Systems and methods for satellite orbit and momentum control

Patent metadata

Field	Value
Publication number	US-10569909-B2
Application number	US-201615085081-A
Country	US
Kind code	B2
Filing date	Mar 30, 2016
Priority date	Mar 30, 2016
Publication date	Feb 25, 2020
Grant date	Feb 25, 2020

Abstract

An example spacecraft includes a first arm having a first end pivotably coupled to the spacecraft and a second end. The example spacecraft includes a first thruster rotatably coupled to the second end of the first arm. The first arm extends from the first pivot point along a first edge of an anti-nadir face of the spacecraft when the first arm is in a stowed position. The first arm is configured to pivot between the stowed position, a first extended position in which the first arm extends outward from the spacecraft relative to the first edge, and a second extended position in which the first arm extends along a third edge of the anti-nadir face and the first thruster is disposed outward of a second edge of the anti-nadir face opposite the first edge.

First claim

What is claimed is:

1. A spacecraft comprising:
a first arm having a first end pivotably coupled to a first pivot point of the spacecraft and a second end;
a first thruster rotatably coupled to the second end of the first arm;
a second arm having a first end pivotably coupled to a second pivot point of the spacecraft and a second end; and
a second thruster coupled to the second end of the second arm,
the first arm extending from the first pivot point along a first edge of an anti-nadir face of the spacecraft when the first arm is in a stowed position and the second arm extending from the second pivot point along a second edge of the anti-nadir face opposite the first edge when the second arm is in a stowed position, the first thruster and the second thruster disposed at the anti-nadir face of the spacecraft when the first arm is in the stowed position and the second arm is in the stowed position,
the first arm configured to pivot between (a) the stowed position of the first arm, (b) a first extended position of the first arm in which the first arm extends outward from the spacecraft relative to the first edge, and (c) a second extended position of the first arm in which the first arm extends along a third edge of the anti-nadir face and the first thruster is disposed outward of the second edge, and
the second arm configured to pivot between (a) the stowed position of the second arm, (b) a first extended position of the second arm in which the second arm extends outward from the spacecraft relative to the second edge, and (c) a second extended position of the second arm in which the second arm extends along a fourth edge of the anti-nadir face and the second thruster is disposed outward of the first edge, wherein the third edge is opposite the fourth edge.

2. The spacecraft of claim 1 , wherein the first thruster is rotatably coupled to the second end of the first arm via a gimbaled platform.

3. The spacecraft of claim 2 , wherein the gimbaled platform is configured to rotate the first thruster relative to a center of gravity of the spacecraft.

4. The spacecraft of claim 1 , further including a motor, the first end of the first arm coupled to the motor.

5. The spacecraft of claim 1 , wherein the first arm has a length substantially equal to a length of the anti-nadir face of the spacecraft.

6. The spacecraft of claim 1 , wherein the first arm comprises aluminum.

7. The spacecraft of claim 1 , wherein the first arm is configured to (1) selectively pivot about the first pivot to position the first thruster in the first extended position of the first arm to generate the change in velocity in a tangential direction and a radial direction during firing and (2) selectively pivot about the first pivot point to position the first thruster in the second extended position of the first arm to generate the change in velocity in a normal direction and a radial direction during firing.

8. The spacecraft of claim 1 , wherein the first pivot point is disposed proximate to a first corner formed by the first edge and the third edge of the anti-nadir face of the spacecraft and the second pivot point is disposed proximate to a second corner formed by the second edge and the fourth edge of the anti-nadir face of the spacecraft.

9. The spacecraft of claim 1 , wherein each of the first arm and the second arm is configured to pivot between a range of 0° and 270° about the respective first pivot point and the second pivot point.

10. The spacecraft of claim 1 , wherein when the first arm is in the first extended position of the first arm, the first thruster is disposed a first distance from the first edge and when the first arm is in the second extended position of the first arm, the first thruster is disposed a second distance from the second edge, the first distance greater than the second distance.

11. The spacecraft of claim 1 , wherein the first arm is a non-articulated arm.

12. The spacecraft of claim 1 , wherein the first edge has a first length and the third edge has a third length less than the first length.

13. The spacecraft of claim 1 , wherein the first arm is to rotate outward relative to the anti-nadir face of the spacecraft to pivot between the first extended position of the first arm and the second extended position of the first arm.

14. A method comprising:
determining, by executing an instruction with a processor, a position of a first thruster of a satellite relative to the satellite to correct an orbit of the satellite, the first thruster rotatably coupled to a first arm at a first pivot point, the first arm coupled to the satellite, the first arm configured to pivot between (a) a stowed position in which the first arm extends from the first pivot point along a first edge of a face of the satellite, (b) a first extended position in which the first arm extends outward relative to the first edge of the face of the satellite, and (c) a second extended position in which the first arm extends along a second edge of the face of the satellite and the first thruster is disposed outward of a third edge of the face of the satellite, wherein the first edge is opposite the third edge;
determining, by executing an instruction with the processor, whether the first arm is to be in one of the stowed position, the first extended position, or the second extended position during firing of the first thruster based on the determination of the position of the first thruster to correct the orbit;
if the one of the stowed position, the first extended position, or the second extended position differs from a current position of the first arm, moving the first arm to the determined one of the stowed position, the first extended position, or the second extended position; and
firing the first thruster to correct the orbit of the satellite with the first arm in the one of the stowed position, the first extended position, or the second extended position.

15. The method of claim 14 , further comprising:
determining a second position of the first thruster relative to a center of gravity of the satellite to control a momentum of the satellite; and
rotating the first thruster relative to the center of gravity of the satellite based on the second position.

16. The method of claim 15 , wherein the rotating comprises pointing the first thruster away from the center of gravity to cause the thruster to produce one or more of roll torque, pitch torque, or yaw torque upon firing of the first thruster.

17. The method of claim 14 , further comprising:
determining a second position of a second thruster relative to the satellite to correct the orbit of the satellite;
pivoting a second arm coupled to the satellite about the satellite to move the second thruster to the second position, the second thruster coupled to the second arm; and
determining a time for at least one of the first thruster or the second thruster to fire.

18. The method of claim 14 , further including determining if the position corrects the orbit of the satellite within a predetermined threshold relative to an intended orbit for the satellite.

19. The method of claim 14 , wherein when the first arm is in the first extended position of the first arm, an end of the first arm to which the first thruster is coupled is disposed a first distance relative to the first edge of the face of the satellite and when the first arm is in the second extended position of the first arm, the end of the first arm is disposed a second distance relative to the first edge, the second distance greater than the first distance.

Assignees

• Boeing Co

Inventors

• Ho Yiu-Hung Monte

Classifications

• B64G1/262 Primary

  having adjustable angles, e.g. gimbaled thrusters · CPC title

• B64G1/242 Primary

  Orbits and trajectories · CPC title

• B64G1/26

  using jets · CPC title

• B64G1/2429

  Station keeping · CPC title