Satellite, satellite control method and satellite communication system

• US 6,352,222 B1
• Filed: 05/20/1998
• Issued: 03/05/2002
• Est. Priority Date: 05/21/1997
• Status: Expired due to Fees

• Current Assignee: Hitachi, Ltd.
• Original Assignee: Hitachi, Ltd.
• Inventors: Ito, Masahiro, Nakamura, Shigeki, Ikeda, Masahiko, Yabutani, Takashi, Maeda, Toshihide, Owada, Masataka, Hamano, Nobuo, Yoshida, Tomiharu
• Primary Examiner(s): ELDRED, JOHN W
• Application Number:
  US09/081,551
• Time in Patent Office: 1,385 Days
• Field of Search: 244/158.R, 455/427, 455/429, 455/430
• US Class Current: 244/158.8
• CPC Class Codes: B64G 1/1007 Communications satellites
• CPC Class Codes: B64G 1/1085 Swarms and constellations
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: H04B 7/18539 Arrangements for managing radio, resources, i.e. for establishing or releasing a connection

Abstract

In order to establish the communication lines among the movable bodies and/or fixed stations and to configure communication system with a small number of satellites, present method has the steps of determining six orbit-related parameters by using a input conditions including a geographical condition of the service area, a desired service time and the tolerance of an ascending vertical angle within which the satellite can be viewed from the service area, and establishing the satellite communication with one or more satellites, an individual satellite being arranged on the orbits selected and combined among plural elliptical orbits corresponding to the determined six orbit-related parameters on which the satellites stay for a sufficiently long time that they may come successfully into sight in the zenith direction.

Claims

1. An artificial satellite traveling on an elliptical orbit, in which said elliptical orbit is defined by six orbit-related parameters obtained with input conditions including the geographical condition of the service area to be covered by the artificial satellite, a minimum operational elevational angle within which the artificial satellite can be viewed from the service area, and a reference time for defining the orbit parameters.

2. An artificial satellite traveling on an elliptical orbit according to claim 1, wherein said six orbit-related parameters are determined by steps including the step of setting a semi-major axis and perigee arguments, the step of setting a semi-vertical angle, a desired service time, and a polygon including the service area, the step of setting a number of artificial satellites, the right ascension of a north-bound node of an individual artificial satellite and a true anomaly of the individual artificial satellite, the step of setting an initial value for the orbital inclination angle, the step of calculating a duration time for the artificial satellite coming into sight from the individual apex of the polygon, the step of setting the combination of an orbital inclination angle and the eccentricity squared, and the step of resetting the right ascension of a north-bound node and true anomaly of an individual artificial satellite.

5. An orbit control system for controlling an orbit of an artificial satellite, comprising:

satellite operation control equipment for obtaining the orbit of satellite, obtaining necessary attitude and orbit controlled variables from the obtained orbit and a predetermined target control value, and making a control command corresponding to these controlled variables and sending it to said satellite,

wherein said satellite is the artificial satellite described in claim 1.

6. A satellite communication system for conducting satellite communications via an artificial satellite, comprising at least an artificial satellite, a satellite communication terminal for conducting satellite communications via an artificial satellite, a gateway communication station for conducting satellite communications via an artificial satellite, a telephone terminal connected to the gateway communication station via a telephone network;

wherein said satellite is the artificial satellite described in claim 1, and

in the case wherein said satellite is used within a target service area said satellite communication station has a send/receive means for sending and receiving signals with the satellite coming in sight within a predetermined range of elevation angle extended in the zenith direction.

7. An earth observation system comprising an artificial satellite in which an earth observation apparatus is installed, and an observation earth station for receiving the result of observation transmitted from the satellite, wherein said satellite is the artificial satellite described in claim 1.

12. An artificial satellite according to claim 1, wherein said satellite travels on such an oblong orbit that the artificial satellite may come in sight at an angle larger than the maximum elevation angle with which a geostationary artificial satellite is viewed from the service area corresponding to the artificial satellite.

13. An artificial satellite traveling on an elliptical orbit according to claim 1, wherein the artificial satellite has an elliptical orbit with a cycle of substantially 24 hours.

