Efficient orbital storage and deployment for spacecraft in inclined geosynchronous orbit
A constellation of Earth-orbiting spacecraft includes a first spacecraft disposed in a first orbit, a second spacecraft disposed in a second orbit, and a third spacecraft disposed in a third orbit. Each of the first orbit, the second orbit and the third orbit is substantially circular with a radius of approximately 42,164 km, and has a specified inclination with respect to the equator within a range of 5° to 20°. The first orbit has a first right ascension of ascending node RAAN1, the second orbit has a second RAAN (RAAN2) approximately equal to RAAN1+120°, and the third orbit has a third RAAN (RAAN3) approximately equal to RAAN1+240°. A fourth spacecraft is disposed in a fourth orbit that has a period of approximately one sidereal day, an inclination of less than 2°, a perigee altitude of at least 8000 km, and an eccentricity between approximately 0.4 and 0.66.
1. A constellation of Earth-orbiting spacecraft, the constellation comprising:
a first spacecraft disposed in a first orbit, a second spacecraft disposed in a second orbit, and a third spacecraft disposed in a third orbit, wherein:
each of the first orbit, the second orbit and the third orbit is substantially circular with a radius of approximately 42,164 km, and has a specified inclination with respect to the equator within a range of 5° to 20°;
the first orbit has a first right ascension of ascending node RAAN1, the second orbit has a second RAAN (RAAN2) approximately equal to RAAN1+120°, and the third orbit has a third RAAN (RAAN3) approximately equal to RAAN1+240°; and
a fourth spacecraft is disposed in a fourth orbit, the fourth orbit having a period of approximately one sidereal day, an inclination of less than 2°, a perigee altitude of at least 8000 km, and an eccentricity within a range of 0.4 to 0.66.
2. The constellation of claim 1 , wherein the fourth spacecraft is configured to perform an orbit transfer maneuver from the fourth orbit to any of the first orbit, the second orbit and the third orbit, the orbit transfer maneuver requiring a velocity increment (ΔV) not greater than 1700 m/s.
3. The constellation of claim 2 , wherein at least one electric thruster onboard the fourth spacecraft is configured to provide the velocity increment.
4. The constellation of claim 1 , wherein each of the first spacecraft, the second spacecraft and the third spacecraft is disposed proximate to a first common longitudinal station.
5. The constellation of claim 1 , further comprising a fifth spacecraft and a sixth spacecraft disposed in the first orbit, a seventh spacecraft and a eighth spacecraft disposed in the second orbit, and a ninth spacecraft and a tenth spacecraft disposed in the third orbit.
6. The constellation of claim 5 , wherein:
each of the first spacecraft, the second spacecraft and the third spacecraft is disposed proximate to a first common longitudinal station;
each of the fifth spacecraft, the seventh spacecraft and the ninth spacecraft is disposed at a second common longitudinal station, different from the first common longitudinal station; and
each of the sixth spacecraft, the eighth spacecraft and the tenth spacecraft is disposed at a third common longitudinal station, different from the first common longitudinal station and the second common longitudinal station.
7. The constellation of claim 6 , wherein an apogee of the fourth orbit is approximately aligned with one of the first common longitudinal station, the second common longitudinal station and the third common longitudinal station.
8. The constellation of claim 1 , wherein the fourth orbit has an initially established line of apses such that apogee is aligned in the direction of the vernal equinox.
9. A constellation of Earth-orbiting spacecraft, the constellation comprising:
a first spacecraft disposed in a first orbit, and a second spacecraft disposed in a second orbit, wherein:
each of the first orbit and the second orbit is substantially circular with a radius of approximately 42,164 km, and has a specified inclination with respect to the equator within a range of 5° to 20°;
the first orbit has a first right ascension of ascending node RAAN1 and the second orbit has a second RAAN (RAAN2) approximately equal to RAAN1+90°; and
a third spacecraft is disposed in a third orbit, the third orbit having a period of approximately one sidereal day, an inclination less than 2°, a perigee altitude of at least 8000 km, and an eccentricity within a range of 0.4 to 0.66.
10. The constellation of claim 9 , wherein the third spacecraft is configured to perform an orbit transfer maneuver from the third orbit to either of the first orbit and the second orbit, the orbit transfer maneuver requiring a velocity increment (ΔV) not greater than 1700 m/s.
11. The constellation of claim 10 , wherein at least one electric thruster onboard the third spacecraft is configured to provide the velocity increment.
12. The constellation of claim 9 , wherein each of the first spacecraft, the second spacecraft and the third spacecraft is disposed proximate to a first common longitudinal station.
13. The constellation of claim 9 , wherein the third orbit has an initially established line of apses such that apogee is aligned in the direction of the vernal equinox.
14. A method comprising:
executing a spare provisioning strategy for a constellation of Earth-orbiting spacecraft, wherein:
the constellation includes two or more spacecraft, including a first spacecraft disposed in a first operational orbit and a second spacecraft disposed in a second operational orbit;
each of the first orbit and the second orbit is substantially circular with a radius of approximately 42,164 km;
the first orbit has a first specified inclination with respect to the equator and the second orbit has a second specified inclination with respect to the equator, the first specified inclination and the second specified inclination each being within a range of 5° to 20°; and
the spare provisioning strategy includes disposing a spare spacecraft in a storage orbit, the storage orbit having a period of approximately one sidereal day, an inclination of less than 2°, a perigee altitude of at least 8000 km, and an eccentricity within a range of 0.4 to 0.66.
15. The method of claim 14 , wherein the spare provisioning strategy further includes transferring the spare spacecraft from the storage orbit to one of the first operational orbit and the second operational orbit.
16. The method of claim 15 , wherein transferring the spare spacecraft from the storage orbit to one of the first orbit and the second orbit includes providing a velocity increment (ΔV) not greater than 1700 m/s.
17. The method of claim 14 , wherein the constellation includes three or more spacecraft, including the first spacecraft disposed in the first operational orbit, the second spacecraft disposed in the second operational orbit, and a third spacecraft disposed in a third operational orbit.
18. The method of claim 17 , wherein the spare provisioning strategy further includes transferring the spare spacecraft from the storage orbit to one of the first orbit, the second orbit and the third orbit.
19. The method of claim 18 , wherein transferring the spare spacecraft from the storage orbit to one of the first orbit, the second orbit and the third orbit includes providing a velocity increment (ΔV) not greater than 1700 m/s.
20. The method of claim 14 , wherein the storage orbit has an initially established line of apses such that apogee is aligned in the direction of the vernal equinox.