Spacecraft momentum unload and station-keeping techniques
View Patent ↗Spacecraft momentum management techniques are coordinated with station-keeping maneuvers or other delta-V maneuvers. A body stabilized spacecraft attitude is controlled, the spacecraft including at least one momentum/reaction wheel, and a set of thrusters. A first momentum storage deadband limit is adjusted, the adjustment being related to a first delta-V maneuver window. A momentum management strategy is executed with the adjusted first momentum storage deadband limit such that a first thruster firing that performs desaturation of the momentum/reaction wheel also provides velocity change beneficial to the first delta-V maneuver.
1. A method comprising:
controlling an attitude of a body stabilized spacecraft, the spacecraft comprising at least one momentum/reaction wheel configured to maintain the attitude with respect to a spacecraft axis by storing momentum, and a set of thrusters, the controlling including:
executing a momentum management strategy coordinated with a first delta-V maneuver, the first delta-V maneuver to be conducted by firing a first thruster during a first window for conducting the first delta-V maneuver, the momentum management strategy including:
shifting a first momentum storage deadband limit; and
firing a second thruster such that impulse from the second thruster desaturates the momentum/reaction wheel in conformance with the shifted first momentum storage deadband limit, and, at the same time, also provides a velocity change beneficial to the first delta-V maneuver; wherein
the momentum management strategy complies with one or both of a first condition and a second condition, the first condition being that the first thruster is different from the second thruster, and the second condition being that firing the second thruster to desaturate the momentum/reaction wheel occurs at least partially outside the first window.
2. The method of claim 1 , wherein shifting the first momentum storage deadband limit increases, during a first time interval proximate to the first window, a first requirement for desaturation impulse.
3. The method of claim 2 , wherein:
the momentum management strategy is coordinated with a second delta-V maneuver, the second delta-V maneuver to be conducted during a second window for conducting the second delta-V maneuver, the momentum management strategy further including:
shifting a second momentum storage deadband limit; and
firing one or both of the second thruster and a third thruster such that impulse from the firing desaturates the momentum/reaction wheel in conformance with the shifted second momentum storage deadband limit, and, at the same time, also provides velocity change detrimental to the second delta-V maneuver.
4. The method of claim 3 , wherein shifting the second momentum storage deadband limit decreases, during a second time interval proximate to the second window, a second requirement for desaturation impulse.
5. The method of claim 1 , wherein the first thruster is an electric thruster, and the second thruster a chemical thruster.
6. The method of claim 1 , wherein each of the first thruster and the second thruster is a chemical thruster.
7. The method of claim 1 , wherein each of the first thruster and the second thruster is an electric thruster.
8. A method comprising:
controlling an attitude of a 3-axis stabilized spacecraft attitude, the spacecraft being in geosynchronous orbit, and comprising at least one momentum/reaction wheel configured to maintain the attitude with respect to an axis by storing momentum, and a set of thrusters, the controlling including:
executing a momentum management strategy coordinated with a first north south statinkeeping (NSSK) maneuver, the first NSSK maneuver to be conducted by firing a first thruster during a first window for conducting the first NSSK maneuver, the momentum management strategy including:
shifting a first momentum storage deadband limit; and
firing a second thruster such that impulse from the second thruster desaturates the momentum/reaction wheel in conformance with the shifted first momentum storage deadband limit, and, at the same time, also provides a velocity change beneficial to the first NSSK maneuver; wherein
the momentum management strategy complies with one or both of a first condition and a second condition, the first condition being that the first thruster is different from the second thruster, and the second condition being that firing the second thruster to desaturate the momentum/reaction wheel occurs at least partially outside the first window.
9. The method of claim 8 , wherein shifting the first momentum storage deadband limit increases, during a first time interval proximate to the first window, a first requirement for desaturation impulse.
10. The method of claim 9 , wherein:
the momentum management strategy is coordinated with a second NSSK maneuver, the second NSSK maneuver to be conducted during a second window for conducting the second NSSK maneuver, the momentum management strategy further including:
shifting a second momentum storage deadband limit; and
firing one or both of the second thruster and a third thruster such that impulse from the firing desaturates the momentum/reaction wheel in conformance with the shifted second momentum storage deadband limit, and, at the same time, also provides velocity change detrimental to the second NSSK maneuver.
