Conventional and adaptive attitude control of spacecraft which use control moment gyros (CMG's) as torque sources are discussed. Control laws predicated on the assumption of a linear system are used since the spacecraft equations of motion are formulated in an 'eigenaxis system' so that they are essentially linear during 'slow' maneuvers even if large angles are involved. The overall control schemes are 'optimal' in several senses. Eigenaxis rotations and a weighted pseudo-inverse CMG steering law are used and, in the adaptive case, a Model Reference Adaptive System (MRAS) controller based on Liapunov's Second Method is adopted. To substantiate the theory, digital simulation results obtained using physical parameters of a Large Space Telescope type spacecraft are presented. These results indicate that an adaptive control law is often desirable.
Adaptive spacecraft attitude control utilizing eigenaxis rotations
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1975 ; Pasadena, CA
01.01.1975
Aufsatz (Konferenz)
Keine Angabe
Englisch
Feedback Control Logic for Spacecraft Eigenaxis Rotations Under Slew Rate and Control Constraints
Online Contents | 1995
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