Continuous Fixed-Time Sliding Mode Control for Spacecraft with Flexible Appendages

摘要

A continuous fixed-time controller is considered for a spacecraft system with flexible appendages. The system is assumed to be subjected to external nonvanishing disturbance. In contrast to existing solutions for spacecraft with flexible appendages, the proposed method guarantees that the origin is reached in fixed-time, independent of the initial condition. Simulation results are presented to demonstrate the effectiveness of the control structure.