Solar wing and solar wing on-orbit repeated unfolding and folding method

By matching the motor with the elastic component of the scissor mechanism, the flexible solar array can be repeatedly deployed and retracted in orbit multiple times. This solves the problem that the solar array mechanism in the prior art is not suitable for repeated use in orbit, simplifies the locking mechanism, and improves the applicability and flexibility of the solar array.

CN120942586AInactive Publication Date: 2025-11-14BEIJING SHENGFAN TECHNOLOGY CO LTD
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Patent Information

Application Number
CN202511332374.8
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-09-17
Publication Date
2025-11-14
Estimated Expiration
Not applicable · inactive patent

AI Technical Summary

Technical Problem

In the prior art, the deployment and retraction mechanisms of solar arrays are not suitable for in-orbit reuse and require additional locking mechanisms or drive units, which limits the size and applicability of solar arrays.

Method used

By matching the torque provided by the motor with the elastic component of the scissor mechanism, the flexible solar array can be repeatedly deployed and retracted in orbit. Through the cooperation of the parallelogram rods and elastic components of the scissor mechanism, the solar array can be automatically deployed and retracted, avoiding the need for an additional locking mechanism.

Benefits of technology

It enables the flexible solar array to be repeatedly deployed and retracted in orbit multiple times, simplifies the mechanism design, avoids complex locking devices, and improves the applicability and flexibility of the solar array.

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Abstract

The invention provides a solar wing device which is characterized in that one end of a flexible solar panel (6) is wound on a winding drum (3), the other end of the flexible solar panel (6) is connected with a uniform load rod (5), and the uniform load rod (5) is always parallel to a rotating shaft of the winding drum (3); the scissor mechanism (4) is formed by cascading four equal-length rods which form parallelograms when unfolded, the flexible solar panel is unfolded and folded in the bottom end-top end direction, elastic components are arranged at the bending positions of the left end and the right end, opposite to each other, of each parallelogram, and the scissor mechanism is driven by the elastic components to be unfolded. The elastic component enables the scissor mechanism (4) to always keep a force for pushing away the uniform load rod (5), and in the unfolding state or the folding state of the solar blanket, the torque generated by the motor adapts to the elastic force generated by the elastic component. The flexible solar wing can be repeatedly unfolded and folded in orbit for many times.
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