System and method for controlling the attitude of a space craft
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/28
출원번호
US-0496140
(2000-02-01)
발명자
/ 주소
John J. Anagnost
Paul C. Kiunke
출원인 / 주소
Raytheon Company
대리인 / 주소
Colin M. Raufer
인용정보
피인용 횟수 :
13인용 특허 :
8
초록▼
A system (30) for adjusting the orientation of a spacecraft adapted for use with a satellite (10). The system (30) includes a first control circuit (32, 38, 40) for canceling any momentum of the spacecraft via a counter-rotating spacecraft bus (16, 18). A second controller (32, 42, 44, 46, 48) orien
A system (30) for adjusting the orientation of a spacecraft adapted for use with a satellite (10). The system (30) includes a first control circuit (32, 38, 40) for canceling any momentum of the spacecraft via a counter-rotating spacecraft bus (16, 18). A second controller (32, 42, 44, 46, 48) orients the spacecraft via the application of internal spacecraft forces. In a specific embodiment, the spacecraft bus (16, 18) serves a dual use as storage section and includes a mass (16) having a moment of inertia on the same order as the moment of inertia of the satellite (10). The satellite (10) includes a bus section (16) and a payload section (14). The mass (16) includes the bus section (16). The first control circuit (32, 38, 40) runs software to selectively spin the mass (16) to cancel the momentum of the satellite (10). The software computes an actuator control signal, via a computer (32), that drives a first actuator (38) that spins the mass (16). The first control circuit (32, 38, 40) further includes a circuit for determining the inertial angular rate of the satellite (10) that includes a gyroscope sensor package (34) in communication with the computer (32). The gyroscope sensor package (34) provides a rate signal to the computer (32) that is representative of the momentum of the satellite (10). The computer (32) runs software for generating the actuator control signal in response to the receipt of the rate signal from the gyroscope sensor package (34). The second controller (32, 42, 44, 46, 48) includes a first reaction wheel (20) having an axis of rotation (26) approximately perpendicular to an axis of rotation (28) of a second reaction wheel (22). The first and second reaction wheels (20, 22) are rigidly mounted to the spacecraft bus (18, 16) and are free to spin about their respective axis. The first and second reaction wheels (20, 22) are selectively spun via first and second actuators (44, 48), respectively, in response to the receipt of first and second steering control signals, respectively.
대표청구항▼
1. An attitude control system for a spacecraft having a payload and an attitude control section, said attitude control system comprising:a mass disposed in said attitude control section; a single degree of freedom joint connecting said mass to said payload whereby the mass has a single degree of fre
1. An attitude control system for a spacecraft having a payload and an attitude control section, said attitude control system comprising:a mass disposed in said attitude control section; a single degree of freedom joint connecting said mass to said payload whereby the mass has a single degree of freedom relative to the payload about a first axis; first means for rotating said mass; second means for controlling said first means; and third means for controlling rotation of said spacecraft about a second axis, said third means including: a first reaction wheel and a second reaction wheel having an axis of rotation at an angle to an axis of rotation of said first reaction wheel.
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이 특허에 인용된 특허 (8)
Rosen Harold A. (Santa Monica CA), Attitude control of spinning spacecraft.
Eisenhaure David B. (Hull MA) Downer James R. (Cambridge MA) Bliamptis Tim E. (Lexington MA) Oberbeck George A. (East Walpole MA) Hendrie Susan D. (Chicago IL), Energy storage attitude control and reference system.
Mehlen, Christian; Pierre, Estelle, Device for controlling relative position(s) by analyzing dual-frequency signals, for a spacecraft of a group of spacecraft in formation.
Wang,Hanching Grant; Fowell,Richard A.; Ih,Che Hang C., Method and apparatus for reaction wheel dynamic compensation in long-duration deployment of a large reflector.
Wang,Hanching Grant; Fowell,Richard A.; Ih,Che Hang C., Method and apparatus for solar tacking momentum maintenance in long-duration deployment of a large reflector.
Seo, Hyun Ho; Yong, Ki Lyuk; Oh, Shi Hwan; Choi, Hong Taek; Lee, Seon Ho; Yim, Jo Ryeong; Kim, Yong Bok; Lee, Hye Jin, Method for improving maneuverability and controllability by simultaneously applying both reaction wheel-based attitude controller and thruster-based attitude controller.
Guo, Lei; Qiao, Jianzhong; Zhang, Ran; Zhang, Peixi; Zhang, Dafa, Method for refined attitude control based on output feedback for flexible spacecraft.
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