Semi-active fault-tolerant control of whole-spacecraft vibration isolation platform based on human-simulated intelligent controller

Satellites are suffered from a series of external loads transmitted from the satellites-rocket interface during the launch phase. The satellite can be caused to experience broadband vibration by those loads. Such vibration may lead to the failure of the sensitive precision instruments inside the satellite. The magnetorheological (MR) damper may suffer from failure due to its internal factors or external environmental conditions during its operation. Under such conditions, addressing the broadband vibration requirement of vibration isolation systems and the performance degradation of MR dampers, the fault-tolerant control of the whole satellite vibration isolation with the MR damper as the actuator is studied. A fault-tolerant control method combining adaptive sliding mode control and human-simulated intelligent control (HSIC) is proposed. A semi-active whole-spacecraft vibration isolation dynamic model based on MR damper faults is derived by incorporating fault factor. A sliding mode observer is designed for fault reconstruction, and an adaptive human-simulated sliding mode fault-tolerant control algorithm is proposed in combination with HSIC for reconfiguration. The effectiveness of the adaptive human-simulated sliding mode fault-tolerant control is verified through simulations and experiments. The results show that the addition of fault-tolerant control can compensate for the loss of control force caused by the failure of the MR damper to a certain extent. This study provides a reference for practical application of the whole-spacecraft controllers.