Calculation method for obtaining antenna arm vibration abatement response

Abstract

The invention discloses a calculation method for obtaining an antenna arm vibration abatement response. According to the antenna arm vibration abatement scheme of a piezoelectric material, the stress of the piezoelectric material is equivalent to an internal moment, and the strain of the piezoelectric material is equivalent to a displacement difference to obtain an analytic coupling calculation model of satellite dynamics, vibration abatement and gesture control. Through the resolving of the model, the antenna vibration frequency response and a time response after vibration abatement can be obtained, the layout analysis of the piezoelectric material on the antenna arm is realized, and the active vibration abatement affect analysis of the antenna arm is realized. An obtained calculation model is a coupling system model which contains the satellite dynamics, the vibration abatement and the gesture control on a top layer, and the cross coupling of each analysis link is fully considered to finish response calculation and also realize the analysis of a vibration transfer mechanism. The stress of the piezoelectric material is equivalent to the internal moment, the strain of the piezoelectric material is equivalent to the displacement difference, and therefore, the method has the advantages of being simple, practical, short in modeling period and convenient in engineering application.

Description

technical field [0001] The invention relates to calculation and analysis of on-orbit vibration suppression of a satellite with a large flexible loop antenna, and belongs to the technical field of microwave remote sensing. Background technique [0002] With the development of my country's aerospace industry and the urgent need of national defense construction, my country is developing a series of new spacecraft such as new electronic reconnaissance satellites, communication satellites and earth observation systems with large antennas. The large flexible and deployable antennas of these spacecraft present typical complex dynamic characteristics such as large flexibility, light weight, weak damping, and nonlinearity, which bring a series of dynamic and control problems to this type of spacecraft. In the future, more and more large-scale deployable antennas will be used on spacecraft, with larger apertures and stricter indicators. Mechanical movements caused by satellite attitud...

AI Technical Summary

Problems solved by technology

For example, the finite element analysis software Abqus is used, but it is mostly suitable for fixed boundary conditions, and it is difficult to apply to floating satellite models, and the obtained model is a simulation model, which can only perform response calculations, and cannot complete vibration mechanism analysis based on analytical models

Therefore, the current analysis lacks a top-level complete system analysis method, and gives an analysis conclusion that is in line with the actual situation of the satellite in orbit.

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