Systems and method of controlling a spacecraft using attitude sensors
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/38
B64G-001/28
출원번호
US-0178440
(2008-07-23)
등록번호
US-8620496
(2013-12-31)
발명자
/ 주소
Liu, Dan Y.
Wang, Qinghong W.
Chiang, Richard Y.
출원인 / 주소
The Boeing Company
대리인 / 주소
Armstrong Teasdale LLP
인용정보
피인용 횟수 :
3인용 특허 :
20
초록▼
A system for damping nutation and removing wobble of a spacecraft spinning about a given axis is provided. The system includes a sensor configured to determine three dimensional attitude measurements of the spacecraft, a processor operatively coupled to the sensor and configured to execute a process
A system for damping nutation and removing wobble of a spacecraft spinning about a given axis is provided. The system includes a sensor configured to determine three dimensional attitude measurements of the spacecraft, a processor operatively coupled to the sensor and configured to execute a process that facilitates aligning the spin axis with a spacecraft momentum vector. The processor, when executing the process, is programmed to receive spacecraft attitude data from the sensor, determine a torque command using the received attitude data, and control a momentum storage actuator on the spacecraft using the determined torque command such that an angular deviation about the given axis is reduced.
대표청구항▼
1. A method of damping nutation and removing wobble of a spacecraft spinning about a given axis, the spacecraft includes an attitude sensor configured to provide three dimensional spacecraft attitude measurements, wherein the attitude sensor includes at least one of a star tracker, sun sensor, horiz
1. A method of damping nutation and removing wobble of a spacecraft spinning about a given axis, the spacecraft includes an attitude sensor configured to provide three dimensional spacecraft attitude measurements, wherein the attitude sensor includes at least one of a star tracker, sun sensor, horizon sensor, and magnetometer, said method comprising: receiving spacecraft attitude data from the attitude sensor;determine an angular position and an angular rate of the spacecraft using the received spacecraft attitude data;determining a torque command using the determined angular rate; andcontrolling a momentum storage actuator of the spacecraft using said determined control torque command such that an angular deviation about the given axis is reduced, wherein the angular deviation includes a nutation and a wobble angle. 2. A method in accordance with claim 1 wherein determining an angular position and an angular rate of the spacecraft further comprises estimating the angular position and the angular rate of the spacecraft using at least one of said received attitude data, an estimated inertia matrix of the spacecraft, an estimated wheel momentum of the spacecraft, and a feedforward acceleration using said determined control torque command. 3. A method in accordance with claim 2 wherein determining a torque command further comprises dampening the nutation of the spacecraft and reducing the wobble angle of the spacecraft with internal momentum. 4. A method in accordance with claim 1 wherein controlling a momentum storage actuator of the spacecraft further comprises executing a control command by at least one of a momentum wheel, a reaction wheel, and a control momentum gyro. 5. A method in accordance with claim 4 further comprising providing a one-dimensional torque to facilitate controlling a wobble angle about a single spacecraft axis. 6. A method in accordance with claim 4 further comprising providing a two-dimensional torque to facilitate controlling a wobble angle to zeros. 7. A system for damping nutation and removing wobble of a spacecraft spinning about a given axis, said system comprising: a sensor configured to determine three dimensional attitude measurements of said spacecraft, wherein said sensor comprises at least one of a star tracker, sun sensor, horizon sensor, and magnetometer;a processor operatively coupled to said sensor and configured to execute a process that facilitates aligning said spin axis with a spacecraft momentum vector, said processor, when executing said process, is programmed to:receive spacecraft attitude data from said sensor;determine an angular position and an angular rate of the spacecraft using the received spacecraft attitude data;determine a torque command using the determined angular rate; andcontrol a momentum storage actuator of said spacecraft using said determined torque command such that an angular deviation about the given axis is reduced, wherein the angular deviation includes a nutation and a wobble angle. 