14. An artificial satellite traveling on an elliptical orbit according to claim 1, wherein the minimum operational elevational angle within which the artificial satellite can be viewed from the service area is at least 55°

.

15. An artificial satellite traveling on an elliptical orbit according to claim 14, wherein the minimum operational elevational angle is about 70°

.

16. An artificial satellite traveling on an elliptical orbit according to claim 1, wherein the reference time for defining the orbit parameters includes an instantaneous time and a time of duration for which the artificial satellite can be viewed from the service area.

17. An artificial satellite traveling on an elliptical orbit according to claim 1, wherein a plurality of artificial satellites are provided, each of the artificial satellites traveling on the elliptical orbit with a cycle of substantially 24 hours, and each of the artificial satellites being viewed from the service area at a time different from one another such that the artificial satellites do not provide substantially simultaneous coverage of the service area.

18. An artificial satellite traveling on an elliptical orbit according to claim 1, wherein the artificial satellite has an inclination angle of less than 60°

.

19. An artificial satellite traveling on an elliptical orbit according to claim 1, wherein the geographical condition of the service area includes latitude, longitude and elevation of points delimiting a polygon encompassing the service area.

20. An artificial satellite traveling on an elliptical orbit according to claim 19, wherein the geographical condition of the service area further includes artificial building structures, plants and natural topographic features, and the minimum operational elevational angle is an angle sufficient for the artificial satellite to be viewed from the service area without being blocked or shielded by the geographical condition of the service area.

21. An artificial satellite traveling on an elliptical orbit according to claim 1, wherein the geographical condition of the service area further includes artificial building structures, plants and natural topographic features, and the minimum operational elevational angle is an angle sufficient for the artificial satellite to be viewed from the service area without being blocked or shielded by the geographical condition of the service area.

3. A group of artificial satellites traveling on an elliptical orbit, wherein six orbit-related parameters of the elliptical orbits of the individual artificial satellites are obtained with input conditions including a geographical condition of the service area to be covered by the artificial satellites, a minimum operational elevational angle within which any one of the group of artificial satellites can be viewed from the service area, and a reference time for defining the orbit parameters, and

wherein one or more artificial satellites are arranged on individual orbital planes within a predetermined range of the minimum operational elevational angle viewed in the zenith direction from the service area by combining plural elliptical orbits so that at least one or more artificial satellites can always come in sight.

4. A group of artificial satellites traveling on an elliptical orbit according to claim 3,

wherein said satellite group comprises two satellites, located in orbits on different orbital planes,

wherein each of said orbits is formed so that the orbit cycle is substantially 24 hours, the eccentricity squared is between 0.24 and 0.38, the orbital inclination angle is between 47 degrees and 52 degrees or between 128 degrees and 133 degrees, and the argument of perigee is 270 degrees, and

wherein said satellites are arranged so that their right ascensions of a north-bound node may be shifted by 180 degrees, and one is arranged to be located at the apogee on the orbit while the other is located at the perigee on the orbit.

22. A group of artificial satellites traveling on an elliptical orbit according to claim 3, wherein each the artificial satellites has an elliptical orbit with a cycle of substantially 24 hours.

23. A group of artificial satellites traveling on an elliptical orbit according to claim 3, wherein the minimum operational elevational angle within which each of the artificial satellites can be viewed from the service area is at least 55°

.

24. A group of artificial satellites traveling on an elliptical orbit according to claim 23, wherein the minimum operational elevational angle is about 70°

.

25. A group of artificial satellites traveling on an elliptical orbit according to claim 3, wherein the reference time for defining the orbit parameters includes an instantaneous time and a time of duration for which each of the artificial satellites can be viewed from the service area.

26. A group of artificial satellites traveling on an elliptical orbit according to claim 3, wherein each of the artificial satellites travel on the elliptical orbit with a cycle of substantially 24 hours, and each of the artificial satellites being viewed from the service area at a time different from one another such that the artificial satellites do not provide substantially simultaneous coverage of the service area.

27. A group of artificial satellites traveling on an elliptical orbit according to claim 3, wherein each of the artificial satellites has an inclination angle of less than 60°

.

