Method and system for dynamic calculation test of satellite-rocket coupled multi-body system

Abstract

The present invention provides a dynamic calculation test method and system of a star-rocket coupled multi-body system, including: physical-mechanical model conversion and topology establishment; establishment of transfer matrices and transfer equations for each element, application of topology and supplementary conditions, and assembling into a system The total transfer matrix and total transfer equation of the total transfer matrix, the system is decoupled by proving the orthogonality analysis, and the dynamic characteristics of the satellite-rocket coupling are analyzed through the modal analysis theory to obtain the inherent characteristics of the system; according to the inherent characteristics of the system, the satellite The calculation of the dynamic response of the arrow coupling; through the simulation calculation, the force of the star-arrow joint is obtained, and the force spectrum input conditions of the force limit control are obtained, and the force limit test is carried out. The invention quickly and accurately obtains the dynamic response of the star-rocket coupling, and then obtains the force spectrum of the star-rocket interface, obtains the input conditions of the force-limit vibration test, and can quickly and accurately perform force-limit vibration test verification.

Description

technical field [0001] The invention relates to the technical field of environment simulation, in particular to a method and system for dynamic calculation and test of satellite-rocket coupling multi-body system. Background technique [0002] The dynamic environment of the spacecraft mainly occurs in the launch phase, and although the action time is short, its importance cannot be ignored. During launch and powered flight, satellites must withstand dynamic loads such as vibration, noise, shock, and acceleration caused by various operations such as take-off, interstage (fairing) separation, secondary ignition, shutdown, and orbiting. The above-mentioned dynamic environment will cause structural damage to the spacecraft and its components, such as: damage to electronic components, failure of instruments and equipment due to short circuit or open circuit of electronic circuits, loose connectors and broken brackets, main structure and secondary components of satellites. Structu...

AI Technical Summary

Problems solved by technology

The above-mentioned dynamic environment will cause structural damage to the spacecraft and its components, such as: damage to electronic components, failure of instruments and equipment due to short circuit or open circuit of electronic circuits, loose connectors and broken brackets, main structure and secondary components of satellites. Structural damage or fracture, etc.

The occurrence of these failures may affect the completion of the release mission, and even lead to the failure of the entire flight mission

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