11. The method of claim 10 , wherein shifting the second momentum storage deadband limit decreases, during a second time interval proximate to the second window, a second requirement for desaturation impulse.
12. The method of claim 8 , wherein shifting the first momentum storage deadband limit includes narrowing a momentum storage deadband during a first time interval proximate to a crossing of a descending node, and widening the momentum storage deadband during a second time interval proximate to a crossing of an ascending node.
13. The method of claim 8 , wherein shifting the first momentum storage deadband limit includes narrowing a momentum storage deadband at a first time interval proximate to a crossing of an ascending node, and widening the momentum storage deadband at a second time interval proximate to a crossing of a descending node.
14. The method of claim 8 , wherein the first thruster is an electric thruster, and the second thruster is a chemical thruster.
15. The method of claim 8 , wherein each of the first thruster and the second thruster is a chemical thruster.
16. The method of claim 8 , wherein each of the first thruster and the second thruster is an electric thruster.
17. A method comprising:
controlling an attitude of a body stabilized spacecraft attitude, the spacecraft comprising at least one momentum/reaction wheel configured to maintain the attitude with respect to an axis by storing momentum, and a set of thrusters, the controlling including:
executing a momentum management strategy coordinated with a first delta-V maneuver, the first delta-V maneuver to be conducted by firing a first thruster during a first window for conducting the first delta-V maneuver, the momentum management strategy including:
making a first adjustment to a momentum storage deadband, the first adjustment being coordinated with the first window, the first adjustment comprising:
a widened deadband proximate to and prior to the first window, and
a narrowed deadband during the first window; and
firing a second thruster, different from the first thruster, such that impulse from the second thruster firing desaturates the momentum/reaction wheel, and, at the same time, also provides a velocity change beneficial to the first delta-V maneuver.
18. The method of claim 17 , wherein:
the momentum management strategy is coordinated with a second delta-V maneuver, the second delta-V maneuver to be conducted during a second window for conducting the second delta-V maneuver, the momentum management strategy further including:
making a second adjustment to the momentum storage deadband, the second adjustment being coordinated with the second window, the second adjustment comprising:
a narrowed deadband proximate to and prior to the second window, and a widened deadband during the second window; and
firing one or both of the second thruster and a third thruster such that impulse from the firing desaturates the momentum/reaction wheel, and, at the same time, also provides velocity change detrimental to the second delta-V maneuver.
19. A body stabilized spacecraft, the spacecraft comprising:
at least one momentum/reaction wheel configured to control a spacecraft attitude with respect to an axis by storing momentum;
a set of thrusters; and
a controller communicatively coupled with the at least one momentum/reaction wheel and the set of thrusters, the controller programmed to:
execute a momentum management strategy coordinated with a first delta-V maneuver, the first delta-V maneuver to be conducted by firing a first thruster during a first window for conducting the first delta-V maneuver, the momentum management strategy including:
shifting a first momentum storage deadband limit; and
firing a second thruster such that impulse from the second thruster desaturates the momentum/reaction wheel in conformance with the shifted first momentum storage deadband limit, and, at the same time, also provides a velocity change beneficial to the first delta-V maneuver; wherein
the momentum management strategy complies with one or both of a first condition and a second condition, the first condition being that the first thruster is different from the second thruster, and the second condition being that firing the second thruster to desaturate the momentum/reaction wheel occurs at least partially outside the first window.
20. The spacecraft of claim 19 , wherein shifting the first momentum storage deadband limit increases, during a first time interval proximate to the first window, a first requirement for desaturation impulse.
21. The spacecraft of claim 20 , wherein:
the momentum management strategy is coordinated with a second delta-V maneuver, the second delta-V maneuver to be conducted during a second window for conducting the second delta-V maneuver, the momentum management strategy further including:
shifting a second momentum storage deadband limit; and
firing one or both of the second thruster and a third thruster such that impulse from the firing desaturates the momentum/reaction wheel in conformance with the shifted second momentum storage deadband limit, and, at the same time, also provides velocity change detrimental to the second delta-V maneuver.
22. The spacecraft of claim 21 , wherein shifting the second momentum storage deadband limit decreases, during a second time interval proximate to the second window, a second requirement for desaturation impulse.
23. The spacecraft of claim 19 , wherein the first thruster is an electric thruster, and the second thruster is a chemical thruster.