8. A system in accordance with claim 7 wherein the momentum storage actuator is configured to reduce the angular deviation about the given axis. 9. A system in accordance with claim 8, wherein the processor further comprises a control law module programmed to provide the torque command to said actuator. 10. A system in accordance with claim 7 wherein the processor, when executing said process, is further programmed to estimate the angular position and the angular rate of the spacecraft using at least one of said received attitude data, an estimated inertia matrix of the spacecraft, an estimated wheel momentum of the spacecraft, and a feedforward acceleration using said determined control torque command. 11. A system in accordance with claim 10 wherein the processor, when executing said process, is further programmed to determine the nutation of the spacecraft and reducing the wobble angle of the spacecraft with internal momentum. 12. A system in accordance with claim 7 wherein the processor, when executing said process, is further programmed to execute a control command by at least one of a momentum wheel, a reaction wheel, and a control momentum gyro. 13. A spacecraft spinning about a given axis comprising: a sensor configured to determine three dimensional attitude measurements of said spacecraft, wherein said sensor comprises at least one of a star tracker, sun sensor, horizon sensor, and magnetometer;a momentum storage actuator configured to reduce an angular deviation about the given axis; anda non-transitory computer readable medium comprising a process to be executed by a processor for use in damping nutation and removing wobble of a spacecraft about the given axis, said processor, when executing said process, is programmed to:receive spacecraft attitude data from said sensor;determine an angular position and an angular rate of the spacecraft using the received spacecraft attitude data;determine a torque command using the determined angular rate; andcontrol the momentum storage actuator of said spacecraft using said determined torque command such that an angular deviation about the given axis is reduced, wherein the angular deviation includes a nutation and a wobble angle. 14. A spacecraft in accordance with claim 13 wherein the momentum storage actuator is configured to reduce the angular deviation about the given axis. 15. A spacecraft in accordance with claim 14, wherein the processor further comprises a control law module programmed to provide the torque command to said actuator. 16. A spacecraft in accordance with claim 13 wherein the processor, when executing said process, is further programmed to estimate the angular position and the angular rate of the spacecraft using at least one of said received attitude data, an estimated inertia matrix of the spacecraft, an estimated wheel momentum of the spacecraft, and a feedforward acceleration using said determined control torque command. 17. A spacecraft in accordance with claim 13 wherein the processor, when executing said process, is further programmed to execute a control command by at least one of a momentum wheel, a reaction wheel, and a control momentum gyro.
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이 특허에 인용된 특허 (20)
Amieux Jean-Claude (Voisins le Bretonneux FRX), Active nutation control system for space vehicle.
Kaplan Marshall H. (State College PA) Patterson Thomas C. (Campbell CA) Ramos Alberto (Beallsville MD), Attitude acquisition maneuver for a bias momentum spacecraft.
Raman Kidambi V. (East Windsor NJ) Muhlfelder Ludwig (Livingston NJ) Hubert Carl H. (Cranbury NJ) Furia Thomas J. (Ambler PA), Attitude control system.
Achkar Issam-Maurice (Cannes-la-Bocca FRX) Guillermin Pierre (Nice FRX), Attitude control system for three-axis stabilized satellite in near-equatorial orbit.
Surauer Michael (Chieming DEX) Bittner Helmut (Munich DEX), Process and a device for controlling the attitude of a three-axis stabilized spinning spacecraft.
Fowell Richard A. (Culver City CA) Yocum John F. (Rancho Palos Verdes CA), Satellite spin axis stabilization using a single degree of freedom transverse momentum storage device.
Sobel, Alexander Jacob; Wang, Qinghong W.; Lemke, Gary; Lui, Timothy; Lee, Kangsik; Caplin, Glenn N.; Fontana, Troy Allen, Reorientation of a spinning spacecraft using gimbaled electric thrusters.
Wang, Qinghong W.; Sobel, Alexander Jacob; Lemke, Gary; Lui, Timothy; Lee, Kangsik; Caplin, Glenn N.; Fontana, Troy Allen, Spin stabilization of a spacecraft for an orbit maneuver.
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