In this paper evaluate the robustness of an attractive Attitude Control System (ACS) scheme, which has recently been proposed using theta-D control design technique to maintain the satellite pointing accuracy subject to loss of two reaction wheels out of its four wheels assembly mounted in pyramid configuration. It will be employed as an adaptive control strategy for handling Reaction Wheels (RW) failure. Three axis stabilization with two remaining RWs is achieved in these missions via the integration of other torque generating device. The high fidelity reaction wheel model and 3 degree of freedom attitude dynamics are used in the simulation to demonstrate the robust performance characteristics of the based adaptive controller where the baseline PID controller fails to provide sufficient robustness
Nonlinear optimal control of spacecraft Attitude Control with Reaction Wheel failure
2013-06-01
1317464 byte
Conference paper
Electronic Resource
English
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