Response surface based optimization method for single reed structure in novel space deployable hinge

Abstract

The present invention provides a response surface based optimization method for a single reed structure in a novel space deployable hinge. The method comprises: according to an actual operating environment of the single reed structure in the novel space deployable hinge, establishing a simplified mechanical model; performing equivalent processing on constraint and loading modes of the single reed structure; obtaining a first-five-order buckling mode and a buckling load of the structure based on ABAQUS; introducing an initial geometric defect to obtain a load-displacement curve, a critical buckling load and a stress distribution cloud chart of the structure; obtaining an optimization model with the maximum buckling bearing capacity under stress constraint of the structure; realizing explicit expressions of a constraint and an objective function based on a response surface method, checking the precision of fitting and updating the model; and simplifying the optimization model into a standard quadratic programming model, and then solving the model by a sequential quadratic programming method to obtain an optimal result. The present invention provides a reliable stability analysis method for the single reed structure, thereby shortening design cycle of the novel space deployable hinge, improving work efficiency and reducing design costs.

Description

technical field [0001] The invention relates to the selection of the optimal size of a single reed structure in a novel space expandable hinge, which belongs to the design of expandable hinges in aerospace vehicles. Background technique [0002] With the implementation of a series of major aerospace science and technology projects such as deep space exploration, manned spaceflight and large-scale launch vehicles, more and more spacecrafts use space expandable structures to meet their envelope space requirements. Space deployable structures have been widely used in solar panels, satellite antennas, and spaceborne radars. Its working process is as follows: the space deployment structure is fixed in the carrier cabin in a contracted state on the ground to reduce the occupied space; after entering orbit, the ground control system issues instructions to implement the pre-designed deployment action; after all actions are completed, the structure is pressed The command is self-loc...

AI Technical Summary

Problems solved by technology

These types of structures are relatively complicated, and additional locking devices are required

And if there is a problem with one of the components, it will affect the work of the entire organization

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