作者: Loren I. Slafer , Sibnath Basuthakur
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摘要: A method and system (12) for controlling the attitude of a spacecraft during its transfer orbit using an on-board, stand-alone, three-axes determination control system. The utilizes set on-board sensors to define two independent angular measurements, which will initially identify z-axis orientation from arbitrary after launch vehicle separation. three-axis gyros are then bias calibrated in order measure transverse rates spacecraft. is continously determined by integrating gyro outputs even if Earth or Sun not visible sensor. state estimator model provided determine presence large wobble nutation. also linear combination estimated attitude, rate acceleration states generate commanded increments with pulse-width frequency modulator. modulator seeks linearize inherently non-linear thruster duty cycle.