A method for extracting spacecraft interface forces and conducting force limit tests based on the least squares method.

By using a least squares-based method and utilizing the current and voltage information of the moving coil of the vibration table, the interfacial force of the spacecraft can be indirectly extracted. This solves the problem of measuring interfacial force parameters in vibration tests of large spacecraft products, reduces costs, and ensures product safety.

CN116735127BActive Publication Date: 2026-06-30BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Patent Information

Application Number
CN202310732015.6
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2023-06-20
Publication Date
2026-06-30
Estimated Expiration
2043-06-20

AI Technical Summary

Technical Problem

Existing technologies cannot effectively measure interfacial force parameters in spacecraft force limit tests, especially in vibration tests of large spacecraft products, and the experimental costs are high.

Method used

By employing a least squares-based method, utilizing the current and voltage information of the moving coil on the vibration table, and through multiple random vibration tests and the least squares method, the load force to load current ratio and the moving coil admittance coefficient are calculated, thereby indirectly extracting the spacecraft interface force and reducing experimental costs.

Benefits of technology

It enables the measurement of interfacial force parameters without the aid of a measuring device, has a wide analysis frequency range, reduces the cost of spacecraft force limit testing, meets the quantitative requirements of interfacial forces, alleviates overtesting, and ensures the safety of spacecraft products.

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Abstract

This invention provides a spacecraft interface force extraction and force limit testing method based on the least squares method, applicable to a spacecraft vibration testing system. The testing system includes a vibration table, an extended table surface or horizontal slide, test fixtures, a signal conditioner, a vibration controller, a power amplifier, a vibration table oil pump, a cooling unit, and an external circulating water system. The testing method comprises fourteen steps. This invention's method analyzes a wide frequency range, reduces the cost of spacecraft force limit testing, meets the engineering application requirements for quantifying interface forces, effectively mitigates overtesting in spacecraft vibration testing, and ensures the safety of spacecraft products and equipment operation.
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