×π)cosθI=(e-cosEi)/(e×cosEi-1) According to the right ascension of the ascending node Ωk In combination with the true anomaly angle θk, the orbits of multiple artificial satellites projected on the ground are consistent with each other, and n satellites from satellite 1 to satellite n continuously give separate orbits projected on the ground. That is, n satellites from No. 1 satellite to No. n satellite repeatedly operate over the designated area.

(viii) Setting of temporary values of ascending node right ascension Ω1 and true anomaly θ1 of No. 1 satellite (No. 11) In order to serve a designated area, a single artificial satellite must operate over the designated area. Therefore, set the ascending node right ascension Ω1 and the true anomaly θ1 of the No. 1 satellite at the reference time, so that it can operate over the designated area. At this time, by setting the true anomaly angle θ1=0 (°) for computer simulation, the ascending node right ascension Ω1 can be easily set.

(ix) Setting of temporary values of ascending node right ascension Ωk and true anomaly angle θk of satellite k (No. 12) According to the ascending node right ascension Ω1 and true anomaly angle θ1 set for satellite No. 1, satellite k The right ascension Ωk and the true anomaly θk of the ascending node at the reference time can be calculated continuously from k=2 to k=n. Specifically, when the ascension of the ascending node Ω1 (unit: radians) of the orbit of the artificial satellite No. 1 is used as a reference, the ascension Ωk (unit: radians) of the ascending node of the artificial satellite k (1kn) orbit is given by the following equation .

The equation Ωk=Ω1+(k-1)/n×360 is used to arrange multiple artificial satellites at equal angular intervals on the orbital plane.

(x) Evaluation (No. 14) Evaluate whether a group of artificial satellites operating in the orbit determined by the orbit parameters given above meet the requirements. For example, the service content of the designated service area has the following requirements.

The duration of continuous service of an artificial satellite to the designated area.

The duration of the artificial satellite visible in the air from a high elevation angle in the designated area.

The distance between the artificial satellite and the designated area, and the change of the distance over time.

The delay time of electromagnetic wave propagation.

Electromagnetic wave Doppler drift, and circuit design.

Observe space solutions in designated areas. The requirements for orbit control of artificial satellites are as follows.

The long-term changes of each track parameter of each track.

The control amount of each track parameter of each track, and the number of thrusters required for control.

The orbit parameters set above are used as input values and can be easily evaluated by computer simulation. Before checking the track arrangement, the items and requirements required for the evaluation are usually set.

(xi) Repeating the process of setting the orbital parameters When the above evaluation does not meet the requirements, repeat the process from step (iii) to step (x). Repeat the process from step (i) to step (x) if necessary. When there is no need to review the temporary value, there is no need to review the corresponding item. There, the sequence of the above procedures can be changed arbitrarily as needed.

In the case of setting the orbital parameters in the above-mentioned method, the artificial satellites No. 1 to the artificial satellites No. n continuously appear in the designated target area served by the group of artificial satellites. In addition, if the right ascension of the ascending node set in step (ix) is determined by the following equation Ωk=Ω1-(k-1)/n×360 (1 kn, k is an integer), and step (vii) is set The anomaly angle of is determined by the following equation 23.93×(k-1)/n×3600=(Ek-e×sinEk)×P/(2×π), then similar results can be obtained. In this case, the artificial satellite No. n to the artificial satellite No. 1 continuously appear in the designated target area provided by the group of artificial satellites.

(xii) When the above evaluation meets the requirements, the final orbit parameters of each artificial satellite at the reference time are obtained.

(2) Examples of orbital parameter values and orbital arrangements set by the above-mentioned algorithm. Examples of orbital parameter values and orbital arrangements that are set by the above-mentioned algorithm are as follows.

As described later, the orbit of the artificial satellite is always changed by the gravity field of the earth and the gravity of the moon and the sun, and the orbit of the artificial satellite is usually controlled at a certain angle within the allowable range. Therefore, each orbit parameter value represents a target nominal value after orbit control.

In the following two tables, Ω1 and θ1 are the ascension and true anomaly of the ascending node of the artificial satellite No. 1 set corresponding to the reference time.

The examples shown in Tables 4 and 5 are the orbital parameters and orbital arrangements of satellite communication and broadcasting networks using three artificial satellites, which operate in orbits with an orbital period of 24 hours. The combination of eccentricity and orbital inclination is within the range shown in Figs. 26 and 27. The argument of perigee is less than 180°.

The example of the track arrangement uses the entire territory of Japan as the target service area.

Table 4

table 5

Artificial satellites using any of the above-mentioned orbital parameters can be seen simultaneously in all cities from Nemuro to Naha from an elevation angle greater than 70°. The maximum visible satellite time is more than 8 hours and the minimum is 6 hours. When the orbital inclination is about 42.5° and the eccentricity is about 0.21, the longest duration of 8 hours can be obtained. Therefore, by adopting a set of artificial satellites with the above-mentioned orbital parameters, at least one or more artificial satellites can be simultaneously visible 24 hours a day from a high elevation angle in all cities from Nemuro to Naha.

In this orbital arrangement example, there are 3 orbital planes as shown in FIG. 6, and artificial satellites 60, 61, and 62 are arranged on their respective orbits. The artificial satellites 60, 61, and 62 travel in orbits 63, 64, and 65 for about 24 hours for a week. The period of each orbit of the artificial satellites 60, 61 and 62 is 24 hours. The arrangement of each orbit makes the argument of perigee in the range of greater than 180° and less than 360°; the eccentricity is not greater than 0.24, and the orbital inclination is greater than 37° and less than 44°, or the eccentricity is greater than 0.24 and less than 0.35, and the orbital inclination is greater than 40° and less than 44°. The ascension of the ascending node of the three artificial satellites is separated by 120°, as shown in Figure 6. This setting makes the apogee of each orbit appear at a proper position over the Japanese territory. As for the positional relationship of the various artificial satellites in each orbit, when the artificial satellite 60 is at the perigee of its corresponding orbit 63, the artificial satellite 61 is one third of the orbital period after the true anomaly corner of its position on the corresponding orbit 64. ; The true anomaly of the artificial satellite 62 on its corresponding orbit 65 is one-third of the orbital period. This orbit arrangement is obtained by the formula shown in the schematic diagram in FIG. 2 and the formula of the argument of perigee setting method, and is achieved by the control method shown in FIGS. 3, 4, and 5.

According to this orbital arrangement, any one of the artificial satellites 60, 61 and 62 is always visible from the Japanese territory from Hokkaido to Okinawa from an elevation angle greater than 70°. Since the orbital periods of the artificial satellites 60, 61, and 62 are nearly 24 hours, the visible time and invisible time of the artificial satellite at an elevation angle greater than 70° are regular and regular. In this case, in the Japanese territory, the outflow of artificial satellites 60, 61 and 62 is now greater than 70° elevation angle, one cycle per day, and the visible time of each artificial satellite staying in the direction greater than 70° elevation angle is the longest 8 hours, the shortest 6 hours. This cycle repeats every day in a 24-hour cycle.

