Method and platform for simulating faults of momentum-bias satellite

Abstract

The invention discloses a method and a platform for simulating faults of a momentum-bias satellite. In the method, a fault simulation functional module is utilized to realize the simulation of the faults of a momentum wheel and a magnetometer. The platform comprises a shafting air-floated platform, a terrestrial magnetism simulator, the momentum wheel, the magnetometer, the fault simulation functional module, an attitude determining and controlling device, an angle measuring device and an orbit model. The invention can achieve the function of simulating the faults of the attitude control system of a momentum-bias small satellite, and can inspect the operational condition and the fault judging and processing abilities of the attitude control software of the attitude control system as well as the emergency treatment measures and the fault coping strategies of the attitude controller of the attitude control system under the condition that the magnetometer and the momentum wheel have multiple faults.

Description

technical field [0001] The invention belongs to the field of satellite failure simulation in spacecraft reliability technology. The invention can be used for component failure simulation of the attitude control system of the bias momentum small satellite, emergency treatment of component failure, feasibility demonstration of the attitude control system scheme and reliability verification of the attitude control software. Background technique [0002] Fault simulation and fault injection is an important link in the development of satellites, and it is also an important means to carry out satellite reliability verification. During the development of the attitude control system scheme, failure analysis and countermeasures are carried out for various possible failures of components. However, whether these analyzes are reasonable and whether the failure response strategies are feasible requires multiple tests on the ground to repeatedly verify the feasibility of the design scheme...

AI Technical Summary

Problems solved by technology

However, based on software fault simulation and fault injection methods, physical components cannot be connected, and functional verification of system electrical performance interface characteristics, fault emergency response capabilities, and coordination of various functional modules cannot be realized in the case of component failures in the attitude control closed-loop loop.

while direct hardware-based fault simulation and fault injection methods cause physical damage to components, which is not advisable for expensive spacecraft equipment

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