Spacecraft fault tolerance control method and verification device for aiming at faults of actuating mechanism

Abstract

The invention relates to a spacecraft fault tolerance control method and a verification device for aiming at faults of an actuating mechanism. The verification device comprises a real-time simulator, an attitude determining module, an attitude control module, an actuating mechanism module, an experiment master control module, a fault injection module, an interference simulating module and a triaxial air floating table. The verification device is a universal verification device. Fault injection of different kinds of actuating mechanisms can be finished through the fault injection module. Furthermore the kind of an attitude control algorithm in the attitude control module is selected through the experiment master control module. A control capability for multiple different types of fault tolerance control methods can be finished for comparative analysis verification. The fault tolerance control method is an H[indefinite] control method, wherein the H[indefinite] control method has an interference inhibition characteristic and is totally ineffective to the actuating mechanism and furthermore has fault tolerance. The spacecraft fault tolerance control method and the verification device can verify effectiveness and engineering practicability of a plurality of interference resistance fault tolerance control methods. The spacecraft fault tolerance control method and the verification device are suitable for ground simulation verification in an aviation spaceflight field. The spacecraft fault tolerance control method and the verification device can be applied on high-precision attitude control of a spacecraft.

Description

technical field [0001] The invention relates to a spacecraft fault-tolerant control method, verification device and verification method for actuator faults. The system involved is a generalized verification device, which can provide different types of faults and provide different types of fault-tolerant control The method provides a comparative analysis and verification platform; the involved fault-tolerant control method has the ability to suppress interference and actuator failure, and can quickly realize reliable control of an attitude control system. The invention belongs to the field of attitude control of spacecraft. Background technique [0002] Due to the high cost of the spacecraft, the basic requirement for the safe operation of the spacecraft is the high reliability of the entire star. According to statistics, in the 30 years from 1957 to 1988, about 140 spacecraft had catastrophic accidents. The economic loss was about 300 million U.S. dollars. In 1999, the succ...

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Problems solved by technology

[0003] The traditional method is to improve the reliability of the system by adopting hardware redundancy, but it also brings about the problem of limited load and complex structural design. Therefore, improving the reliability of the spacecraft attitude system from the algorithm software has gradually become a major issue. An important research direction. There are various existing fault-tolerant control methods, but some fault-tolerant control methods do not consider the disturbance moments such as environmental disturbances in the actual spacecraft system at the same time. In addition, the existing anti-jamming and fault-tolerant methods are a kind of active control method. On the basis of the reliability of the existing spacecraft components has been greatly improved, continuing to use the active fault-tolerant method will bring about complex calculation problems, which will increase the The Burden of Onboard Computers on Spacecraft

[0004] Most of the traditional spacecraft control system verification devices are built for a specific task and model, and a single control method in the loop of the spacecraft control system lacks versatility and universality for scientific research; in addition, the traditional spacecraft The control system test platform has less consideration for interference and failure, and does not fully consider the actual working conditions of the spacecraft system, lacking completeness

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