Abstract The problem of stabilizing the spacecraft orbit attitude was solved analytically for the sixth order model of its rotary motion with the use of the output feedback control synthesis that is based on decomposition of a control object. Numerical simulation data are presented.
Analytical Synthesis of Stabilization Laws for Spacecraft Orbit Attitude Using Information on an Angle and the Full Vector of Angular Velocity
Russian Aeronautics ; 61 , 2 ; 201-211
2018-04-01
11 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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