Figures 8 to 34 show examples of orbital alignment systems used for satellite communications or satellite broadcasting. Therefore, by using artificial satellites represented by artificial satellites 90 in Figures 8 to 34, it is possible to establish that shielding objects or Satellite communications or satellite broadcasting systems in which interfering objects cause communication interruptions.

Tables 6 and 7 show examples of orbital parameters and orbital arrangements of satellite communication and broadcasting networks composed of 4 artificial satellites with an orbital period of 24 hours. The combination of eccentricity and orbital inclination can be within the range shown in FIG. 35 and FIG. 36. The argument of perigee is less than 180°.

Table 6

Table 7

Artificial satellites using any of the above-mentioned orbital parameters can be seen simultaneously in all cities from Nemuro to Naha from an elevation angle greater than 70°. The maximum visible satellite time is more than 8 hours and the minimum is 6 hours. When the orbital inclination is about 42.5° and the eccentricity is about 0.21, the longest duration of 8 hours can be obtained. Therefore, by adopting a set of artificial satellites with the above-mentioned orbital parameters, at least one or more artificial satellites can be simultaneously visible 24 hours a day from a high elevation angle in all cities from Nemuro to Naha.

In this orbital arrangement example, there are 4 orbital planes as shown in FIG. 7, and the artificial satellites 70a, 70b, 70c, and 70d are arranged on their respective orbits. The artificial satellites 70a, 70b, 70c, and 70d travel on orbits 71a, 71b, 71c, and 71d, respectively, for about 24 hours. The period of each orbit of the artificial satellites 70a, 70b, 70c and 70d is 24 hours. The arrangement of each orbit makes the argument of perigee in the range of greater than 180° and less than 360°; the eccentricity is not greater than 0.24, and the orbital inclination is greater than 37. °, less than 44°, or eccentricity greater than 0.24, less than 0.35, orbital inclination greater than 40°, less than 44°. The ascension of the ascending node of the four artificial satellites is separated by 90°, as shown in Figure 7. This setting makes the apogee of each orbit appear at an appropriate position over the Japanese territory. As for the positional relationship of the artificial satellites in each orbit, when the artificial satellite 70a is at the perigee of its corresponding orbit 71a, the artificial satellite 70b is one-fourth of the orbital period after the true anomaly corner of the position on the corresponding orbit 71b. The artificial satellite 70c is at the apogee of its corresponding orbit 71c; the true anomaly of the artificial satellite 70d on its corresponding orbit 71d is ahead of a quarter of the orbital period.

According to this orbital arrangement, any one of the artificial satellites 70a, 70b, 70c, and 70d is always visible from the Japanese territory from Hokkaido to Okinawa from an elevation angle greater than 70°. Since the respective orbital periods of the artificial satellites 70a, 70b, 70c, and 70d are nearly 24 hours, the visible time and invisible time of the artificial satellite at an elevation angle greater than 70° are regular and regular. This orbit arrangement is obtained by the formula shown in the schematic diagram in FIG. 2 and the formula of the argument of perigee setting method, and is achieved by the control method shown in FIGS. 3, 4, and 5.

In this case, in Hokkaido, Honshu, Shikoku and Kyushu, and the four islands of Okinawa, the artificial satellites 70a, 70b, 70c, and 70d rotate once a day and are now greater than 70° elevation angle, and each artificial satellite stays at a zenith greater than 70° The visible time of the direction is 8 hours at the longest and 6 hours at the shortest. In addition, sometimes multiple artificial satellites can be seen in the direction of the zenith greater than 70°. This cycle repeats every day in a 24-hour cycle.

Figures 8 to 34 show examples of orbital alignment systems used for satellite communications or satellite broadcasting. Therefore, by using artificial satellites represented by artificial satellites 90 in Figures 8 to 34, it is possible to establish that shielding objects or Satellite communications or satellite broadcasting systems in which interfering objects cause communication interruptions.

(3) Realization and control of the method of setting orbit parameters and setting orbit arrangement The orbit of the artificial satellite with the orbit parameters thus set is controlled and realized in this way.

As shown in Figure 3, when the artificial satellite 20 is launched, the information of the six orbital parameters 17 previously set at the reference time is input to the launch tool tracking and control device 21, and the information of the scheduled launching orbital parameters 22 is transmitted from 21 to the launcher. tool. The launch tool 23 is automatically launched into a predetermined orbit according to the information or through the control of the launch tool tracking and control device 21.

After the artificial satellite is launched into orbit, the information of the six orbital parameters at the reference time is periodically input to the artificial satellite tracking and control device 18, so that the information of the control command 19 is transmitted to the artificial satellite 20, and the artificial satellite 20 is installed on it. The control system controls 6 orbital parameters for the predetermined orbit time.

This orbit control method is based on a general method, as detailed below.

The 6 orbital parameters 17 (semi-major axis 11, argument of perigee 12, eccentricity 13, orbital inclination angle 14, ascending node right ascension 15 and true anomaly angle 16) at the reference time obtained from the above formula are used as the scheduled injection The orbital parameters are input to the launch tool tracking and control device 21, as shown in FIG. 3. This information is transmitted from the launch tool tracking and control device 21 to the launch tool 23 in order to launch the artificial satellite 20 into a predetermined orbit. In the launch phase, when the launch tool 23 installed on the artificial satellite 20 is about to deviate from the predetermined orbit, the launch tool 23 will automatically correct the orbit, that is, the launch tool tracking and control device 21 will transmit the orbit correction command to the launch tool 23 to control the launch tool.

Even after the launch tool 23 reaches the predetermined launch orbit parameters, these orbit parameters are affected by the earth's gravitational field, the sun's moon gravitational force, and the perturbation of the solar window, and they always change short-term and long-term with the passage of time. In this case, the artificial satellite 20 needs to be controlled.

As shown in Fig. 4, usually, the six orbital parameters 31 of the orbit of the artificial satellite 20 are measured in such a way that the transmitting and receiving system 24 of the artificial satellite tracking and control device 18 receives the remote ranging signal 27 sent by the artificial satellite 20. , And extract the ranging signal 28 and send it to the range measuring system 25, and then the computer system 26 uses its orbit calculation program to calculate the measured range and its rate of change 29 as the final input. The computer system 26 uses its orbit control program 32 to compare the six orbit parameters 31 obtained with the six orbit parameters of the predetermined reference time, and calculate the necessary attitude control variables and orbit control variables 33. In this way, it is possible to calculate when and how long the gas injection device installed on the artificial satellite should inject which thruster. The command generation program 34 of the computer system 26 converts the calculation result into a control command 35, and the control command 35 is sent to the artificial satellite 20 through the transmission and reception system 24 of the artificial satellite tracking and control device 18.

As shown in FIG. 5, the communication system 37 installed on the artificial satellite 20 receives the control command transmitted to the artificial satellite 20, and then transmits it to the data processing system 38, where the transmission command is resolved. The attitude and orbit control system 39 installed on the artificial satellite appropriately processes the information of the attitude control variable and the orbit control variable 41 from the deciphered command, and operates the attitude control thruster 42 as needed to change the attitude of the artificial satellite 20. In addition, The gas injection device 40 of the artificial satellite equipped with the propulsion system is launched according to the command, and finally the artificial satellite 20 is injected and controlled on the orbit indicated by the 6 orbital parameters of the above-mentioned reference time. When the artificial satellite 20 is equipped with a GPS satellite receiver, the artificial satellite 20 itself pre-stores the 6 orbit parameters 17 of the preferred reference time at that moment, and automatically controls the orbit with the 6 orbit parameters 17 of the stored reference time.

