Six-degree-of-freedom distributed semi-physical simulation method and system of launch vehicle

Abstract

The invention discloses a six-degree-of-freedom distributed semi-physical simulation method of a launch vehicle. The method comprises: S1, establishing a six-degree-of-freedom distributed semi-physical model of a launch vehicle and establishing simulation models for all modules in the model; S2, according to an input and output relationship between all modules in the six-degree-of-freedom distributed semi-physical model of a launch vehicle, erecting a six-degree-of-freedom distributed semi-physical simulation system of the launch vehicle; and S3, establishing a test flow of the six-degree-of-freedom distributed semi-physical simulation system of the launch vehicle, operating the six-degree-of-freedom distributed semi-physical simulation system of the launch vehicle, simulating six-degree-of-freedom data of flight of the launch vehicle so as to complete six-degree-of-freedom distributed semi-physical simulation of the launch vehicle. In addition, the invention also discloses a simulation system. Therefore, the motion rule and characteristics of the conveyer can be reproduced vividly and comprehensively; and the correctness, parameter coordination, interference adaptability, and flight software reliability of the control system plan can be checked.

Description

technical field [0001] The invention relates to the technical field of six-degree-of-freedom semi-physical simulation of a launch vehicle, in particular to a six-degree-of-freedom distributed semi-physical simulation method and system for a launch vehicle. Background technique [0002] The traditional method of the simulation technology of the launch vehicle control system adopts the separate three-degree-of-freedom simulation, that is, the guidance system simulation with the center-of-mass motion as the object and the attitude control system simulation with the center-of-mass motion as the object. In the case of small disturbances and small deviations, the coupling between the guidance system and the attitude control system is not serious, and can be designed and simulated independently. With the increasing complexity of space transport vehicles, the improvement of guidance accuracy requirements, and the application of explicit guidance such as iterative guidance, transport...

AI Technical Summary

Problems solved by technology

With the increasing complexity of space transport vehicles, the improvement of guidance accuracy requirements, and the application of explicit guidance such as iterative guidance, transport vehicles will face large attitudes, large disturbances, and serious attitude-orbit coupling problems during flight.

The guidance system uses the ballistic parameters measured in real time by the navigation system to guide the ballistic deviation caused by various disturbances and control the shutdown point to make the rocket shoot to the target with precision. The attitude control realizes the center of mass motion control by adjusting the thrust according to the guidance and guidance instructions. , because the guidance signal cannot be accurately estimated, the traditional test method for the adaptability of the attitude control system to the iterative guidance cannot be assessed

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