Rigid-Framed Flexible Solar Array for Compact Satellite Stowage
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Solution Overview
Problem
Existing solar array technologies for satellites face challenges due to severe packaging, weight, and deployment requirements in space, with many designs being complex, non-rigid, and prone to thermal issues.
Innovation Solution
The proposed solution involves a flexible photovoltaic panel held within a rigid modular frame that applies circumferential force to the panel, using modular expansion members to create radial tension. This configuration allows for self-deploying hinges and a stowage mechanism to stack panels compactly for launch and deploy autonomously in space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If rigid honeycomb panels are used to form solar arrays, then structural rigidity is improved, but weight and packaging complexity worsen
Solution Approach 1:
The patent uses flexible photovoltaic panels instead of rigid honeycomb structures. The flexible panels are mounted on a deployable frame structure that provides rigidity only when deployed, while allowing compact folding during launch. This eliminates the need for heavy rigid honeycomb panels that must maintain structural integrity throughout launch and operation.
Solution Approach 2:
The solar array transitions from a static rigid structure to a dynamic deployable structure. The array is folded compactly during launch and then deployed in space to achieve the required surface area. This dynamic approach allows the structure to be compact when needed and rigid when needed, eliminating the need for continuous rigid support.
2Weight of stationary object
If flexible solar arrays are used to reduce weight, then weight is improved, but structural stability and rigidity worsen
Solution Approach 1:
The array structure is designed to be flexible during launch (folded state) and rigid during operation (deployed state). The deployable frame structure provides the necessary rigidity once deployed, while allowing compact folding for launch. This dynamic behavior resolves the contradiction between flexibility for weight reduction and rigidity for structural stability.
Solution Approach 2:
The solar array is divided into multiple segments or panels that can be folded together during launch and then extended or locked into position when deployed. This segmentation allows the array to be compact during transport while providing a large, rigid surface area when deployed for power generation.
3Volume of moving object
If complex deployment mechanisms are used to achieve compact stowage, then stowage volume is improved, but device complexity worsens
Solution Approach 1:
The solar array panels are nested or folded together in a compact configuration during launch, similar to a nested doll structure. Each panel fits within or alongside the others, achieving maximum compactness without requiring complex mechanical deployment mechanisms. The structure relies on simple hinges and friction-based locking rather than complex actuators.
4Stability of the object's composition
If photovoltaic arrays are made rigid for structural stability, then structural stability is improved, but power-to-weight ratio worsens
Solution Approach 1:
The patent uses flexible photovoltaic panels that are lightweight and can be folded compactly. These flexible panels maintain sufficient structural stability when deployed and locked into position on the deployable frame, while being significantly lighter than rigid honeycomb structures. This improves the power-to-weight ratio while maintaining adequate structural stability for the application.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This arrangement provides high power-to-weight and power-to-stowed-volume ratios, suitable for small to medium-sized satellites, while minimizing thermal issues and enhancing manufacturability and cost-effectiveness.
Implementation Method 1
A second portion of the interconnected modular segments comprises expansion members configured to establish a circumferential force about the frame and apply a radial tension to the flexible photovoltaic panel
Data Source
AI summary
Provided herein are various enhancements for solar panels and photovoltaic array assemblies. In one example, a system includes solar panel assemblies each comprising a frame defining a mounting area formed from modular segments having receiving features configured to accept spline elements that mount a perimeter of a flexible photovoltaic panel into the mounting area and apply a radial tension to the flexible photovoltaic panel. A stowage mechanism is configured to hold the solar panel assemblies in a stacked configuration and comprising a rod assembly disposed through apertures in the frames of each of the solar panel assemblies. A deployment mechanism is configured to deploy the solar panel assemblies from the stacked configuration into a deployed configuration and comprising self-opening hinges attached between selected pairs of the frames.