A high-stiffness deployable large-area flexible solar wing and a method for deploying the same
By employing a phased deployment method involving a linkage support mechanism, deployable C-shaped rod components, and a solar blanket assembly, the problem of insufficient support stiffness in traditional solar arrays is solved, enabling large-area deployment with high support stiffness, which is suitable for high-power astronautical landing probes.
CN122144187APending Publication Date: 2026-06-05BEIJING INST OF SPACECRAFT SYST ENG
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- BEIJING INST OF SPACECRAFT SYST ENG
- Filing Date
- 2025-08-07
- Publication Date
- 2026-06-05
AI Technical Summary
Technical Problem
Traditional solar array structures have low support stiffness, which limits the deployment area of the solar arrays on astronautical landers and cannot meet high power requirements.
Method used
It employs a linkage support mechanism, a deployable C-shaped rod assembly, a deployable solar blanket assembly, and an end support mechanism. By releasing constraints in stages and utilizing gravity, it achieves large-area deployment, forming a simply supported beam structure to improve support stiffness.
Benefits of technology
It achieves large-area deployment with high support stiffness, can be stably deployed on the surface of celestial bodies, meets high power requirements, and has high deployment reliability.
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Smart Images
Figure CN122144187A_ABST
Abstract
The present application discloses a high support stiffness deployable large area flexible solar wing, comprising: a connecting rod support mechanism, a deployable C-shaped rod assembly, a deployable solar blanket assembly, a terminal support mechanism and a compression release mechanism. The present application also discloses a deployment method of the above solar wing, comprising a first stage of deployment: the compression release mechanism is unlocked and released once, the connecting rod support mechanism drives the deployment end of the deployable C-shaped rod assembly to rotate to be parallel to the surface of the celestial body; a second stage of deployment: the deployable C-shaped rod assembly is deployed to a preset length; a third stage of deployment: the compression release mechanism is unlocked and released twice, the deployment end of the deployable C-shaped rod assembly is inclined to the surface of the celestial body until the terminal support mechanism contacts the surface of the celestial body; a fourth stage of deployment: the deployable solar blanket assembly is rolled and deployed along the surface of the deployable C-shaped rod assembly. The solar wing has the characteristics of high stiffness, large area and high reliable deployment, and is suitable for celestial body landing probes with higher power requirements.
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