Adaptive harmonic disturbance compensation system
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IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/26
B64G-001/36
출원번호
US-0748037
(1996-11-12)
발명자
/ 주소
Goodzeit Neil Evan
Ratan Santosh
출원인 / 주소
Lockheed Martin Corp.
대리인 / 주소
Meise
인용정보
피인용 횟수 :
28인용 특허 :
0
초록▼
A spacecraft (10) carries a solar panel (17) which rotates to follow the sun, and also carries various thrusters (20). Thruster plume impingement on the solar panel affects the torque applied to the spacecraft body (12) in a manner which depends upon solar panel angle. The errors in the thrust durin
A spacecraft (10) carries a solar panel (17) which rotates to follow the sun, and also carries various thrusters (20). Thruster plume impingement on the solar panel affects the torque applied to the spacecraft body (12) in a manner which depends upon solar panel angle. The errors in the thrust during stationkeeping tend to perturb attitude, especially early in the maneuver, because of the delay inherent in the attitude control loop. A torque bias is summed with the residual torque demand signal to correct for the errors in torque. The torque bias signal is generated by a Fourier model of the torques, updated by an adaptive tuning filter, so that successive stationkeeping maneuvers progressively adapt the amplitude and phase of the Fourier coefficients in a manner which tends to minimize the residual torque demand and attitude error. Thus, the torque bias signal automatically approaches the correct value.
대표청구항▼
[ What is claimed is:] [1.] A spacecraft, comprising:a body defining a center of mass, and at least one axis:at least one solar panel rotationally movable relative to said body;attitude sensing means coupled to said body for determining spacecraft attitude and attitude rate about said axis;a source
[ What is claimed is:] [1.] A spacecraft, comprising:a body defining a center of mass, and at least one axis:at least one solar panel rotationally movable relative to said body;attitude sensing means coupled to said body for determining spacecraft attitude and attitude rate about said axis;a source of commanded attitude about said axis;error signal generating means coupled to said source of commanded attitude and to said attitude sensing means, for generating error signals representative of the deviation of said spacecraft attitude from said commanded attitude;processing means including an output port, and also including an input port coupled to said error signal generating means, for processing said error signals in a manner including at least an integrating component, for generating torque demand signals at said output port of said processing means;a plurality of thruster means coupled to said body, at least one of said thruster means being arranged for imparting a thrust along lines of force which do not pass through said center of mass of said body, whereby energization of said at least one of said plurality of thruster means tends to create a torque about said axis, and energization of selected ones of said plurality of said thruster means results in a change in velocity of said body together with unwanted residual torques about said axis;thruster selection logic means coupled to said plurality of thruster means, for receiving thruster drive signals, and for energizing selected ones of said plurality of thruster means in response to said thruster drive signals;velocity change thruster control means coupled to said plurality of thruster means, for energizing selected ones of said thruster means, for nominally imparting only a velocity to said body, but which undesirably tends to impart residual torques attributable to thruster plume impingement on said at least one solar panel;coupling means coupled to said output port of said processing means and to said thruster selection logic means, for receiving said torque demand signals, and for generating said thruster drive signals, said coupling means closing a degenerative feedback loop which tends to operate said thruster means in a manner which reduces said deviation of said attitude from said commanded attitude, whereby operation by said velocity change thruster control means of said selected ones of said thruster means tends to immediately generate said residual torques, which tend to be compensated by said degenerative feedback loop, but with a delay which allows said attitude of said body of said spacecraft to deviate from said commanded attitude about said axis, said coupling means further comprising (a) summing means including a torque bias signal input port and an input port coupled to said output port of said processing means, for summing torque bias signals applied to said torque bias signal input port with said torque demand signals, for thereby generating said thruster drive signals, and (b) torque bias signal generating means coupled to said output port of said processing means and to said torque bias input port of said summing means, said torque bias signal generating means comprising torque bias modeling means coupled to said output port of said processing means for receiving said torque demand signals, and for, in response to solar panel rotational angle, generating signals representing the amplitude and phase of Fourier components representing said torque bias signals.
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