Space thin film structure clamp shape optimization design method for restraining creases

A space thin film, optimization design technology, applied in the direction of design optimization/simulation, calculation, special data processing applications, etc., can solve the problems that affect the shape accuracy and performance of the space structure, reduce the area of ​​the thin film, out-of-plane buckling, etc., to achieve effective Facilitate assembly and space expansion, simple fixture configuration, and easy processing and manufacturing

Active Publication Date: 2018-06-08
DALIAN UNIV OF TECH
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Problems solved by technology

However, since the film can hardly withstand the in-plane compressive stress, it is prone to out-of-plane buckling, that is, the wrinkling phenomenon, under external loads.
Physical tests and finite element analysis of the structural form given by the traditional design show that the space film structure

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  • Space thin film structure clamp shape optimization design method for restraining creases
  • Space thin film structure clamp shape optimization design method for restraining creases
  • Space thin film structure clamp shape optimization design method for restraining creases

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Embodiment Construction

[0025] Specific embodiments of the present invention will be described in detail below in conjunction with technical solutions and accompanying drawings.

[0026] In the first step, the shape optimization of the fixture components is performed

[0027] 1.1) Determine the design domain according to the size requirements of the structure and the actual loading situation, and divide the finite element element grid, and establish the finite element model of the membrane structure with clamps. Rigid fixture components were simulated with 1000 times the modulus of elasticity of the membrane. Select some design points on the connection line between the membrane and the fixture, and use B-spline function interpolation to generate the boundary of the fixture and the membrane. figure 1 is the design domain of the space film antenna structure, according to the symmetry of the structure, 11 design points are selected for each fixture, image 3 Design the domain for the solar sail struct...

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Abstract

The invention belongs to the field of aerospace thin film structural design, and provides a space thin film structure clamp shape optimization design method for restraining creases. The problem that aspace thin film structure is prone to creases under the tensile effect of a traditional clamp is solved. On the basis of nonlinear finite element analysis, the loading boundary conditions are changedby optimizing the shape of a clamp, the minimum main stress of units in a thin film area is maximized, the main stress distribution of the thin film is adjusted and controlled, the global optimum design is found through a global optimization algorithm, then a novel clamp with arcuate and inverted-T-shaped boundaries is obtained, and the aim of completely restraining the creases is achieved. The creases in the thin film are restrained, the thin film is not tailored, and it can be ensured that the thin film has sufficiently large working area; the method is suitable for designing the clamp fora space antenna, a solar sail and other space thin film structures, the thin film creases are easily restrained, the structure working performance is ensured, and no manufacturing, launching or running cost is added.

Description

technical field [0001] The invention belongs to the field of aerospace thin film structure design, and relates to a method for optimally designing the shape of a fixture for a space thin film structure. Background technique [0002] Flexible films are widely used in aerospace structures due to their light weight, ability to withstand large deformations, and easy folding / unfolding. The membrane and the unfolding mechanism are connected by a rigid clamp, and tension stress is generated in the membrane surface after being unfolded in space to realize its specific function. However, since the film can hardly withstand in-plane compressive stress, it is prone to out-of-plane buckling, that is, wrinkling, under external loads. Physical tests and finite element analysis of the structural form given by the traditional design show that the space film structure is prone to a large number of wrinkles after unfolding, which will seriously affect the surface accuracy and performance of ...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23G06F30/15G06F2111/10
Inventor 罗阳军邢健亢战李明
Owner DALIAN UNIV OF TECH
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