Rocket-spacecraft coupling multibody system dynamics calculation test method and system

Abstract

The invention provides a rocket-spacecraft coupling multibody system dynamics calculation test method and system. The method comprises steps that physical mechanics model transformation and topological structure construction are performed; transfer matrixes and transfer equations of various components are established, a topological structure and supplementary conditions are utilized, a total transfer matrix and a total transfer equation of the system are obtained through assembling, the system is decoupled through proving orthogonality analysis, the modal analysis theory is utilized to analyzerocket-spacecraft coupling dynamics characteristics, and inherent characteristics of the system are obtained; according to the inherent characteristics of the system, rocket-spacecraft coupling dynamics response calculation is performed; through simulation calculation, the rocket-spacecraft connected interface force condition is obtained, the force spectrum input conditions of force limit controlare obtained, and the force limit test is performed. The method is advantaged in that the rocket-spacecraft coupling dynamics response is quickly and accurately obtained, the rocket-spacecraft interface force spectrum is obtained, the input conditions of the force limit vibration test is obtained, and the force limit vibration test can be quickly and accurately verified.

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

Images