As described above, the orbit parameter 17 calculated by the aforementioned formula is controlled and realized.

In addition, when multiple artificial satellites are arranged in orbits, it is necessary to appropriately control the individual orbits of the artificial satellites so that the orbits of the artificial satellites maintain a more harmonious orbital arrangement relationship.

The system to be described below uses a set of artificial satellites operating in orbits consistent with the present invention derived from the foregoing equations.

(4) System using artificial satellites operating in orbit according to the present invention (4-1) Example of system 1 An example of system 1 is a satellite broadcasting system.

Fig. 8 shows a specific example of a satellite broadcasting system according to the present invention.

The satellite broadcasting system shown in FIG. 8 includes: a group of artificial satellites 90, which have subsystems suitable for the elliptical orbit of the present invention, such as attitude control system, power supply system, communication system, thermal control system, etc.; base station 91, through artificial The satellite group 90 transmits satellite broadcasting; and the satellite broadcasting terminal 92 receives the satellite broadcasting through the artificial satellite group 90.

The base station 91 shown in FIG. 9 includes: an antenna 91a, an antenna guiding and tracking system 91b, a high-power amplifier 91c, a frequency converter 91d, a modulator 91e, an error correction encoder 91f, an encoder 91g, and a multiplexer 91h, Encoder 91i.

The image information 91k and the sound information 91l are efficiently encoded by the encoder 91i, and the other image and sound information and data 91j are multiplexed by the multiplexer 91h. In addition, they are encoded by the encoder 91g, and the error correction code is added by the error correction encoder 91f. In addition, they are modulated by the modulator 91e to be suitable for wireless communication, converted into a carrier wave by the frequency converter 91d, and amplified by the large electric power amplifier 91c, It is then transmitted from the antenna 91a, and the group of artificial satellites 90 is guided by the antenna guidance and tracking system 91b.

On the other hand, as shown in FIG. 10, the satellite broadcasting terminal 92 includes: an antenna 92a, a low noise amplifier 92b, a frequency converter 92c, a demodulator 92d, an error corrector 92e, a decoder 92f, a demultiplexer 92g, Decoder 92h, frame memory 92i.

The electromagnetic wave emitted by the satellite group 90 is received by the antenna 92a, amplified by the low noise amplifier 92b, converted into an intermediate frequency by the frequency converter 92c, and demodulated into a digital signal by the demodulator 92d. In addition, if there is an error in the digital signal, the error corrector 92e is corrected, the encrypted information is decrypted by the decoder 92f, and the demultiplexer 92g selects the desired broadcast. In addition, the signal is changed back to image information 92k and sound information 92l via the decoder 92h. The decoder 92h has a frame memory 92i so as to be able to compensate for the lack of data.

According to the present invention, even when the satellite broadcasting terminal 92 uses a directional antenna, the advantage is that it is only sufficient to orient it in the zenith direction, and the user does not need to search for the direction of the satellite group (north, south, east or west) at all.

In addition, in the case of broadcasting from a stationary satellite, the satellite broadcasting terminal antenna of the moving object needs to be symmetrical in direction and sensitive in the 45° direction. However, in the case of the present invention, since the antenna only needs to have directivity in the zenith direction, the advantage is that the antenna is easy to manufacture and the antenna gain can be increased by more than twice. Using this advantage, the satellite output power can be reduced by 1/2, that is, if the output power remains the same, the information (broadcast) that can be transmitted is twice the original.

In addition, since the artificial satellite group 90 is always located at a high elevation angle, no matter what the environment of the moving object, such as a place where a street with tall buildings is open only in the direction of the zenith, the electromagnetic waves of the artificial satellite 90 can be directly received. Therefore, it is possible to provide a high-quality receiving environment without reflecting waves from tall buildings, and the advantage is that compared with the case of geostationary satellite broadcasting, even if the same frequency band is used, more information (broadcasting) can be sent. The above effect can be demonstrated in the following system.

Hereinafter, referring to Figures 9 and 10, an example of adding an accounting system and broadcasting only to limited paying customers will be described.

As shown in FIG. 9, the accounting system 91m of the base station 91 includes: a restriction receiver 91n, a customer manager 91o, an accounting management system 91p, and a restriction reception module issuer 91q.

The satellite broadcasting terminal 92 includes a restricted receiving module 92m, as shown in FIG. 10.

Customer information (receiving status of the viewing fee, viewing request information, address, name, etc.) is managed by the customer manager 91o, and the accounting management system 91p controls each customer's data by controlling the encoder 91g through the restricted receiver 91n according to the customer information. password. In addition, the accounting management system 91p uses the restricted reception module issuer 91q to issue restricted reception modules (for example, IC cards) based on the customer information of the customer management system 91o. Although not mentioned here, the customer charging information of the financial institution is entered into the accounting management system 91p, and the customer information is updated with the customer manager 91o.

The user can receive the requested broadcast by inserting the above-mentioned restricted receiving module 92m obtained by payment into the decoder 92f of the satellite broadcasting terminal 92.

Therefore, by using the broadcasting program encryption device of the base station 91 and the decryption device of the satellite broadcasting terminal 92, it is possible to only broadcast to a limited satellite broadcasting terminal and charge a service fee.

Fig. 11 shows another specific example of a satellite broadcasting system.

The satellite broadcasting system shown in FIG. 11 includes: a group of artificial satellites 90, which have subsystems suitable for the elliptical orbit of the present invention, such as attitude control system, power supply system, communication system, thermal control system, etc.; The satellite group 90 transmits satellite broadcasting; the ground broadcasting station 93; and the satellite broadcasting terminal 94, which has a device for receiving satellite broadcasting through the artificial satellite group 90, and a device for receiving ground broadcasting.

As shown in FIG. 12, the terrestrial broadcasting station 93 includes an antenna 93a, a high-power amplifier 93b, a frequency converter 93c, a modulator 93d, an error correction encoder 93e, an encoder 93f, a multiplexer 93g, and an encoder 93h.

The image information 93j and the sound information 93k are efficiently encoded by the encoder 93h, and the other image and sound information and data 93i are multiplexed by the multiplexer 93g. In addition, they are encoded by the encoder 93f, and the error correction code is added by the error correction encoder 93e. In addition, they are modulated by the modulator 93d to be suitable for wireless communication, converted into a carrier wave by the frequency converter 93c, and amplified by the high electric power amplifier 93b. Then it transmits from the antenna 93a.

On the other hand, as shown in FIG. 13, the satellite broadcasting terminal 94 includes an antenna 94a1 and a low-noise amplifier 94b1 for receiving terrestrial broadcasting, an antenna 94a2 and a low-noise amplifier 94b2 for receiving electromagnetic waves from the artificial satellite group 90 Frequency converter 94c, demodulator 94d, error corrector 94e, decoder 94f, demultiplexer 94g, encoder 94h, frame memory 94i for ground station and satellite broadcasting.

