Parameter determination method for reducing disturbance of solar wing rotation on satellite laser terminal

By establishing the whole-satellite multidisciplinary electromechanical coupled flexible multibody dynamics and control equations, determining the optimal parameters, and solving the problem of disturbance to the satellite laser terminal caused by the rotation of the dual-axis solar array of a large-inclination satellite, low-cost and rapid satellite attitude optimization was achieved, ensuring the stability of laser communication.

CN116384188BActive Publication Date: 2026-05-26CHINA ACADEMY OF SPACE TECHNOLOGY
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
CHINA ACADEMY OF SPACE TECHNOLOGY
Filing Date
2023-03-30
Publication Date
2026-05-26

AI Technical Summary

Technical Problem

Existing technologies cannot effectively reduce the disturbance impact of the rotation of the dual-axis solar array on satellite laser terminals at large inclination angles, leading to interruption of communication optical links and difficulty in adjusting sensitive parameters.

Method used

The multidisciplinary electromechanical coupled flexible multibody dynamics and control equations of the entire satellite were established. Combined with parameter sensitivity analysis and optimization method, the optimal parameters were determined to reduce the disturbance of the solar array rotation on the satellite attitude.

Benefits of technology

By optimizing the design, the disturbance of the dual-axis solar array rotation on the satellite attitude can be reduced quickly and at low cost, ensuring stable communication of the laser terminal and meeting the high-precision requirements of the inter-satellite link.

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Abstract

A parameter determination method for reducing the disturbance of satellite laser terminals caused by dual-axis solar array rotation is proposed. Addressing the problem of the severe impact of the stepping motion of dual-axis solar arrays on satellite attitude at large inclination angles, a whole-satellite dynamics and control model is established based on the virtual power principle, considering satellite orbital parameters, solar array drive mechanism parameters, solar array structural parameters, and reaction wheels. Optimization methods are then used to optimize key parameters affecting satellite attitude caused by dual-axis solar array rotation, obtaining usable parameters for reducing solar array disturbance. This method can effectively reduce the impact of dual-axis solar array rotation on satellite attitude jitter, lower the development cost of high-precision, high-stability pointing laser payloads on satellites, and improve the on-orbit robustness of such payloads.
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