Apogee at constant time-of-day equatorial (ACE) orbit

• US 5,326,054 A
• Filed: 01/21/1988
• Issued: 07/05/1994
• Est. Priority Date: 10/06/1986
• Status: Expired due to Term

• Current Assignee: Space Systems/Loral Incorporated (Loral Space and Communications Incorporated)
• Original Assignee: Space Systems/Loral Incorporated (Loral Space and Communications Incorporated)
• Inventors: Turner, Andrew E.
• Primary Examiner(s): Gregory, Bernarr E.
• Application Number:
  US07/146,651
• Time in Patent Office: 2,357 Days
• Field of Search: 342/356, 342/352-355, 342/357-358, 244/158 R, 244/164, 455/13, 364/459
• US Class Current: 244/158.4
• CPC Class Codes: B64G 1/1007 Communications satellites
• CPC Class Codes: B64G 1/242 Orbits and trajectories

Abstract

A man-made satellite (1) traveling in an elliptical orbit. The orbit has five or six daily apogees, which are positioned above the same longitudes of the earth at substantially the same local time-of-day for each day of the year. The longitudes and times-of-day can be preselected subject only to the proviso that they be equispaced. The apsidal rotation rate in inertial space (ARRIS) of the orbit is substantially equal to the mean rate at which the earth revolves about the sun. The orbit is preferably equatorial, in order to simplify ground tracking and to maximize the impact of the apsidal rotation.

Claims

1. A man-made satellite that is made to travel in an elliptical orbit about the earth, wherein:

the satellite revolves about the earth a discrete number of times per day;

each of the apogees corresponding to the daily revolutions is positioned over the same earth longitude at substantially the same local time-of-day for each day of the year; and

the apsidal rotation rate in inertial space of the orbit is substantially equal to the mean rate at which the earth revolves about the sun.

2. The satellite of claim 1 wherein the orbit lies substantially in the plane containing the earth'"'"'s equator.

3. The satellite of claim 1 wherein the satellite revolves about the earth five times per day.

4. The satellite of claim 3 in which the semi-major axis of the orbit is approximately 14,450 km;

and the eccentricity of the orbit is approximately 0.49.

5. The satellite of claim 3 wherein the orbit'"'"'s apogee radius is approximately 21,480 km;

and the orbit'"'"'s perigee radius is approximately 7,410 km.

6. The satellite of claim 3 wherein the five daily apogees are positioned above any set of five preselected equispaced earth longitudes.

7. The satellite of claim 1 wherein the orbit follows substantially the same angular path each day of the year from the point of view of any point on the earth.

8. The satellite of claim 1 wherein the satellite revolves about the earth six times per day.

9. The satellite of claim 8 in which the semi-major axis of the orbit is approximately 12,775 km;

and the eccentricity of the orbit is approximately 0.23.

10. The satellite of claim 8 wherein the orbit'"'"'s apogee radius is approximately 15,710 km;

and the orbit'"'"'s perigee radius is approximately 9,840 km.

11. The satellite of claim 8 wherein the six daily apogees are positioned above any set of six preselected equispaced earth longitudes.

12. The satellite of claim 1 wherein said satellite communicates with several tracking stations located on the earth, each tracking station having an antenna adapted to point towards the satellite.

13. A method for placing a man-made satellite into an elliptical orbit about the earth, said orbit having a discrete number of daily apogees, each apogee positioned over the same earth longitude at substantially the same local time-of-day for each day of the year, said method comprising the step of:

causing the apsidal rotation rate in inertial space of the orbit to be substantially equal to the mean rate at which the earth revolves about the sun.

14. The method of claim 13 further comprising the step of periodically performing a stationkeeping maneuver on the satellite to keep at least one of the parameters from the set of parameters comprising inclination and eccentricity within a preselected deadband.

15. The method of claim 14 wherein:

there is at least one tracking station located on the earth, said tracking station having an antenna adapted to point towards the satellite; and

each deadband is chosen so that the satellite comes into view of the tracking station at substantially the same time-of-day every day of the year, and the apparent motion across the sky of the satellite with respect to the tracking station is substantially the same for every day of the year.

16. The method of claim 15 wherein the tracking station antenna tracks the satellite by means of a single programmed tracking sequence that is used every day of the year.