The electromagnetic waves emitted by the terrestrial broadcasting station 93 are received by the antenna 94a1 and amplified by the low noise amplifier 94b1. On the other hand, the electromagnetic waves emitted by the satellite group 90 are received by the antenna 94a2 and amplified by the low noise amplifier 94b2. Each signal is received by a frequency converter. 94c is converted into an intermediate frequency, and demodulated into a digital signal by a demodulator 94d. In addition, if there is an error in the digital signal, the error corrector 94e is corrected, the encrypted information is decrypted by the decoder 94f, and the demultiplexer 94g selects the desired broadcast. In addition, the signal is changed back to image information 94k and sound information 94l via the decoder 94h. The decoder 94h has a frame memory 94i so as to be able to compensate for the lack of data.

Since the satellite broadcasting terminal 94 can not only receive terrestrial broadcasting but also satellite broadcasting, the advantage of the satellite broadcasting terminal 94 is that the user can freely select desired broadcasting programs. In addition, there is an advantage that if the user owns the satellite broadcasting terminal 94, he does not need to have both the satellite broadcasting terminal and the terrestrial broadcasting terminal. In addition, the antenna can be used as the antennas 94a1 and 94a2 at the same time.

The following will describe an example in which an accounting system is added and only broadcast to limited paying customers with reference to Figures 12 and 13.

As shown in FIG. 12, the accounting system 93m of the base station 93 includes: a restriction receiver 93n, a customer manager 93o, an accounting management system 93p, and a restriction receiving module issuer 93q.

The satellite broadcasting terminal 94 includes a restricted receiving module 94m, as shown in FIG. 13.

Customer information (receiving status of the viewing fee, viewing request information, address, name, etc.) is managed by the customer manager 93o, and the accounting management system 93p controls each customer's information by controlling the encoder 93f through the limit receiver 93n according to the customer information. password. In addition, the accounting management system 93p uses the restricted reception module issuer 93q to issue restricted reception modules (for example, IC cards) based on the customer information of the customer management system 93o. Although not mentioned here, the customer charging information of the financial institution is entered into the accounting management system 93p, and the customer information is updated with the customer manager 93o.

The user can receive the requested broadcast by inserting the above-mentioned restricted receiving module 92m obtained by payment into the decoder 94f of the satellite broadcasting terminal 94.

Therefore, by using the broadcasting program encryption device of the base station 93 and the decryption device of the satellite broadcasting terminal 94, it is possible to only broadcast to a limited satellite broadcasting terminal and charge a service fee.

Fig. 14 shows another specific example of a satellite broadcasting system.

The satellite broadcasting system shown in FIG. 14 includes: a group of artificial satellites 90, which have subsystems suitable for the elliptical orbit of the present invention, such as attitude control system, power supply system, communication system, thermal control system, etc.; ground communication device 95, Such as public networks, cellular phones, etc.; base station 96 having a device for transmitting satellite broadcasts through the artificial satellite group 90 and the above-mentioned ground communication device; and a satellite broadcasting terminal 97 having a device for receiving satellite broadcasts through the artificial satellite group 90 and the above-mentioned ground Communication device.

The base station 96 shown in FIG. 15 includes: an antenna 96a, an antenna guidance and tracking system 96b, a high-power amplifier 96c, a frequency converter 96d, a modulator 96e, an error correction encoder 96f, an encoder 96g, and a multiplexer 96h, Encoder 96i, data selector 96n, data storage 96o and ground communication network 95.

The request information 96m from the terrestrial communication network 95 is input to the data selector 96n, and the image information 96k, sound information 96l and data 96j are drawn from the data memory 96o if necessary. In addition, the image information 96k and the audio information 96i are efficiently encoded, and the other image and audio information and data 96j are multiplexed by the multiplexer 96h. In addition, they are encoded by the encoder 96g, and the error correction code is added by the error correction encoder 96f. In addition, they are modulated by the modulator 96e to be suitable for wireless communication, converted into a carrier wave by the frequency converter 96d, and amplified by the high power amplifier 96c, It is then transmitted from the antenna 96a, and the group of artificial satellites 90 is guided by the antenna guidance and tracking system 96b.

On the other hand, as shown in FIG. 16, the satellite broadcasting terminal 92 includes an antenna 97a, a low noise amplifier 97b, a frequency converter 97c, a demodulator 97d, an error corrector 97e, a decoder 97f, a demultiplexer 97g, The decoder 97h, the frame memory 97i, the transmitter 97n and the ground communication network 95 are required.

For example, PHS, cellular phone, etc. require 97m, which is sent by the request transmitter 97n to the base station 96 of FIG. 15 through the terrestrial communication network 95. The base station 96 sends the requested information to the group of artificial satellites 90. The electromagnetic waves emitted by the artificial satellite group 90 are received by the antenna 97a, amplified by the low-noise amplifier 97b, converted into the intermediate frequency by the frequency converter 97c, and demodulated into digital by the demodulator 97d. signal. In addition, errors in the digital signal are corrected by the error corrector 97e, the encrypted information is decrypted by the decoder 97f, and the demultiplexer 97g selects the desired broadcast. In addition, the signal is changed back to image information 97k and sound information 97l via the decoder 97h. The decoder 97h has a frame memory 97i so as to be able to compensate for the lack of data.

Therefore, the satellite broadcasting terminal 97 has an advantage that the user can send a request to the base station 91 in order to broadcast desired information.

The satellite broadcasting terminals 92, 94, 97 of the present invention can be installed on moving objects such as cars, trains, ships, aircrafts, etc., and can also be carried by pedestrians, climbers, and so on. Moreover, the satellite broadcasting terminal can also be used in non-mobile places such as homes.

The content of the broadcast program is not limited in the present invention.

Broadcasting programs include not only television broadcasting and sound broadcasting, but also digital information.

There are various programs broadcast, such as weather information, fishing information (water level, water temperature, etc.), ITS information [traffic volume information, traffic speed information, traffic jam location information, traffic jam time information, driving environment information, and affected area information , Traffic restriction information, optimal route information, congestion time information, parking lot status information, parking lot reservation information, destination information (weather, travel, sightseeing, dining, entertainment information), various reservation information (public transportation, Hotel, entertainment facilities)], map information (map information, update information, etc.), car navigation information (car navigation information, update information, etc.), software program information (car navigation program, competition program, OS, etc.), sound data (including Use MP3 compression, etc.), and entertainment information.

In addition, the programs broadcast also include Internet and other multimedia information and differential GPS information.

In addition, the broadcast programs also have information that is limited to a region or the area where the moving objects are moving, such as information about the business hours of shopping malls or supermarkets, information about art galleries and museum exhibitions, information about movie theaters or theater introductions, and information about criminals or miscellaneous personnel.

The following will describe an example in which an accounting system is added and only broadcast to limited paying customers with reference to Figs. 15 and 16.

As shown in FIG. 15, the accounting system 96p of the base station 96 includes a restriction receiver 96q, a customer manager 96r, an accounting management system 96s, and a restriction reception module issuer 96t.

