Universal parameterized configuration design method for spacecraft equipment mounting bracket

Abstract

A universal parameterized configuration design method for a spacecraft equipment mounting bracket comprises the following steps: S1, decomposing functional components of the spacecraft equipment mounting bracket according to functions of the spacecraft equipment mounting bracket; S2, setting a basic configuration of the spacecraft equipment mounting bracket, determining key geometric features of the basic configuration, and extracting size parameters of the key geometric features to obtain a parameterized configuration of the spacecraft equipment mounting bracket; and S3, taking weight reduction as a target, automatically adjusting size parameters to drive the parameterized configuration of the spacecraft equipment mounting bracket to change, and obtaining the lightweight configuration of the spacecraft equipment mounting bracket. The problems of high configuration design difficulty, complex design process, large geometric model modification workload, non-visual optimization design result and the like are solved.

Description

technical field [0001] The invention relates to a configuration design method for a bracket product. Background technique [0002] The mounting bracket of spacecraft equipment is a structural part that provides a suitable installation interface for spacecraft equipment and ensures the realization of its functions. There are many types of brackets on spacecraft, a large number and poor versatility, so there is a strong demand for new research and development of brackets. In addition, most of the brackets are made of metal materials such as aluminum alloy or magnesium alloy, and the total weight is relatively large. The design of the bracket usually requires optimization of weight reduction. [0003] Support structure design is one of the important ways of weight reduction design. At present, the following two design ideas are generally adopted in the structural design of spacecraft equipment supports: (1) Design based on experience, inheriting the existing configuration sch...

AI Technical Summary

Problems solved by technology

[0007] The technical problem to be solved by the present invention is to provide a general parametric configuration design of the spacecraft equipment mounting bracket in response to the design requirements of the spacecraft equipment mounting bracket in the form of an integrated configuration of metal materials and to overcome the deficiencies in the prior art method, provide a general-purpose spacecraft equipment mounting bracket and a set of key features (parameters) that affect the configuration, and solve problems such as high difficulty in configuration design, complex design process, heavy workload in geometric model modification, and unintuitive optimization design results

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