Satellite Solar Panel Stowage Using Planar Rolled Arrays
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Solution Overview
Problem
Conventional satellite solar panel deployment systems face challenges such as increased deployment faults, bulkiness, and reduced power harvesting due to accordion-style arrangements and mid-point attachments, which can lead to orbital debris and damage.
Innovation Solution
A system with a satellite body featuring a planar rolled solar array configuration, utilizing first-type and second-type hinge mechanisms, and a hold down and release mechanism (HDRM) for secure stowage and controlled deployment, allowing panels to unfold into a linear configuration with reduced components and bulk.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If accordion-style solar panel arrangement is used, then the solar panels can be folded for stowage, but the deployment fault risk increases and orbital debris is generated
Solution Approach 1:
The solar array is divided into multiple individual panels that can be independently deployed. Each panel is attached to the satellite body separately, allowing for controlled deployment of individual panels rather than requiring coordinated movement of the entire array. This segmentation reduces deployment complexity and fault risk.
Solution Approach 2:
Instead of folding panels accordion-style with multiple tie-down mechanisms, the invention uses a single tie-down mechanism that releases to allow panels to unfold in reverse sequence. The panels are constrained during stowage and then released to deploy naturally, inverting the conventional approach of active deployment mechanisms.
2Stability of the object's composition
If multiple tie-down/release mechanisms are used to secure panel edges, then the panels can be securely stowed, but the device bulk increases and deployment complexity increases
Solution Approach 1:
Multiple tie-down functions are merged into a single tie-down mechanism. The mechanism secures both edges of the solar array during stowage and releases both edges simultaneously during deployment. This consolidation reduces the number of separate mechanisms from multiple to one, decreasing bulk and complexity.
Solution Approach 2:
The single tie-down mechanism performs multiple functions: securing the first edge, securing the second edge, and enabling controlled release of both edges. This multi-functional design eliminates the need for separate mechanisms for each edge, reducing overall system complexity.
3Volume of moving object
If mid-point attachment is used for solar array, then the array can be folded against satellite body, but unused volume is created and power harvesting potential is reduced
Solution Approach 1:
The solar array is attached at asymmetric locations - specifically at the edges of the satellite body rather than at the midpoint. This asymmetric attachment allows the panels to be positioned more efficiently in the stowed configuration while maximizing the deployed area, eliminating the unused volume problem associated with mid-point attachment.
Solution Approach 2:
Instead of folding panels inward toward the satellite body center, the invention allows panels to extend outward in a different spatial dimension. The panels are attached at edges and can deploy perpendicular to the satellite body surface, utilizing available space more effectively and increasing the effective harvesting area.
Data Source
AI summary
The disclosed technology includes systems, methods, and mechanism configurations related to satellite solar panels, including stowing arrangements, deployment sequences, special purpose hinges, hold down and release mechanisms, and associated components for controlled deployment of the satellite solar panels.