The satellite broadcasting terminal 97 includes a restricted receiving module 97o, as shown in FIG. 16.

Customer information (receiving status of the viewing fee, viewing request information, address, name, etc.) is managed by the customer manager 96r. According to the customer information, the accounting management system 96s restricts the receiver 96q and controls the encoder 96g to control each customer's password. In addition, the accounting management system 96s uses the restricted reception module issuer 96t to issue restricted reception modules (for example, IC cards) based on the customer information of the customer management system 96r. Although not mentioned here, the customer charging information of the financial institution is input into the accounting management system 96s, and the customer information is updated with the customer manager 96r.

The user can receive the requested broadcast by inserting the above-mentioned restricted receiving module 97o obtained by payment into the decoder 97f of the satellite broadcasting terminal 97.

Therefore, by using the broadcasting program encryption device of the base station 96 and the decryption device of the satellite broadcasting terminal 97, it is possible to only broadcast to a limited satellite broadcasting terminal and charge a service fee.

(4-2) Example of System 2 An example of System 2 is a satellite broadcasting system.

Fig. 17 shows a specific example of a satellite communication system according to the present invention.

The satellite communication system shown in FIG. 17 includes: a group of artificial satellites 90, which have sub-systems suitable for the elliptical orbit of the present invention, such as attitude control systems, power supply systems, communication systems, thermal control systems, etc.; base stations 98 and artificial satellites The satellite group 90 is a satellite communication transmitting and receiving device 99 that performs satellite communication.

The base station 98 shown in FIG. 18 includes: an antenna 98a, an antenna guiding and tracking system 98b, a high-power amplifier 98c, a frequency converter 98d, a modulator 98e, an encoder 98f, a low noise amplifier 98h, a frequency converter 98i, and a demodulator 98j and Zemaji 98k.

The transmitted data 98g is encoded by the encoder 98f, encrypted, and error correction code is added. In addition, it is modulated by the modulator 98e to be suitable for wireless communication, converted into a carrier wave by the frequency converter 98d, amplified by the high-power amplifier 98c, and then sent from the antenna 98a. After launching, the antenna guiding and tracking system 98b is used to guide the group of artificial satellites 90. On the other hand, the electromagnetic waves emitted by the satellite group 90 are received by the antenna 98a, amplified by the low-noise amplifier 98h, converted into an intermediate frequency by the frequency converter 98i, and decoded into a digital signal by the demodulator 98j. In addition, after error correction, decryption and decoding by the decoder 98k, the received data 98l is obtained.

On the other hand, the satellite communication transmitting and receiving device 99 shown in FIG. 19 includes: an antenna 99a, a large electric power amplifier 99b, a frequency converter 99c, a modulator 99d, an encoder 99e, a low noise amplifier 99g, a frequency converter 99h, Demodulator 99i and decoder 99j.

The transmitted data 99f is encoded by the encoder 99e, encrypted, and error correction code is added. In addition, it is modulated by the modulator 99d to be suitable for wireless communication, converted into a carrier wave by the frequency converter 99c, amplified by the high-power amplifier 99b, and then sent from the antenna 99a Launch out. On the other hand, the electromagnetic waves emitted by the satellite group 90 are received by the antenna 99a, amplified by the low-noise amplifier 99g, converted into an intermediate frequency by the frequency converter 99h, and decoded into a digital signal by the demodulator 99i. In addition, the decoder 99j undergoes error correction, decryption and decoding to obtain received data 99k.

According to the present invention, since at least one of the artificial satellites in the group is visible in the vicinity of the zenith, by using the satellite communication system, even in areas where there are artificial buildings, trees, and mountains that block the view, the communication line is Can be easily maintained for a long time.

For example, by installing the base station 98 in the inter-network connection communication station of the public line, and allowing individuals to carry the satellite communication transmitting and receiving device 99, this satellite communication system can be used as a cellular phone.

For example, by installing the base station 98 in the hospital and installing the satellite communication transmitting and receiving device 99 on the ambulance, and sending image data about the patient from the ambulance to the hospital, medical experts in the hospital can communicate appropriate first aid measures, thereby Patients sent to the hospital by ambulance can receive appropriate treatment. Therefore, if the patient receives appropriate emergency treatment, it is possible to save his life.

For example, by installing the base station 98 in the broadcasting station and installing the satellite communication transmitting and receiving device 99 on the broadcasting vehicle, the satellite communication system can be used for the TV broadcasting of sports programs such as marathon relays, so that high-quality images can be transmitted in real time. Get dynamic programs.

For example, by installing the base station 98 in the fire station and installing the satellite communication transmitting and receiving device 99 on the fire truck, since the high-quality images of the fire fighting scene can be transmitted to the fire station from high buildings or narrow roads in real time, the fire station can make appropriate judgment.

For example, by installing the base station 98 in the police station and installing the satellite communication transmitting and receiving device 99 on the police patrol car, since high-quality images of criminals can be transmitted to the police station in real time, effective alert measures can be taken.

For example, by installing the base station 98 in a hospital with medical experts and installing the satellite communication transmitting and receiving device 99 on a mobile object, the mobile object listens to the clinical requirements, opinions or diagnosis of medical experts in remote places, and exchanges patient information. Information can also be transmitted in real time in mountainous areas, which can resolve regional differences in medical services.

For example, by installing the base station 98 in the stock center and the satellite communication transmitting and receiving device 99 on the vending machine, since the detailed catalog can be checked regularly or at will, customer service can be improved.

In addition, the satellite communication system can also be applied to train control information communication, train maintenance communication, train signal control communication, motor vehicle operation communication, ship information operation communication, data acquisition system (pontoons, pontoons, etc.), personal computer communication (e-mail) , Internet, online shopping, etc.), parking space information provision or reservation system, etc.

Fig. 20 shows still another specific example of a satellite communication system according to the present invention.

The satellite communication system shown in FIG. 20 includes: a group of artificial satellites 90 according to the present invention; a base station 98 for satellite communication through the artificial satellite group 90; a group of artificial satellites 100 including a global positioning measurement system; satellite communication transmission and The receiving device 101 has the function of measuring its own position using the positioning signals of the group of artificial satellites constituting the global positioning system, and also has the function of communicating through the group of artificial satellites 90.

The satellite communication transmitting and receiving device 101 shown in FIG. 21 includes: an antenna 101a, a high power amplifier 101b, a frequency converter 101c, a modulator 101d, an encoder 101e, a multiplexer 101f, a low noise amplifier 101h, and a frequency converter The device 101i, the demodulator 101k and the GPS receiver 101m.

The transmitted data 101g is multiplexed by the multiplexer 101f with the positioning information 101n sent by the GPS receiver 101m, encoded by the encoder 101e, encrypted, and error correction code is added. In addition, it is modulated by the modulator 101d to be suitable for wireless The communication is converted into a carrier wave by the frequency converter 101c, amplified by the high-power amplifier 101b, and then transmitted from the antenna 101a. On the other hand, the electromagnetic waves emitted by the satellite group 90 are received by the antenna 101a, amplified by the low-noise amplifier 101h, converted into an intermediate frequency by the frequency converter 101i, and decoded into a digital signal by the demodulator 101j. In addition, the decoder 101k obtains received data 101l after error correction, decryption, and decoding.

