Deployable Solar Panel Assembly Single Joint Vibration Control
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Solution Overview
Problem
Satellites face challenges with low-frequency vibration modes interfering with line-of-sight control and energy supply due to the presence of two joints between the satellite and solar generators, which affect stiffness and pointing accuracy, and require additional mass and bulk to reconcile observation and energy recharge missions.
Innovation Solution
A deployable assembly with a single joint, where the main axis of rotation is on a first edge of a panel, and intermediate axes of rotation are on non-adjacent edges, incorporating a servo-control geared motor and prestressing means to control vibrations and maintain optimal orientation towards the sun without excess mass.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If two joints are used between the satellite and solar array (one for deployment, one for orientation), then the solar array can be deployed and oriented towards the sun, but the rigidity of the solar array decreases and vibration control becomes difficult
Solution Approach 1:
The patent combines the deployment and orientation functions into a single joint mechanism. The solar array is deployed and oriented towards the sun using one articulation device with a single rotation axis, eliminating the need for a second orientation joint. This merging of functions maintains solar array rigidity while achieving the required adaptability for sun pointing.
2Use of energy by moving object
If more solar panels are mounted on the satellite to ensure energy supply during observation phase, then energy supply is improved, but the mass and bulk of the satellite increase
Solution Approach 1:
The patent employs a dynamically adjustable solar array that can change its orientation relative to the satellite body. During the observation phase, the solar array is oriented towards the sun to maximize energy capture. This dynamic reconfiguration allows the satellite to maintain energy supply capabilities without requiring excessive solar panel area, thereby controlling satellite mass.
3Use of energy by moving object
If the satellite orients itself towards the sun for energy storage, then energy capture is optimized, but the observation mission is disrupted
Solution Approach 1:
The patent segments the satellite into functionally independent parts: the satellite body that performs observation tasks and the solar array that handles energy capture. The solar array can be independently oriented towards the sun using the single articulation device, while the satellite body maintains its observation orientation. This segmentation allows both energy capture and observation missions to proceed simultaneously without mutual disruption.
Data Source
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AI summary
The present invention relates to a deployable assembly (30) comprising a carrier structure (25), an assembly (20) of panels (21, 22), each of the panels (21, 22) being connected to the adjacent panel by a hinge defining an intermediate axis of rotation, capable of moving from a stored configuration in which the panels (21, 22) are folded on top of each other to a deployed configuration, by rotation of the panels (21, 22) around the respective intermediate axes of rotation, in which the panels are arranged substantially in the same plane, an articulation device (26) defining a principal axis of rotation of the assembly (20) of panels (21, 22) with respect to the carrier structure (25).According to the invention, the assembly (20) of panels (21, 22) is mobile in rotation about the intermediate rotation axes and the main rotation axis to go from the stored configuration to the deployed configuration and the assembly (20) of panels (21, 22) is only mobile in rotation about the main rotation axis in the deployed configuration so as to orient the assembly (20) of panels (21, 22) relative to the supporting structure (25).