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Minimum fuel attitude and nutation controller for spinning spacecraft
Minimum fuel attitude and nutation controller for spinning spacecraft
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机译:航天器的最小燃油姿态和章动控制器
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摘要
A method, apparatus, article of manufacture, and a memory structure for controlling an attitude and a nutation of a spacecraft spinning about a first axis. The method comprises the steps of measuring a spacecraft attitude rate 1(t) about a second axis substantially orthogonal to the first axis; generating a rate correction value 1(t)/0, wherein 0 is an inertial nutation frequency of the spinning spacecraft, and is a proportionality factor; determining a spacecraft attitude angle 2(t) about a third axis substantially orthogonal to the first axis and the second axis; generating an error signal e(t) as 2(t)1(t)/0; and applying a torque to rotate the spacecraft along the second axis. The article of manufacture comprises a program storage device storing instructions implementing the instructions described above. The apparatus comprises an attitude rate sensor for measuring the spacecraft attitude rate 1(t) about a second axis substantially orthogonal to the first axis; means for measuring a spacecraft attitude angle 2(t) about a third axis substantially orthogonal to the first axis; a processor, in communication with the attitude rate sensor, for generating an error signal e(t)2(t)1(t)/0, wherein 0 is an inertial nutation frequency of the spinning spacecraft, and a is a proportionality factor; and a torquer for applying a torque to the spacecraft along the second axis in accordance with the generated error signal e(t).
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