In this system, the positioning information of the transmitting and receiving devices can be sent to the base station.

In addition, regarding timing for sending positioning information, there are a request method (signal is transmitted only when the user requests it) and a polling method (the transmission request by the receiving center station, the transmission and receiving device automatically transmits the signal).

For example, by installing the base station 98 in a mountaineering search and rescue center such as a police station or a fire station, and allowing the mountaineer to carry the satellite communication transmitting and receiving device 101, if the mountaineer is in danger, the rescue activity can be carried out quickly and accurately, because the center can Learn about the position of the mountaineer. In addition, due to the two-way communication capability, the present invention has an advantage that it can encourage mountaineers in distress with language and can confirm whether the information is wrong. In addition, in order to reduce weight and power consumption, the satellite communication transmitting and receiving device may only have a transmitting function.

For example, by installing the base station 98 in a maritime search and rescue center such as a police station or a fire station, and installing a satellite communication transmitting and receiving device 101 on a ship, it is possible to perform an error check and quickly and accurately perform rescue operations, because if the ship In the event of a wreck, the center and the Maritime Safety Bureau can learn the location of the wrecked vessel. In addition, due to the two-way communication capability, the present invention has an advantage in that words can be used to encourage the crew of the wrecked ship and can confirm whether the information is wrong. In addition, in order to reduce weight and power consumption, the satellite communication transmitting and receiving device may only have a transmitting function.

For example, by installing the base station 98 in a police station and letting an individual carry the satellite communication transmitting and receiving device 101, if the person wanders or gets lost, rescue activities can be carried out quickly and accurately because the police station can detect the person's location. In addition, due to the two-way communication capability, the present invention has an advantage that it can encourage mountaineers in distress with language and can confirm whether the information is wrong. In addition, in order to reduce weight and power consumption, the satellite communication transmitting and receiving device may only have a transmitting function.

For example, by installing the base station 98 in the police station and installing the satellite communication transmitting and receiving device 101 on the vehicle, if the vehicle is stolen, the search can be carried out quickly and accurately, because the police station can detect the stolen vehicle s position.

For example, by installing the base station 98 in the material distribution center, and installing the satellite communication transmitting and receiving device 101 on the moving objects (truck, train, taxi, bus, container), the material distribution management can be carried out quickly and accurately. Arrange management with moving objects, because the center can instantly detect the location of moving objects.

In addition, the satellite communication system can also be applied to the most suitable channel guidance system, on-demand navigation system, animal behavior monitoring [wild animals (behavior monitoring), cattle herd (prevention of getting lost, exercise detection), zoo animals (danger prevention), etc. ].

Fig. 22 shows still another specific example of a satellite communication system according to the present invention.

The satellite communication system shown in FIG. 22 includes: a group of artificial satellites 90, which have subsystems suitable for the elliptical orbit of the present invention, such as attitude control system, power supply system, communication system, thermal control system, etc.; through the artificial satellite group 90 A base station 98 for satellite communication; and a satellite communication transmitting and receiving device 102, which have the function of measuring at least one of the consumption of electricity, urban gas, and urban water, and can communicate through the artificial satellite group 90.

In the case of measuring electrical consumption, the satellite communication transmitting and receiving device 102 includes: an antenna 102a, a high-power amplifier 102b, a frequency converter 102c, a modulator 102d, an encoder 102e, a multiplexer 102f, and a low-noise amplifier 102h, The frequency converter 102i, the demodulator 102j, the decoder 102k and the electric power meter 102m are as shown in FIG. 23.

The transmission data 102g is multiplexed by the multiplexer 102f with the consumption information 102n output by the electric power meter 102m, encoded by the encoder 102e, encrypted, and error correction code is added. In addition, it is modulated by the modulator 102d to be suitable for wireless The communication is converted into a carrier wave by the frequency converter 102c, amplified by the high-power amplifier 102b, and then transmitted from the antenna 102a. On the other hand, the electromagnetic waves emitted by the satellite group 90 are received by the antenna 102a, amplified by the low-noise amplifier 102h, converted into an intermediate frequency by the frequency converter 102i, and decoded into a digital signal by the demodulator 102j. In addition, the decoder 102k obtains received data 1021 after error correction, decryption, and decoding.

In this system, the total power consumption measured by the satellite communication transmitting and receiving device 102 can be calculated at the base station 98. In addition, public service fees such as electricity, city gas, and water are collected door-to-door. However, by using artificial satellites operating in orbit according to the present invention, the total amount of public service charges can be calculated through satellites. This is because as long as the satellite communication transmitting and receiving device 102 is installed, even residents surrounded by tall buildings or have no communication In a mountainous area of the facility, satellite communication lines are also easy to guarantee. Therefore, the personnel expenditure required to count the consumption can be greatly reduced. As a result of reduced personnel expenses, it can be expected that public service costs can be further reduced.

Fig. 24 shows another specific example of a satellite communication system.

The satellite communication system shown in FIG. 24 includes: a group of artificial satellites 90, which have subsystems suitable for the elliptical orbit of the present invention, such as attitude control system, power supply system, communication system, thermal control system, etc.; through the artificial satellite group 90 The base station 98 for satellite communication; and the satellite communication transmitting and receiving device 103, which have the function of collecting and rebroadcasting information in the information network, and can also communicate through the artificial satellite group 90.

As shown in FIG. 25, the satellite communication transmitting and receiving device 103 includes: an antenna 103a, a large electric power amplifier 103b, a frequency converter 103c, a modulator 103d, an encoder 103e, a multiplexer 103f, a low noise amplifier 103h, and a frequency converter The device 103i, the demodulator 103j, the decoder 103k, the demultiplexer 1031 and the network 103n.

The transmitted data 103g is multiplexed by the multiplexer 103f with the consumption network information 10301 output by the network 103n, encoded by the encoder 103e, encrypted, and error correction code is added, and is modulated by the modulator 103d to be suitable for wireless communication It is converted into a carrier wave by the frequency converter 103c, amplified by the high-power amplifier 103b, and then emitted from the antenna 103a. On the other hand, the electromagnetic wave emitted by the artificial satellite group 90 is received by the antenna 103a, amplified by the low noise amplifier 103h, converted into an intermediate frequency by the frequency converter 103i, and decoded into a digital signal by the demodulator 103j. In addition, after error correction, decryption and decoding by the decoder 103k, the received data 103m and the network information 103o2 input to the network are obtained.

In this system, network information such as office or home network information (security, utility status/use value and utility utilization) can be communicated between the satellite communication transmitting and receiving device 103 and the base station 98. In addition, by using the artificial satellite operating in orbit according to the present invention, the antenna device is installed in the residents surrounded by high-rise buildings, and the satellite communication line can be easily ensured. In addition, in the case of security information, there is an advantage that even if the telephone line is cut, the contact (report) method can be independently guaranteed via satellite.

Fig. 26 shows still another specific example of a satellite communication system.

