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Composite material X-shaped support structure optimization design method and system for connecting fuel storage tank

A composite material and optimization design technology, applied in design optimization/simulation, constraint-based CAD, instruments, etc., can solve the problems that structural design methods, structural forms and material systems cannot be simply borrowed, and meet lightweight requirements , reduce the difficulty, reduce the effect of structural weight

Active Publication Date: 2020-01-24
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0004] As a new type of structural part in the launch vehicle, the composite material X-shaped support has different structural form and material system than the original metal support, so the structural design method of the original metal support cannot be simply borrowed

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  • Composite material X-shaped support structure optimization design method and system for connecting fuel storage tank
  • Composite material X-shaped support structure optimization design method and system for connecting fuel storage tank
  • Composite material X-shaped support structure optimization design method and system for connecting fuel storage tank

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Embodiment Construction

[0059] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0060] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relationship between the components in a certain posture (as shown in the accompanying drawings). Relative positional relationship, movement conditions, etc., if the specific posture changes, the directional indication will also change accordingly.

[0061] In addition, in t...

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Abstract

The invention discloses a composite material X-shaped support structure optimization design method and system for connecting a fuel storage tank, and the method comprises the steps: firstly determining design parameters according to the structural features of a composite material X-shaped support, and building a parameterized geometric model; carrying out finite element analysis on the integral model containing the fuel storage tank and the composite material X-shaped support, and determining a displacement boundary condition; based on the parameterized geometric model, establishing a finite element model of the composite material X-shaped support, and utilizing an experiment design method to obtain an optimization design variable; establishing an optimization design model based on the parameterized geometric model, the displacement boundary conditions and the optimization design variables, and obtaining optimization design parameters meeting constraint conditions; and finally, based on optimization design parameters and selection of a layering mode, establishing a finite element model based on layering for strength check analysis, and obtaining the composite material X-shaped support structure meeting the strength design requirement. The composite material X-shaped support structure designed by the design method has the advantages of light weight and high strength.

Description

technical field [0001] The invention relates to the technical field of launch vehicle structure design, in particular to a method and system for optimizing the design of a composite material X-shaped support structure used for connecting fuel storage tanks. Background technique [0002] With the rapid increase in the demand for space exploration, the research and development of new launch vehicles has become increasingly urgent. New types of launch vehicles have stricter requirements for lightweight structures, and composite materials have become one of the preferred materials for spacecraft structural parts due to their high specific strength and specific stiffness. A lot of practice has proved that, compared with the metal material structure with the same performance, the application of composite materials in aerospace products can reduce the weight by 10-50%, and the cost can be reduced by 10-20%. [0003] During the entire launch process of the launch vehicle, the compo...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/23G06F111/04G06F119/14
Inventor 王浩刘意鞠苏江大志
Owner NAT UNIV OF DEFENSE TECH
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