Satellite finite element model equivalent modeling method for multiple loads

By using a multi-point constraint simulation method for screw connections and a load finite element equivalent model, the problems of low computational efficiency and difficulty in achieving both high accuracy in the finite element model of multi-load small satellites are solved. This method enables efficient and convenient finite element model assembly and accuracy matching, and is suitable for rapid iterative design of multi-load small satellites.

CN118839420BActive Publication Date: 2025-10-17CHANGGUANG SATELLITE TECH CO LTD
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Patent Information

Application Number
CN202410910731.3
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2024-07-09
Publication Date
2025-10-17
Estimated Expiration
2044-07-09

AI Technical Summary

Technical Problem

In existing technologies, finite element model processing methods for multi-payload small satellites are difficult to balance computational efficiency, accuracy, and ease of modeling. Especially when there are many payloads and they are of complex types, existing methods suffer from large computational scale, low computational efficiency, poor ease of operation, and difficulty in judging computational accuracy.

Method used

A multi-point constraint simulation screw connection method is adopted to assemble the load finite element physical model with the satellite main structure finite element physical model. By establishing an equivalent finite element model of the load, the degrees of freedom of the load finite element physical model are reduced. The mass and stiffness matrices of the equivalent finite element model are adjusted by modal characteristic equations to achieve accuracy matching with the physical model.

Benefits of technology

It significantly reduces the degrees of freedom of the whole-satellite finite element model of multi-payload small satellites, improves computational efficiency, realizes interaction between different finite element software, ensures computational accuracy and modeling convenience, and meets the needs of rapid iterative design.

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Abstract

The application relates to a multi-load-oriented satellite finite element model equivalent modeling method, which comprises the following steps: establishing a satellite main structure finite element physical model; establishing a load finite element physical model and calculating the modal frequency and the modal vibration mode of the load finite element physical model; establishing a load finite element equivalent model according to the calculation results of the modal frequency and the modal vibration mode of the load finite element physical model; assembling the load finite element physical model and the satellite main structure finite element physical model through multi-point constraint screw connection simulation to obtain a satellite finite element physical model containing the load finite element physical model; and assembling the load finite element equivalent model and the satellite main structure finite element physical model through multi-point constraint screw connection simulation to obtain a satellite finite element hybrid model containing the load finite element equivalent model. The application can be applied to the finite element model simplification modeling of a satellite platform single machine device and is not limited to the finite element model simplification modeling of a load.
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Citation Information

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