Satellite Solar Wing Semi-Rigid Panel Vibration Control
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Solution Overview
Problem
Satellite solar generator wings face challenges in increasing their power-to-weight ratio while ensuring safe storage during transport, as existing designs with rigid and semi-rigid panels exhibit undefined vibration behavior during launch, leading to increased mass and costs.
Innovation Solution
A satellite solar generator wing design featuring at least two rigid solar panels and one semi-rigid solar panel, where the semi-rigid panel is decoupled from the rigid panels in the transport position, allowing it to oscillate freely, and coupled via a releaseable coupling unit that maintains a predefined distance, with movement limiters to control vibration amplitudes and stiffening elements for added rigidity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the active area of solar panels is increased to improve power output, then the power-to-weight ratio improves, but the mass to be transported into space increases
Solution Approach 1:
The solar generator wing is divided into multiple individual solar panels (rigid and semi-rigid) that can be folded and stacked together. This segmentation allows the large total active area to be achieved through multiple smaller panels that can be compactly arranged during transport, effectively increasing power output without proportionally increasing transport mass.
Solution Approach 2:
The solar panels are designed to be folded and stacked one on top of another during transport, with the semi-rigid panel nested between two rigid panels. This nesting arrangement minimizes the volume and mass footprint during launch while maintaining the total active area for power generation in the deployed state.
2Strength
If rigid solar panels are used to ensure structural stability, then the structural strength improves, but the weight increases
Solution Approach 1:
The solar generator wing uses a hybrid configuration where only certain panels (the outer panels and panels requiring high stability) are made rigid, while intermediate panels are made semi-rigid. This local application of rigidity provides structural stability only where necessary, reducing the overall weight compared to using entirely rigid panels.
Solution Approach 2:
The invention employs a composite structure combining rigid and semi-rigid panels in a single solar generator wing assembly. This composite approach leverages the high strength-to-weight ratio of rigid panels in critical locations while using lighter semi-rigid panels in less critical areas, optimizing the overall strength-weight balance.
3Weight of moving object
If semi-rigid solar panels are used to reduce weight, then the weight decreases, but the vibration behavior becomes undefined during launch
Solution Approach 1:
A coupling unit acts as an intermediary element that connects the semi-rigid solar panel to the rigid panels during transport. This coupling unit provides vibration damping and stabilization, ensuring predictable vibration behavior during launch while allowing the semi-rigid panel to maintain its weight advantages. The coupling unit mediates between the rigid structure requirements and the lightweight semi-rigid panel.
4Power
If the number of solar panels is increased to expand active area, then the power output increases, but the device complexity increases
Solution Approach 1:
Multiple solar panels are merged into a single folded and stacked assembly that functions as one integrated solar generator wing. The panels are coupled together and folded in a coordinated manner, allowing multiple panels to be managed as a single unit during transport and deployment, thereby reducing operational complexity despite the increased number of panels for higher power output.
Data Source
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Figure 5~6b
AI summary
A satellite solar generator wing (10) is described, comprising at least two rigid solar panels (14, 16) and at least one semi-rigid solar panel (18, 20), which are connected to one another in such a way that the solar panels can assume an operating position and a transport position. In the transport position, the solar panels (14-20) are held one above the other, with the semi-rigid solar panel (18, 20) being freely suspended between the two rigid solar panels (14, 16). Furthermore, a satellite with at least one satellite solar generator wing (10) is described.