航天器姿态控制系统传感器故障诊断方案设计

2019 CAA Symposium on Fault Detection, Supervision and Safety for Technical Processes (SAFEPROCESS) Pub Date : 2019-07-01 DOI:10.1109/SAFEPROCESS45799.2019.9213391

Li-Guo Yuan, Shuyi Wang, Wenjing Liu, Chengrui Liu

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引用次数: 0

摘要

针对由陀螺仪、地球传感器和太阳传感器组成的航天器姿态控制系统传感器分系统，研究了基于观测器的故障检测和故障定位问题，以保证故障诊断结果与执行器故障解耦。给出了航天器姿态控制系统的运动学方程和各种传感器的测量模型。然后将传感器子系统视为一个以陀螺仪输出为输入，地球传感器输出和太阳传感器输出为输出的虚拟系统。在此基础上，根据航天器姿态控制系统的不同轴线设计了不同功能的观测器，并提出了相应的诊断逻辑。最后，通过卫星姿态控制系统的仿真验证了算法的有效性。

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Sensor fault diagnosis scheme design for spacecraft attitude control system

Aiming at the sensor subsystem of spacecraft attitude control system equipped with gyroscopes, earth sensors and sun sensors, the observer-based fault detection and fault location problems are studied to ensure the decoupling of fault diagnosis results with actuator faults. The kinematics equation of spacecraft attitude control system and the measurement model of various sensors are given. Then the sensor subsystem is regarded as a virtual system with gyroscope outputs as input and earth sensor outputs and sun sensor outputs as outputs. On this basis, observers with different functions are designed according to different axes of spacecraft attitude control system, and the diagnostic logic is proposed correspondingly. Finally, the effectiveness of the algorithm is verified by the simulation of the satellite attitude control system.

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2019 CAA Symposium on Fault Detection, Supervision and Safety for Technical Processes (SAFEPROCESS)

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