A closed-loop verification system and method for a lunar landing and take-off control system

Abstract

The invention relates to a closed loop verification system and method for a lunar landing and taking off control system, particularly relates to the closed loop verification system and method for thelunar landing and taking off control system with a variable thrust engine, and belongs to the technical field of ground verification of space vehicles. According to the method, simulation of an orbitand attitude control engine is conducted through two working manners of digital simulation and entity simulation, engine signals are collected by a dynamic computer to achieve dynamic driving during the lunar landing and taking off process and provide position and attitude information for on-board equipment, and therefore a closed loop is achieved; the two working manners can be switched accordingto ground verification demands. The closed loop verification method is adopted by the ground verification of a GNC sub system of on-board combination of the third phase of lunar exploration, and a better effect is achieved in the process of systematic closed loop verification; the closed loop system plays an important role in the processes of system fault recognition, regression testing and problem rapid searching and positioning, and the authenticity, sufficiency and testing efficiency of ground verification are improved.

Description

technical field [0001] The invention relates to a closed-loop verification system and method of a lunar landing and take-off control system, in particular to a closed-loop verification system and method of a lunar landing and take-off control system including a variable thrust engine, and belongs to the technical field of spacecraft ground verification. Background technique [0002] According to the requirements of the third phase of the lunar exploration mission, the landing and ascending assembly will softly land on the lunar surface. After the automatic sampling of the moon, the ascending device will use the lander as a platform to take off and return to the orbit around the moon and rendezvous with the orbiting return assembly (orbiter and returner). , to complete the sample transfer. In order to complete the task, three types of engines are configured in the GNC subsystem of the upper assembly, namely, the constant thrust attitude control engine, the 3000N orbital contr...

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Problems solved by technology

[0005] (1) The traditional closed-loop verification method can only simulate the jet duration of the thruster, but cannot simulate the thrust of the variable thrust engine, and cannot realize the closed-loop verification of the lunar soft landing process;

[0006] (2) When simulating the thruster through the serial port or parallel port pulse acquisition method, the thrust and response characteristics of the engine are mainly simulated by digital means, but this method is different from the communication sequence, action response time, thrust establishment time, and There are large differences in design states such as valve action characteristics, the authenticity and reliability of ground verification are poor, and the verification of control systems is insufficient;

[0007] (3) In the traditional verification method, the verification mode is single, and it cannot be selected according to different verification requirements. The adequacy and rapidity of the verification cannot be considered as a whole, and the verification efficiency and effect are poor.

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