24. The spacecraft of claim 19 , wherein each of the first thruster and the second thruster is a chemical thruster.
25. The spacecraft of claim 19 , wherein each of the first thruster and the second thruster is an electric thruster.
26. A body stabilized spacecraft configured for operation in geosynchronous orbit, the spacecraft comprising:
at least one momentum/reaction wheel configured to control a spacecraft attitude with respect to an axis by storing momentum;
a set of thrusters; and
a controller communicatively coupled with the at least one momentum/reaction wheel and the set of thrusters, the controller programmed to:
execute a momentum management strategy coordinated with a first north south stationkeeping (NSSK) maneuver, the first NSSK maneuver to be conducted by firing a first thruster during a first window for conducting the first NSSK maneuver, the momentum management strategy including:
shifting a first momentum storage deadband limit; and
firing a second thruster such that impulse from the second thruster desaturates the momentum/reaction wheel in conformance with the shifted first momentum storage deadband limit, and, at the same time, also provides a velocity change beneficial to the first NSSK maneuver; wherein
the momentum management strategy complies with one or both of a first condition and a second condition, the first condition being that the first thruster is different from the second thruster, and the second condition being that firing the second thruster to desaturate the momentum/reaction wheel occurs at least partially outside the first window.
27. The spacecraft of claim 26 , wherein shifting the first momentum storage deadband limit increases, during a first time interval proximate to the first window, a first requirement for desaturation impulse.
28. The spacecraft of claim 27 , wherein:
the momentum management strategy is coordinated with a second NSSK maneuver, the second NSSK maneuver to be conducted during a second window for conducting the second NSSK maneuver, the momentum management strategy further including:
shifting a second momentum storage deadband limit; and
firing one or both of the second thruster and a third thruster such that impulse from the firing desaturates the momentum/reaction wheel in conformance with the shifted second momentum storage deadband limit, and, at the same time, also provides velocity change detrimental to the second NSSK maneuver.
29. The spacecraft of claim 28 , wherein shifting the second momentum storage deadband limit decreases, during a second time interval proximate to the second window, a second requirement for desaturation impulse.
30. The spacecraft of claim 26 , wherein shifting the momentum storage deadband limit includes narrowing a momentum storage deadband during a first time interval proximate to a crossing of a descending node, and widening the momentum storage deadband during a second time interval proximate to a crossing of an ascending node.
31. The spacecraft of claim 26 , wherein shifting the first momentum storage deadband limit includes narrowing a momentum storage deadband at a first time interval proximate to a crossing of an ascending node, and widening the momentum storage deadband at a second time interval proximate to a crossing of a descending node.
32. The spacecraft of claim 26 , wherein the first thruster is an electric thruster, and the second thruster is a chemical thruster.
33. The spacecraft of claim 26 , wherein each of the first thruster and the second thruster is a chemical thruster.
34. The method of claim 26 , wherein each of the first thruster and the second thruster is an electric thruster.
35. A body stabilized spacecraft, the spacecraft comprising:
at least one momentum/reaction wheel configured to control a spacecraft attitude with respect to an axis by storing momentum;
a set of thrusters; and
a controller communicatively coupled with the at least one momentum/reaction wheel and the set of thrusters, the controller programmed to:
execute a momentum management strategy coordinated with a first delta-V maneuver, the first delta-V maneuver to be conducted by firing a first thruster during a first window for conducting the first delta-V maneuver, the momentum management strategy including:
making a first adjustment to a momentum storage deadband, the first adjustment being coordinated with the first window, the first adjustment comprising:
a widened deadband proximate to and prior to the first window, and
a narrowed deadband during the first window; and
firing a second thruster, different from the first thruster, such that impulse from the second thruster firing desaturates the momentum/reaction wheel, and, at the same time, also provides a velocity change beneficial to the first delta-V maneuver.
36. The spacecraft of claim 35 , wherein:
the momentum management strategy is coordinated with a second delta-V maneuver, the second delta-V maneuver to be conducted during a second window for conducting the second delta-V maneuver, the momentum management strategy further including:
making a second adjustment to the momentum storage deadband, the second adjustment being coordinated with the second window, and the second adjustment comprising:
a narrowed deadband proximate to and prior to the second window, and a widened deadband during the second window; and
firing one or both of the second thruster and a third thruster such that impulse from the firing desaturates the momentum/reaction wheel, and, at the same time, also provides velocity change detrimental to the second delta-V maneuver.