28. A group of artificial satellites traveling on an elliptical orbit according to claim 3, wherein the geographical condition of the service area includes latitude, longitude and elevation of points delimiting a polygon encompassing the service area.

29. A group of artificial satellites traveling on an elliptical orbit according to claim 28, wherein the geographical condition of the service area further includes artificial building structures, plants and natural topographic features, and the minimum operational elevational angle is an angle sufficient for the artificial satellite to be viewed from the service area without being blocked or shielded by the geographical condition of the service area.

30. A group of artificial satellites traveling on an elliptical orbit according to claim 3, wherein the geographical condition of the service area further includes artificial building structures, plants and natural topographic features, and the minimum operational elevational angle is an angle sufficient for the artificial satellite to be viewed from the service area without being blocked or shielded by the geographical condition of the service area.

8. A method of determining six orbit-related parameters of an artificial satellite traveling on an elliptical orbit, wherein said six orbit-related parameters of the elliptical orbit of the artificial satellite are obtained with input conditions including a geographical condition of a service area to be covered by the artificial satellites, a minimum operational elevational angle within which any one of the group of artificial satellites can be viewed from the service area, and a reference time defining orbit parameter.

9. A method of determining six orbit-related parameters according to claim 8, comprising the steps of:

setting a polygon including a semi-major axis, a perigee argument, a semi-vertical angle, a service time and a service area,

setting a number of satellites and a right ascension of a north-bound node and true anomaly of an individual satellite,

setting an initial value for an orbital inclination angle,

calculating a duration time for a satellite coming into sight from each apex of the polygon,

setting a combination of orbital inclination angle and eccentricity squared, and

resetting the right ascension of the north-bound node and true anomaly of the individual satellite.

31. A method according to claim 8, wherein the geographical condition of the service area includes latitude, longitude and elevation of points delimiting a polygon encompassing the service area.

32. A method according to claim 31, wherein the geographical condition of the service area further includes artificial building structures, plants and natural topographic features, and the minimum operational elevational angle is an angle sufficient for the artificial satellite to be viewed from the service area without being blocked or shielded by the geographical condition of the service area.

33. A method according to claim 8, wherein the geographical condition of the service area further includes artificial building structures, plants and natural topographic features, and the minimum operational elevational angle is an angle sufficient for the artificial satellite to be viewed from the service area without being blocked or shielded by the geographical condition of the service area.

10. A method of arranging a plurality of artificial satellites traveling on elliptical orbits,

wherein six orbit-related parameteres of the elliptical orbits of the individual artificial satellites are obtained with input conditions including a geographical condition of a service area to be covered by the artificial satellites, a minimum operational elevational angle within which any one of the group of artificial satellites can be viewed from the service area, and a reference time defining the orbit parameters, and

wherein in the case where plural artificial satellites are arranged, one of more artificial satellites may be arranged on individual orbital planes within a predetermined range of the minimum operational elevational angle as viewed in the zenith direction from the service area by combining plural elliptical orbits so that at least one or more artificial satellites can always come in sight.

34. A method according to claim 10, wherein the geographical condition of the service area includes latitude, longitude and elevation of points delimiting a polygon encompassing the service area.

35. A method according to claim 34, wherein the geographical condition of the service area further includes artificial building structures, plants and natural topographic features, and the minimum operational elevational angle is an angle sufficient for the artificial satellite to be viewed from the service area without being blocked or shielded by the geographical condition of the service area.

36. A method according to claim 10, wherein the geographical condition of the service area further includes artificial building structures, plants and natural topographic features, and the minimum operational elevational angle is an angle sufficient for the artificial satellite to be viewed from the service area without being blocked or shielded by the geographical condition of the service area.

11. A method of determining six orbit-related parameters of artificial parameters, comprising the steps of:

setting a polygon including a semi-major axis, a perigee argument, a semi-vertical angle, a service time and a service area,

setting a number of satellites and a right ascension of a north-bound node and true anomaly of the individual satellites,

setting an initial value for an orbital inclination angle,

calculating a duration time for a satellite coming into sight from each apex of the polygon,

setting a combination of orbital inclination angle and eccentricity squared, and

resetting the right ascension of a north-bound node and true anomaly of the individual satellite.