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Pipe hinge space deployable structure optimization design method considering composite material damage

A composite material and optimization design technology, applied in computer-aided design, design optimization/simulation, calculation, etc., can solve problems such as composite material damage, fracture failure, etc., to improve work efficiency, save design costs, and achieve accurate and fast mechanical properties Effect

Pending Publication Date: 2019-07-09
BEIJING UNIV OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, since the fiber is an elastic and brittle material, it is prone to fracture and failure during the large deformation process, which may cause damage to the composite material

Method used

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  • Pipe hinge space deployable structure optimization design method considering composite material damage
  • Pipe hinge space deployable structure optimization design method considering composite material damage
  • Pipe hinge space deployable structure optimization design method considering composite material damage

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0047] In the first step, the geometric model of the tube hinge space deployable structure is established as figure 1 As shown in Fig. 1, the cylindrical shell model is established by means of rotation, and then the groove in the middle of the pipe hinge is cut out by extruding and cutting.

[0048] In the second step, use the modeling software TexGen to establish the microstructure of the unit cell of the woven material, and define the yarn path, shape, size, fiber and matrix parameters, etc. Import the model into Abaqus for finite element analysis, and calculate equivalent material properties and failure parameters after homogenization.

[0049] The third step is to establish a finite element model according to the actual working conditions of the pipe hinge, such as figure 2 shown. The parts at both ends of the pipe hinge are divided into clamping parts, and two reference points RP-1 and RP-2 are established at the center position, and the reference point and the clampin...

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Abstract

The invention provides a pipe hinge space deployable structure optimization design method considering composite material damage. The method comprises the following steps: establishing a finite elementmodel of a pipe hinge space deployable structure; obtaining equivalent material performance and failure parameters by utilizing material homogenization; performing simulation analysis on folding of the pipe hinge to obtain a ppipe hinge bending moment-turn angle curve and a damage factor; establishing a parameter optimization model which takes strain energy as a target, takes the thickness, the groove length and the groove width of the pipe hinge as design variables and takes a material damage factor as a constraint; constructing an objective function and a response surface of the constraintfunction based on a response surface method, and realizing explicit representation of the constraint and the objective function; solving results by using genetic algorithms. The problem that the composite material pipe hinge loses efficacy in the folding process is considered, the design period of the space deployable structure of the pipe hinge is shortened in an optimized mode, the working efficiency is improved, and the design cost is saved.

Description

technical field [0001] The invention relates to the selection of the optimal size of a novel tubular space expandable structure, which is suitable for space expandable structures in aerospace vehicles. Background technique [0002] The space deployable structure is a brand-new aerospace structure product, which has the characteristics of high reliability and long life. It is the core device for the deployment of solar panels. When it enters the space orbit, the ground control system issues instructions to make it perform pre-designed deployment actions. After all the actions are completed, the structure will lock itself according to the instructions and maintain the unfolded working state. . These include the deployable structure with spring hinge, which is a new type of deployable structure. The core component is a spring unit, which is a thin-walled cylindrical shell structure. It can use the elastic strain energy accumulated during folding to realize the automatic unfold...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23
Inventor 叶红玲李博文史雪松张洋
Owner BEIJING UNIV OF TECH
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