Aeronautics and astronautics – Spacecraft – Attitude control
Patent
1992-12-18
1995-09-26
Kashnikow, Andres
Aeronautics and astronautics
Spacecraft
Attitude control
244165, 244171, 244176, 364434, B64G 126, B64G 128, B64G 140
Patent
active
054528690
ABSTRACT:
A method and system (12) for controlling the attitude of a spacecraft during its transfer orbit using an on-board, stand-alone, three-axes attitude determination and control system. The system utilizes a set of on-board sensors to define two independent angular measurements, which will initially identify the z-axis orientation of the spacecraft from an arbitrary attitude after launch vehicle separation. A set of three-axis gyros are then bias calibrated in order to measure the transverse rates of the spacecraft. The three-axis attitude of the spacecraft is continously determined by integrating the gyro outputs even if the Earth or Sun is not visible by an on-board sensor. A state estimator model is provided to determine the three-axis attitude of the spacecraft in the presence of large wobble and nutation. The system also utilizes a linear combination of the estimated attitude, rate and acceleration states to generate commanded rate increments with a pulse-width frequency modulator. The pulse-width frequency modulator seeks to linearize the inherently non-linear thruster duty cycle.
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Basuthakur Sibnath
Slafer Loren I.
Denson-Low W. K.
Gudmestad Terje
Hughes Aircraft Company
Kashnikow Andres
Mojica Virna Lissi
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