Embedded VxWorks based satellite attitude and orbit control system fault simulation system and method

Abstract

The invention relates to an embedded VxWorks based satellite attitude and orbit control system fault simulation system and method, which adopts a host computer and a target machine technology to realize a single machine model and a failure mode. The method comprises the following steps. A fault simulation host computer runs the Matlab modeling software, establishes a fault model based on Simulink, and generates a target application under the VxWorks real-time operating system under. A fault simulation target machine, connected with the fault simulation host computer through a network, runs the VxWorks real-time operating system and the target application for fault simulation. A fault injection and instruction control machine, connected with the fault simulation target machine and a satellite mounted single-mode machine respectively for transmitting the failure mode instruction of the single-mode machine to realize the switching between the single-mode simulation serial port of the fault simulation target machine and the real single-mode serial port of the satellite mounted single-mode machine. The system and the method of the invention can carry out fault diagnosis and system reconfiguration tests to improve the fault-tolerant ability of the single-machine hardware and the attitude track working in the failure mode of the satellite attitude control system so as to ensure the safety of the satellite.

Description

technical field [0001] The invention relates to a fault simulation method for a satellite attitude and orbit control system, in particular to a fault simulation method for a satellite attitude and orbit control system based on embedded VxWorks, and belongs to the technical field of satellite simulation. Background technique [0002] As the core of the satellite, the satellite attitude and orbit control system, its performance will directly affect the success of the entire satellite mission; therefore, once a failure occurs, it will often have a serious impact on the entire satellite. Attitude and orbit control system faults will propagate and accumulate in the control system, telemetry diagnosis has delay and incomplete information, and autonomous diagnosis is limited by the spaceborne computer, etc. Therefore, theoretical analysis alone is not enough, and a combination of experimental verification and theory is required approach to explore fault diagnosis and reconstruction...

AI Technical Summary

Problems solved by technology

[0004] 1. Although the physical simulation system that completely adopts a real stand-alone machine is authentic, it is difficult to simulate various failure modes of the control system, and is only suitable for simulating the normal mode of the control system

In order to simulate the failure of control components, artificial destruction must be carried out, and the failure modes that can be simulated are extremely limited. Since the control components on satellites are usually very expensive, it is obvious that the price paid for this is too high and the cost is too high

[0005] 2. The controllability of the simulation process is not high, and real-time switching between the real stand-alone machine and the model is not possible

[0006] 3. The simulation system that completely uses the model for fault simulation has poor simulation fidelity, low real-time requirements, and cannot fully reflect the hardware operation process of the actual sensor and actuator

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