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

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...

AI Technical Summary

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 resources. None of the existing mature platforms can meet the large payload carrying requirements of large volume, large mass, and large slenderness ratio.

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