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- W185317154 abstract "A control system is presented for three axis gas jet satellite attitude control employing parabolic switching boundaries with parameters which adapt to a disturbing acceleration estimate in order to achieve a steady state limit cycle of preset amplitude in the arc second region without zero offset, also minimizing fuel consumption and thruster operation frequency. The control law accepts angle error, rate and disturbing acceleration estimates obtained from a third order state estimator with an angle error measurement from a rate integrating gyro and an acceleration input derived from the jet drive. Time optimal recovery from large initial angle errors and rapid response to step changes in disturbing acceleration are achieved. In addition, stable control is obtained with disturbing accelerations approaching the control jet acceleration. A slew control algorithm is incorporated which enables the same control law to be utilized for fuel optimal slewing through unlimited angles, about one axis at a time. Simulation results are presented including demonstration of stochastic performance with gyro and jet noise. The technique has application to scientific spacecraft where precise pointing is required within stringent mass and power limitations. A good example is the application to ESA's EXOSAT spacecraft which carries scientific instruments with ultimate angular accuracies of about 5 arc seconds." @default.
- W185317154 created "2016-06-24" @default.
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- W185317154 date "1979-09-01" @default.
- W185317154 modified "2023-09-25" @default.
- W185317154 title "An Adaptive, High Precision, Gas Jet Satellite Attitude Control System for Microprocessor Implementation" @default.
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- W185317154 doi "https://doi.org/10.1016/s1474-6670(17)65728-8" @default.
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