The satellite communication system shown in FIG. 26 includes: a group of artificial satellites 90, which have subsystems suitable for the elliptical orbit of the present invention, such as attitude control system, power supply system, communication system, thermal control system, etc.; through the artificial satellite group 90 The base station 98 for satellite communication; and the satellite communication transmitting and receiving device 104, which have the function of monitoring the environment, and can also communicate through the artificial satellite group 90.

As shown in FIG. 27, the satellite communication transmitting and receiving device 104 includes: an antenna 104a, a large electric power amplifier 104b, a frequency converter 104c, a modulator 104d, an encoder 104e, a multiplexer 104f, a low noise amplifier 104h, and a frequency conversion The detector 104i, the demodulator 104j, the decoder 104k and the detector 104m. The transmission data 104g is multiplexed by the multiplexer 104f with the measurement information 104n output by the detector 104m, and is encoded by the encoder 104e, encrypted, and error correction code is added. In addition, it is modulated by the modulator 104d to be suitable for wireless communication. It is converted into a carrier wave by the frequency converter 104c, amplified by the high-power amplifier 104b, and then emitted from the antenna 104a. On the other hand, the electromagnetic waves emitted by the satellite group 90 are received by the antenna 104a, amplified by the low-noise amplifier 104h, converted into an intermediate frequency by the frequency converter 104i, and decoded into a digital signal by the demodulator 104j. In addition, after error correction, decryption and decoding by the decoder 104k, the received data 1041 is obtained.

By using the artificial satellite operating in orbit according to the present invention, it is possible to easily communicate in places surrounded by tall buildings or in mountainous areas without any communication facilities. Therefore, since it is easy to collect environmental data (weather information, water levels (river, lake, etc.), earthquakes, volcanoes, carbon monoxide, nitrogen oxides, sulfur dioxide, dioxide, etc.) in a wide area, for example, by connecting the base station 98 Installed in the environmental center, and placed the satellite communication transmitting and receiving device 104 with the function of monitoring the environment in different areas, a quick and accurate way to solve the problem can be designed to protect the residents and the environment in the area. And since there are almost no restrictions on the installation location of the satellite communication transmitting and receiving device 104, the expenditure required to collect environmental data can be greatly reduced. In addition, there are emergency communication methods (sending when the environmental data value exceeds a predetermined limit value) and round-robin detection methods (when receiving a request from a central station, the transmitting and receiving devices automatically send the information) with regard to the timing of sending environmental information.

Fig. 28 shows still another specific example of a satellite communication system.

The satellite communication system shown in FIG. 28 includes: a group of artificial satellites 90, which have subsystems suitable for the elliptical orbit of the present invention, such as attitude control system, power supply system, communication system, thermal control system, etc.; through the artificial satellite group 90 The base station 98 for satellite communication; and the satellite communication transmitting and receiving device 105, which have the function of detecting and monitoring abnormal conditions, and can communicate through the artificial satellite group 90.

As shown in Fig. 29, the satellite communication transmitting and receiving device 105 includes: an antenna 104a, a high power amplifier 105b, a frequency converter 105c, a modulator 105d, an encoder 105e, a multiplexer 105f, a low noise amplifier 105h, and a frequency conversion The detector 105i, the demodulator 105j, the decoder 105k and the detector 105m.

The transmission data 105g is multiplexed by the multiplexer 105f with the abnormal detection information 105n output by the detector 105m, and is encoded by the encoder 105e, encrypted and error correction code is added. In addition, it is modulated by the modulator 105d to be suitable for wireless The communication is converted into a carrier wave by the frequency converter 105c, amplified by the high-power amplifier 105b, and then transmitted from the antenna 105a. On the other hand, the electromagnetic waves emitted by the satellite group 90 are received by the antenna 105a, amplified by the low noise amplifier 105h, converted into an intermediate frequency by the frequency converter 105i, and decoded into a digital signal by the demodulator 105j. In addition, the decoder 105k obtains received data 105l after error correction, decryption, and coding.

In this system, an emergency signal can be automatically generated when an abnormal situation occurs. For example, the base station 98 is installed in the fire station, and the satellite communication transmitting and receiving device 105, which has the function of monitoring the abnormal conditions of the vehicle such as large collision or airbag operation, is placed on the vehicle. When a traffic accident occurs, the fire station and insurance company can automatically know An abnormal situation occurred, and rescue activities for the driver and passengers were quickly carried out.

For example, the base station 98 is installed in the Maritime Safety Administration, and the satellite communication transmitting and receiving device 105, which has the function of monitoring abnormal conditions of vehicles such as water ingress or excessive collisions, is installed on the ship. The Maritime Safety Administration can automatically learn when a ship accident occurs. Thus the crew and passengers can be rescued safely.

Fig. 30 shows another specific example of a satellite communication system.

The satellite communication system shown in FIG. 30 includes: a group of artificial satellites 90, which have subsystems suitable for the elliptical orbit of the present invention, such as attitude control system, power supply system, communication system, thermal control system, etc.; through the artificial satellite group 90 A base station 98 for satellite communication; and a satellite communication transmitting and receiving device 108, which has the function of receiving traffic information 107 such as VICS sent by the traffic information publishing system 106, and can communicate through the artificial satellite group 90; and a ground communication network 95, It sends the request of the satellite communication transmitting and receiving device 108 to the traffic information issuing system 106 via the base station 98.

As shown in FIG. 30, the base station 98 uses the received signal obtained from the satellite communication transmitting and receiving device 108 as a user request, and sends it to the traffic information issuing system 106 via the ground communication network 95. In addition, the information sent by the traffic information release system 106 is sent to the user as transmission data.

As shown in FIG. 31, the traffic information release system 106 includes: an antenna 106a, a high-power amplifier 106b, a frequency converter 106c, a modulator 106d, an error correction encoder 106e, an encoder 106f, a multiplexer 106g, and a data selector 106i, data storage 106j and ground communication network 95.

The request information 106k via the terrestrial communication network 95 is input to the data selector 106i, and the traffic information 106h is extracted from the data storage 106j if necessary. In addition, the traffic information 106h is multiplexed by the multiplexer 106g, encoded by the encoder 106f, error correction code is added by the error correction encoder 106e, and modulated by the modulator 106d to be suitable for wireless communication. The converter 106c converts it into a carrier wave, which is amplified by the high-power amplifier 106b, and then radiated from the antenna 106a.

On the other hand, as shown in FIG. 32, the satellite communication transmitting and receiving device 108 includes: an antenna 108a, a high power amplifier 108b, a frequency converter 108c, a demodulator 108d, an encoder 108e, a low noise amplifier 108g, and a frequency converter 108h , Demodulator 108i, decoder 108j, traffic information antenna 108n, traffic information receiver 108m and car navigator 108l.

The user request 108f is encoded by the encoder 108e, encrypted and added with an error correction code. In addition, it is modulated by the modulator 108d to be suitable for wireless communication, converted into a carrier wave by the frequency converter 108c, amplified by the high-power amplifier 108b, and then sent from the antenna 108a Launch out. On the other hand, the electromagnetic waves emitted by the satellite group 90 are received by the antenna 108a, amplified by the low-noise amplifier 108g, converted into an intermediate frequency by the frequency converter 108h, and decoded into a digital signal by the demodulator 108i. In addition, after error correction, decryption and decoding by the decoder 108j, the traffic information as the received data 108k is obtained and output to the car navigator 108l.

