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

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 ...

AI Technical Summary

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 is prone to a large number of wrinkles after unfolding, which will seriously affect the shape accuracy and performance of the space structure

To solve this problem, although the wrinkles can be suppressed by digging holes inside or on the edge of the film, the area of ​​the film will inevitably be reduced

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