Simulation analysis method for unfolding mechanism

Through the expansion mechanism simulation analysis methods, including static simulation, finite element simulation and structural modal frequency simulation, the problem that flexible solar wings are difficult to verify their functions and performance in the expanded state is solved, ensuring that their performance under different load conditions meets the design requirements.

CN119740421AInactive Publication Date: 2025-04-01深圳市魔方卫星科技有限公司
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Patent Information

Application Number
CN202411675656.3
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-11-22
Publication Date
2025-04-01
Estimated Expiration
Not applicable · inactive patent

AI Technical Summary

Technical Problem

In the flexible solar wings, it is difficult to verify whether their functions and performance really meet the index requirements, especially when affected by external and internal loads.

Method used

The expansion mechanism simulation analysis method is used, including external load static simulation, internal load static simulation, finite element simulation, displacement and stress cloud map observation, and structural mode frequency simulation, to verify the performance of the flexible solar wing.

Benefits of technology

Through simulation analysis, we ensure that the maximum stress and maximum displacement of the flexible solar wing under different load conditions meet the design requirements and meet the stiffness and performance indicators, and then verify whether its functions and performance meet the standards.

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Abstract

The invention discloses a simulation analysis method for an unfolding mechanism in the technical field of flexible solar wings, and the method comprises the following steps: S1, external load statics simulation: carrying out the statics simulation of an inertial load caused by the movement of a spacecraft in a complete unfolding state of a flexible solar wing, internal load statics simulation: statics simulation is carried out on the tensioning force applied to the constant force spring in the tensioning state when the flexible solar wing is in the completely unfolded state; finite element simulation: performing finite element simulation by using software, fixing a base of the flexible solar wing, and arranging spring constraints at four corners of the flexible solar wing, according to the unfolding mechanism simulation analysis method, in a complete unfolding state of the flexible solar wing, an external load is mainly an inertial load caused by movement of a spacecraft, and the space between the flexible solar wing and the base is smaller than the space between the flexible solar wing and the base. The internal load is mainly tensile force applied by a constant force spring of the tensioning module, a series of simulation can be performed on the flexible solar wing by applying a simulation analysis method, and whether the function and the performance of the flexible solar wing can meet index requirements or not is verified.
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