In this system, the driver can receive traffic information 107 such as VICS, and can also request the required traffic information from the satellite communication transmitting and receiving device 108 through the base station and a group of satellites 90, and through the traffic information release system 106 and a group of satellites. All satellites 90 can obtain information. Therefore, the driver can obtain detailed and timely traffic information.

The traffic information includes the following information.

That is, ITS information [traffic volume information, traffic speed information, traffic congestion location information, traffic congestion time information, driving environment information, affected area information, traffic restriction information, optimal route information, congestion time information, parking lot conditions Information, parking lot reservation information, destination information (weather, travel, sightseeing, dining, entertainment information), various reservation information (public transportation, hotels, entertainment facilities)], map information (map information, update information, etc.), cars Navigation information (car navigation information, update information, etc.), software program information (car navigation program, race program, OS, etc.).

(4-3) System example 3 System example 3 is an inter-satellite communication system.

Fig. 33 shows a specific example of the inter-satellite communication system according to the present invention.

The inter-satellite communication system shown in FIG. 33 includes: a group of artificial satellites 90, which have subsystems suitable for the elliptical orbit of the present invention, such as attitude control system, power supply system, communication system, thermal control system, etc.; through the artificial satellite group 90 is a base station 98 for satellite communication; a satellite communication transmitting and receiving device 110 and a set of artificial satellites 109, all of which can communicate through a set of artificial satellites 90.

In this system, if a group of artificial satellites 109 are in an operating range such that the group of artificial satellites 109 cannot directly communicate with the satellite communication transmitting and receiving device 110 or the base station 98, but can communicate with a group of artificial satellites 90, The information of a group of artificial satellites 109 can be obtained through a group of artificial satellites 90. Therefore, this system can obtain information of a wider area from a group of artificial satellites 109.

For example, when the artificial satellite 109 is equipped with an earth surveying device, the base station and the satellite communication transmitting and receiving device 110 can receive the measurement data, and can request the required measurement data. Therefore, this system can obtain the required measurement data in a wider area.

(4-4) System example 4 System example 4 is an earth survey system.

Fig. 34 shows a specific example of the earth survey system according to the present invention.

The earth survey system shown in Figure 34 includes: a set of artificial satellites 111, which have subsystems suitable for the elliptical orbit of the present invention, such as attitude control systems, power supply systems, communication systems, thermal control systems, etc.; and base stations 98, To receive the measurement results transmitted by a group of artificial satellites 111.

In this system, since the orbit of a group of artificial satellites 111 is at a high elevation angle relative to the ground, the earth survey information that is not affected by obscured objects can be collected by the base station 98.

Finally, referring to Figures 63-66, a brief description of satellite services in some countries.

(1) The contour line shown in Figure 63 is an example of the simulation result of the visible service time ratio (%) of any artificial satellite at an elevation angle of 70° or more. In the UK, if 3 artificial satellites are used to provide 24 hours a day service , Its orbital inclination is 60°, the eccentricity is 0.3, and the argument of perigee is 270°.

In the United Kingdom, as for the combined parameters of the orbital inclination and eccentricity when using 4 artificial satellites, the orbital inclination is between 55° and 65°, and the eccentricity is between 0.25 and 0.35.

In addition, the contour line shown in Figure 64 is an example of the simulation result of the visible service time ratio (%) of any artificial satellite at an elevation angle of 70° or more. In the United Kingdom, if 4 artificial satellites are used to provide 24 hours a day service, The orbital inclination is 60°, the eccentricity is 0.25, and the argument of perigee is 270°.

In the United Kingdom, as for the combined parameters of the orbital inclination and eccentricity when using 4 satellites, the orbital inclination is between 50° and 65°, and the eccentricity is between 0.15 and 0.35.

(2) The contour line shown in Fig. 65 is an example of the simulation result of the visible service time ratio (%) of any artificial satellite at an elevation angle of 70° or more. In the major countries of the European Community, if 3 artificial satellites are used to provide 24 per day Hourly all-weather service, with an orbital inclination of 50°, an eccentricity of 0.25, and an argument of perigee of 270°.

In the main countries of the European Community, as for the combined parameters of the orbital inclination and eccentricity when using 4 artificial satellites, the orbital inclination is between 45° and 55°, and the eccentricity is between 0.15 and 0.3.

(3) The contour line shown in Figure 66 is an example of the simulation result of the visible service time ratio (%) of any artificial satellite at an elevation angle of 70° or more. In New Zealand, if 3 artificial satellites are used to provide 24 hours a day service , The orbital inclination is 50°, the eccentricity is 0.3, and the argument of perigee is 90°.

In New Zealand, as for the combined parameters of the orbital inclination and eccentricity when using 4 artificial satellites, the orbital inclination is between 45° and 55°, and the eccentricity is between 0.25 and 0.35.

The results of the present invention are as follows.

(1) Regarding the results of the method of setting the argument of perigee. According to the present invention, regarding an elliptical orbit with any orbital inclination, the change in the argument of perigee can be considered in advance when setting the orbital parameters. This change is caused by the influence of the earth's gravity field. of.

(2) Regarding the results of the method of arranging multiple artificial satellites orbits. According to the present invention, any artificial satellites are used to intensively and continuously perform communication services or broadcast services in a designated area around which orbiting celestial bodies, or any artificial satellites are used. In the case of centralized and continuous monitoring of designated areas of its orbiting celestial bodies or centralized and continuous service of weather in designated areas, it is easy to set semi-major axis, eccentricity, orbital inclination, argument of perigee, and ascending node The six man-made satellite orbit parameters, right ascension and true anomaly.

In addition, according to the present invention, any artificial satellite can be used to centrally and continuously perform communication services or broadcast services in designated areas where the artificial satellites orbit celestial bodies.

In addition, according to the present invention, any artificial satellite can be used to centrally and continuously monitor the designated area where the artificial satellite orbits the celestial body or to provide concentrated and continuous service to the weather in the designated area.

(3) With regard to the orbital parameters, the results of the arrangement of multiple artificial satellites obtained from the above items (1) and (2). According to the present invention, the technical requirements for the satellite communication transmitting and receiving devices set up due to the short reach of electromagnetic waves can be Moderate relaxation, and can establish a communication system with a short communication delay time.

In addition, according to the present invention, since the orbit is close to a circular shape, it is possible to shorten the communication and broadcast failure time that occurs during the service switching time between multiple artificial satellites.

In addition, according to the present invention, due to the use of 3 or 4 artificial satellites, the arrangement of the artificial satellites allows any one of them to be visible at the same time from the Nemuro to the Japanese territory of Naha from an elevation angle greater than 70°. These artificial satellites can be used very well. Easily communicate and broadcast services to mobile objects.

(4) Common results of the above items (1) to (3) According to the present invention, it is possible to provide an orbit control system that controls the orbit of an artificial satellite based on the orbit parameters set by the above method.