Universal parameterized configuration design method for spacecraft equipment mounting bracket

A technology of equipment installation and design methods, applied in multi-objective optimization, special data processing applications, and constraint-based CAD, etc., can solve the problems of heavy geometric model modification, unintuitive optimization design results, and high difficulty in configuration design. Achieve the effect of speeding up the product design progress, good standardization, and easy modeling process

Pending Publication Date: 2021-08-20
CHINA ACADEMY OF SPACE TECHNOLOGY
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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 deficiencie

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  • Universal parameterized configuration design method for spacecraft equipment mounting bracket
  • Universal parameterized configuration design method for spacecraft equipment mounting bracket
  • Universal parameterized configuration design method for spacecraft equipment mounting bracket

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Embodiment

[0071] (1) The general parametric configuration design implementation process based on the spacecraft equipment mounting bracket of the present invention is as follows: figure 2 As shown, it mainly includes five steps: determination of support design constraints, division of support functional modules, parametric configuration design of equipment installation modules, parametric configuration design of support installation modules, and parametric configuration design of support modules, as shown in figure 1 .

[0072] (2) A typical spacecraft equipment mounting bracket basic configuration based on the present invention is as follows: image 3 (a), image 3 As shown in (b), the assembled form of the bracket and the equipment is as follows Figure 4 shown.

[0073] (3) Figure 5 The geometric features of the spacecraft equipment mounting bracket in various directions are given. Among them, the F surface is the equipment installation surface (equipment installation module);...

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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...

Claims

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Application Information

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IPC IPC(8): G06F30/17G06F111/04G06F111/06
CPCG06F30/17G06F2111/04G06F2111/06
Inventor 李修峰高令飞刘正山王伟高秀会
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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