Abstract
Aiming at strong coupling and nonlinear dynamic equations for a space-based observation satellite, a sliding mode controller with feed-forward compensation is proposed in this paper. The theorem of moment of momentum is applied to formulate the exact nonlinear dynamic equations of a multibody satellite. On this basis, sliding-mode control-based, dual-loop forward-feed compensation control is used to control the attitude of the space-based observation microsatellite. By comparing with the conventional control method, simulation results demonstrate that the proposed control method has superior performance in terms of suppression from external disturbances and vibration. Better dynamic and static performance indices than the conventional control method are achieved.
Highlights
Space observation systems consist of two parts, that is, the space- and ground-based space observation systems
The latter is subject to atmospheric propagation jitter, astronomical refraction, ionosphere scintillation, and limits of national boundaries
Space-based observation is an important direction of future space target detection
Summary
Space observation systems consist of two parts, that is, the space- and ground-based space observation systems. The latter is subject to atmospheric propagation jitter, astronomical refraction, ionosphere scintillation, and limits of national boundaries. Space-based observation techniques can effectively solve such problems and have the advantages of flexible maneuverability, wide monitoring ranges, long-distance observation, and so forth. Space-based observation is an important direction of future space target detection. Space-based observation satellites contain rotating rigid parts and flexible appendages. The rotation of rigid parts, elastic vibration of flexible appendages, and motion of satellite attitude influence each other, comprising
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