This paper studies multi-spacecraft system attitude consensus control with model uncertainty, sensor faults and time-varying input delay. Attitude dynamics of the spacecraft is described using Euler angles. Predictor-based state transformation method is proposed to get delay-free system states with delay information unknown. Afterwards, descriptor observer is used to estimate system states and sensor disturbances. Disturbance attenuation controller is designed based on system state estimates. Finally, a simulation example demonstrates the system performance under the designed algorithm.
Attitude Consensus of Multiple Uncertain Spacecraft Systems with Sensor Faults and Input Delay
Lect. Notes Electrical Eng.
International Conference on Guidance, Navigation and Control ; 2024 ; Changsha, China August 09, 2024 - August 11, 2024
2025-03-04
10 pages
Article/Chapter (Book)
Electronic Resource
English
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