Algorithm for simultaneous attitude maneuver and momentum dumping
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/24
G05D-001/00
출원번호
US-0645296
(2009-12-22)
등록번호
US-8352101
(2013-01-08)
발명자
/ 주소
Thomas, Ronald Shawn
Milford, Richard I.
출원인 / 주소
The Boeing Company
대리인 / 주소
Vista IP Law Group, LLP
인용정보
피인용 횟수 :
4인용 특허 :
42
초록▼
A system and method are disclosed for simultaneous attitude maneuver and momentum dumping. The attitude maneuver is performed using nominal wheel control to minimize propellant usage, while applying a momentum management command to the thruster control loop in order for the wheels to accomplish the
A system and method are disclosed for simultaneous attitude maneuver and momentum dumping. The attitude maneuver is performed using nominal wheel control to minimize propellant usage, while applying a momentum management command to the thruster control loop in order for the wheels to accomplish the desired spacecraft maneuver while simultaneously being reset to a de-saturated target state. The system and method involve a wheel system comprised of reaction wheels and/or a control moment gyroscope (CMG), at least one thruster, and control logic that is in communication with the wheel system and thruster(s). If a spacecraft maneuver is in progress, the control logic biases an error input signal to a thruster control loop to track the wheel maneuver to prevent unnecessary propellant consumption. The control logic is further operable to output thruster torque commands and wheel torque commands that accomplish the maneuver while achieving the desired final momentum target.
대표청구항▼
1. A method for simultaneous attitude maneuver and momentum dumping, the method comprising: determining if a spacecraft maneuver is in progress;if a spacecraft maneuver is in progress, determining reaction wheel speed or control moment gyroscope (CMG) gimbal position and wheel speed;computing moment
1. A method for simultaneous attitude maneuver and momentum dumping, the method comprising: determining if a spacecraft maneuver is in progress;if a spacecraft maneuver is in progress, determining reaction wheel speed or control moment gyroscope (CMG) gimbal position and wheel speed;computing momentum components; summing the momentum components in order to compute an adjusted total system momentum; computing system momentum due to spacecraft rate commands;computing final momentum targets; computing momentum residual;applying an active control law to the momentum residual; andoutputting computed thruster torque commands and reaction wheel/CMG torque commands. 2. The method for simultaneous attitude maneuver and momentum dumping of claim 1, wherein an executive software dispatcher initiates the spacecraft maneuver. 3. The method for simultaneous attitude maneuver and momentum dumping of claim 1, wherein the system momentum is obtained from the reaction wheel speed or control moment gyroscope gimbal position and wheel speed measurements, spacecraft inertial rate, and spacecraft inertia tensor. 4. The method for simultaneous attitude maneuver and momentum dumping of claim 1, wherein the final momentum targets are based on the adjusted total system momentum, actuator momentum, maneuver commands, and post-maneuver momentum. 5. The method for simultaneous attitude maneuver and momentum dumping of claim 1, wherein the momentum residual is equal to the final momentum targets minus the adjusted total system momentum. 6. The method for simultaneous attitude maneuver and momentum dumping of claim 1, wherein the active control law is a proportional integral derivative (PID) control law. 7. The method for simultaneous attitude maneuver and momentum dumping of claim 1, wherein the active control law is a proportional integral (PI) control law. 8. The method for simultaneous attitude maneuver and momentum dumping of claim 1, wherein the computed thruster torque commands are conditioned to preclude actuator saturation. 9. The method for simultaneous attitude maneuver and momentum dumping of claim 1, wherein the computed reaction wheel/CMG torque commands are conditioned to preclude actuator saturation. 10. The method for simultaneous attitude maneuver and momentum dumping of claim 1, wherein the computed thruster torque commands are outputted to a thruster-processing algorithm. 11. The method for simultaneous attitude maneuver and momentum dumping of claim 1, wherein the computed reaction wheel/CMG torque commands are outputted to a reaction wheel/CMG processing algorithm. 12. A system for simultaneous attitude maneuver and momentum dumping, the system comprising: a reaction wheel/CMG system;at least one thruster; and control logic in communication with the reaction wheel/CMG system and the at least one thruster, the control logic operable to: (a) determine if a spacecraft maneuver is in progress;(b) if a spacecraft maneuver is in progress, determining reaction wheel speed or control moment gyroscope gimbal position and wheel speed;(c) compute momentum components;(d) sum the momentum components in order to compute an adjusted total system momentum;(e) compute system momentum due to spacecraft rate commands;(f) compute final momentum targets;(g) compute momentum residual; (h) apply an active control law to the momentum residual; and(i) output computed thruster torque commands and reaction wheel/CMG torque commands. 13. The system for simultaneous attitude maneuver and momentum dumping of claim 12, wherein the system momentum is obtained from the reaction wheel speed or control moment gyroscope gimbal position and wheel speed measurements, spacecraft inertial rate, and spacecraft inertia tensor. 14. The system for simultaneous attitude maneuver and momentum dumping of claim 12, wherein the final momentum targets are based on the adjusted total system momentum, actuator momentum, maneuver commands, and post-maneuver momentum. 15. The system for simultaneous attitude maneuver and momentum dumping of claim 12, wherein the momentum residual is equal to the final momentum targets minus the adjusted total system momentum. 16. The system for simultaneous attitude maneuver and momentum dumping of claim 12, wherein the active control law is a proportional integral derivative (PID) control law. 17. The system for simultaneous attitude maneuver and momentum dumping of claim 12, wherein the active control law is a proportional integral (PI) control law. 18. The system for simultaneous attitude maneuver and momentum dumping of claim 12, wherein the computed thruster torque commands are conditioned to preclude actuator saturation. 19. The system for simultaneous attitude maneuver and momentum dumping of claim 12, wherein the computed reaction wheel/CMG torque commands are conditioned to preclude actuator saturation.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (42)
Kaplan Marshall H. (State College PA) Patterson Thomas C. (Campbell CA) Ramos Alberto (Beallsville MD), Attitude acquisition maneuver for a bias momentum spacecraft.
Yocum ; Jr. John F. ; Cazeau Patrick A. ; Koffman Stephen J. ; Baker Douglas A., Method of controlling attitude of a momentum biased spacecraft during long-duration thruster firings.
Wirthman David J. (Mountain View CA) Higham John S. (Mountain View CA) Baylocq Michel B. (Menlo Park CA) Chu Peter Y. (Palo Alto CA), Post transition momentum management.
Tilley Scott W. (Belmont CA) Liu Tung Y. (Union City CA) Higham John S. (Mountain View CA), Spacecraft attitude control and momentum unloading using gimballed and throttled thrusters.
Michael F. Barsky ; Thomas M. Tanner ; Loren I. Slafer ; Paul D. Williams ; George B. Semeniuk ; Joseph M. Allard GB, Stationkeeping method utilizing open-loop thruster pulses and closed-loop authority limited momentum storage devices.
Bender Douglas J. ; Nakano William A. ; Burkett William L. ; Obert Kenneth R. ; Bowles Tiffany ; Bockman Stuart F., Sun-referenced safe-hold control for momentum biased satellites.
Yocum John F. (Rancho Palos Verdes CA) Tolmasoff Mike W. (Whittier CA) Faber Thomas D. (Woodland Hills CA), Three axes stabilized spacecraft and method of sun acquisition.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.