Spacecraft double-drum parallel connection structure bearing design method based on multi-constraint conditions

A design method and technology of spacecraft, applied in the field of spacecraft, can solve the problems of wasting volume and weight resources, unable to meet the needs of large volume, large mass and large payload, and optimizing design.

Active Publication Date: 2018-04-27
SHANGHAI AEROSPACE SYST ENG INST
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  • Application Information

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Problems solved by technology

However, this type of design is not optimized according to the actual carrying requirements of the payload, which wastes precious volume and weight res

Method used

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  • Spacecraft double-drum parallel connection structure bearing design method based on multi-constraint conditions
  • Spacecraft double-drum parallel connection structure bearing design method based on multi-constraint conditions
  • Spacecraft double-drum parallel connection structure bearing design method based on multi-constraint conditions

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Embodiment Construction

[0030] The present invention will be further described in detail below through specific embodiments in conjunction with the accompanying drawings.

[0031] This example provides a load-bearing design method for the dual-tube parallel structure of a spacecraft based on multiple constraints. For the convenience of description, the whole of the double-tube parallel structure is called the load-bearing tube. The structural diagram of the load-bearing tube is as follows figure 1 As shown, it includes an outer cylinder 1, an inner cylinder 2 and a supporting structure 3. The tops of the outer cylinder 1 and the inner cylinder 2 are connected in parallel through an upper flange 4 and bolts, and the lower part is connected in parallel through a lower flange 5 and bolts. The supporting structure 3 and the The lower part of the outer cylinder 1 is connected with bolts through the lower flange 5, and the supporting structure 3 connects the outer cylinder 1 and the inner cylinder 2 with o...

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Abstract

The invention provides a spacecraft double-drum parallel connection structure bearing design method based on multi-constraint conditions. The spacecraft double-drum parallel connection structure bearing design method comprises the steps of building a finite element model of a bearing cylinder overall structure; conducting static analysis on the finite element model and extracting maximum stress ofan inner drum and an outer drum; conducting dynamic analysis on the finite element model, and tracking the longitudinal, transverse and torsional first order main frequency of the bearing cylinder overall structure through modal effective factors; with minimizing the bearing cylinder overall structure weight being a target, optimizing and analyzing the bearing cylinder overall structure through stress permission constraint conditions and frequency constraint conditions which are set in advance to obtain the mass of a bearing cylinder; distributing the bearing proportion of the outer drum andthe inner drum to achiecve joint bearing of the outer drum and the inner. Resource configuration and optimization are achieved, and meanwhile, the union of the outer drum and the inner drum can achieve joint bearing of a large effective load.

Description

technical field [0001] The invention relates to the technical field of spacecraft, in particular to a load-bearing design method for a double-tube parallel structure of a spacecraft based on multiple constraint conditions. Background technique [0002] The spacecraft structure platform loaded with large payloads can meet the needs of some special fields. At present, there is no similar spacecraft structure platform for design reference. It is necessary to design an integrated load carrying payload and spacecraft structure platform according to actual needs. A new type of binocular parallel structure scheme. [0003] The large payload has a strong structure and good rigidity, but its volume and mass are large, and its shape is slender, which belongs to the large payload system. The traditional spacecraft design completely separates the payload from the platform structure, and the platform pursues serialization and generalization. One platform can carry multiple types of load...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23G06F2119/06
Inventor 张华刘汉武赵启龙吴松洪亚军柳征勇唐平李东颖
Owner SHANGHAI AEROSPACE SYST ENG INST
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