A multidisciplinary micro-vibration evaluation and optimization design method and system

Abstract

The invention discloses an optimal design method and system for multidisciplinary micro-vibration evaluation. The method comprises the following steps that: firstly, independently carrying out micro-vibration structure transfer characteristic modeling, micro-vibration source modeling, optical system modeling and control system modeling; then, establishing an integrated model to utilize three methods to carry out micro-vibration performance evaluation; if an evaluation result can not meet performance requirements, carrying out integrated model parameterization; and then, carrying out system-level multidisciplinary optimal design by aiming at a parameterization model to guarantee that general design can meet system requirements. Compared with a traditional method, the method is characterizedin that the influence of a stellate structure and a camera structure for micro-vibration transfer can be comprehensively considered under a situation that a gesture influence is not considered, an improved micro-vibration source mathematical model is used for comprehensively reflecting the dynamic characteristics of the micro-vibration source, optical performance analysis is introduced to directly evaluate the influence of the micro-vibration for the optical performance, three analysis methods can be simultaneously used for evaluation, three results can be mutually supplemented and compared,and the credibility and the effectiveness of the evaluation result are improved.

Description

technical field [0001] The invention relates to a multidisciplinary evaluation method for the impact of various microvibrations related to high-precision optical equipment of spacecraft, and belongs to the field of system-level multidisciplinary comprehensive modeling and analysis. Background technique [0002] Micro-vibration refers to the small amplitude of the spacecraft caused by the normal operation of the equipped equipment (such as high-speed rotating parts such as momentum wheels, stepping parts such as solar wing drive mechanisms, and swinging parts such as infrared camera swing mirrors) during the spacecraft’s orbital operation. reciprocating motion. Micro-vibration source refers to the equipment that causes micro-vibration. The micro-vibration energy is very small, compared with the strain caused by the mechanical environment of the launch section, the micro-vibration is at least one order of magnitude smaller, and will not cause structural damage. In addition t...

AI Technical Summary

Problems solved by technology

③ Difficulty in control: The micro-vibration amplitude is small and the frequency is high, the attitude control system is difficult to measure, and it cannot be controlled in the whole frequency band; in addition, the micro-vibration covers a wide frequency band, and it is basically impossible to control it by one means

[0007] (1) Using the dynamic model of central rigid body + flexible attachment, the transmission and influence of the star structure and camera structure on micro-vibration are not considered;

[0008] (2) The dynamic model of the micro-vibration source only considers the static unbalance and dynamic unbalance of the high-speed rotating parts, and does not consider the dynamic characteristics and harmonic characteristics of the micro-vibration source itself;

[0009] (3) The influence of light transmission is not considered, and only the star attitude angle is used to represent the change of the camera boresight;

[0011] (5) The above methods are only used for the evaluation of certain indicators, and cannot carry out system-level multidisciplinary optimization design

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