Satellite Solar Panel Hinge Mechanism for Reduced Stowage Volume
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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 solar panels attached via first-type hinge mechanisms, secured by second-type hinge mechanisms at the edges, and constrained by a hold down and release mechanism (HDRM) for planar rolling and unrolling, allowing for reduced bulk and improved deployment control.
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 complexity and fault risk increase due to multiple tie-down mechanisms
Solution Approach 1:
The solar array is divided into multiple individual panels that can be independently deployed. Each panel has its own hinge mechanism and can be released separately by individual HDRMs, eliminating the need for complex coordinated release of multiple tie-down mechanisms while maintaining compact stowage capability
Solution Approach 2:
Instead of using tie-down mechanisms to restrain panels during launch and then releasing them, the invention inverts the approach by using HDRMs to actively hold panels in a deployed position and allowing them to fold stowward when released. This reverses the conventional restraint-release paradigm
2Volume of moving object
If solar panels are attached at mid-point of satellite body, then folding against one side is enabled, but unused volume remains and effective panel size is reduced
Solution Approach 1:
The solar panels are attached at the edge regions of the satellite body rather than at the mid-point, utilizing the perimeter dimension of the satellite. This allows panels to be positioned along the edges and folded against adjacent faces, maximizing the use of available satellite surface area while maintaining compact stowage
Solution Approach 2:
Different regions of the satellite body are utilized for different purposes: edge regions are used for solar panel attachment to maximize panel area, while face centers are used for other satellite components. This local optimization ensures that each region serves its most appropriate function
3Reliability
If multiple tie-down/release mechanisms are used to secure panel edges, then panels can be restrained during launch, but device bulk increases and deployment reliability decreases
Solution Approach 1:
The HDRM serves multiple functions: it acts as a hinge mechanism for folding panels, a restraint mechanism during launch, and a deployment actuator in orbit. This multi-functionality eliminates the need for separate tie-down mechanisms, reducing overall device complexity while maintaining or improving reliability through integrated design
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.