Abstract
This paper solves the problem of attitude consensus for flexible spacecraft formation under actuator failures and saturation constraints. Three insightful distributed consensus control laws are designed based on the Lyapunov’s stability theory and graph theory. The induced oscillations of the spacecraft’s flexible appendages are compensated online with adaptive update parameters. Attitude consensus for the multiple spacecraft system can be achieved with limited information transfer. The modal variables of the flexible appendages are avoided in the distributed controllers in order to reduce the payload of the spacecraft. In addition, the issue of actuator saturation is rejected by applying a switching control scheme. Numerical simulations are performed to demonstrate that the proposed controller can guarantee attitude consensus despite the presence of modeling uncertainties, external disturbances, and simultaneous loss of actuator effectiveness faults and additive faults.
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