Essentially passive method for inverting the orientation of a dual spin spacecraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/28
B64G-001/24
출원번호
US-0477274
(1990-02-07)
발명자
/ 주소
Fong Herbert S. (Rancho Palos Verdes CA)
출원인 / 주소
Hughes Aircraft Company (Los Angeles CA 02)
인용정보
피인용 횟수 :
7인용 특허 :
0
초록▼
An essentially passive and “fuel-less”method for inverting the orientation of a preferably nutationally stable, dual spin spacecraft disposed in an inclined orbit, includes the steps of increasing the rotational speed of (i.e., “spinning up”) the spacecraft\s despun platform and decreasing the rotat
An essentially passive and “fuel-less”method for inverting the orientation of a preferably nutationally stable, dual spin spacecraft disposed in an inclined orbit, includes the steps of increasing the rotational speed of (i.e., “spinning up”) the spacecraft\s despun platform and decreasing the rotational speed of (i.e., “spinning down”) the spacecraft\s rotor, to thereby generate, via product of inertia coupling, a transverse torque of sufficient magnitude to temporarily destabilize the spacecraft and cause the spacecraft spin axis, which is the minimum moment of inertia axis of the spacecraft, to diverge and precess through a flat spin orientation and towards a final, inverted orientation, e.g., disposed at a precession angle of 180°relative to the initial orientation of the spacecraft spin axis. Normally, prior to the spacecraft spin axis reaching the final, inverted orientation, the spin axis encounters and is “stuck at”a barrier nutation angle beyond which further precession of the spacecraft spin axis is not possible without the implementation of a final acquisition procedure, which includes the steps of detecting the occurrence of the spin axis reaching the barrier nutation angle, and in response thereto, instituting limit cycle rotational motion of the platform, to thereby render non-secular the rotational motion of the platform, whereby the spacecraft damping system is brought into its pull-in or effective operating range for penetrating the barrier nutation angle, in order to achieve acquisition of the final inverted orientation of the spacecraft spin axis. Limit cycle rotation of the platform is preferably effectuated by way of applying a first and a second series of torquing pulses to the spacecraft despin motor suitable for reducing the rotational speed of the platform, the first series of pulses being of larger magnitude than that of the second series of pulses.
대표청구항▼
A method for at least substantially inverting the orientation of a dual spin spacecraft, the spacecraft including a gyroscopic spinning rotor rotatably coupled via a despin motor and bearing assembly to a despun platform, the spin axis of the spacecraft being its minimum moment of inertia axis, the
A method for at least substantially inverting the orientation of a dual spin spacecraft, the spacecraft including a gyroscopic spinning rotor rotatably coupled via a despin motor and bearing assembly to a despun platform, the spin axis of the spacecraft being its minimum moment of inertia axis, the method including the steps of: determining whether or not said spacecraft is nutationally stable, and practicing the remaining steps only if it is determined that said spacecraft is nutationally stable; controlling said despin motor in such a manner as to accelerate rotation of said despun platform and decelerate rotation of said rotor, to thereby generate, via product of inertia coupling, a transverse torque perpendicular to said spin axis; wherein said transverse torque is of sufficient magnitude to temporarily destabilize said spacecraft and cause said spin axis to diverge and precess towards a flat spin orientation, whereby said spacecraft spin axis becomes the maximum moment of inertia axis of said spacecraft; and, continuing to practice said controlling step, to thereby cause said spacecraft spin axis to precess through said flat spin orientation towards a final, inverted orientation.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허를 인용한 특허 (7)
Cosner Christopher M. ; Matsunami Scott M. ; Behrin David L., Agile, spinning spacecraft with sun-steerable solar cell array and method.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.