Hubless Flexible Solar Array for Passive Membrane Deployment
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Solution Overview
Problem
Conventional solar arrays for spacecraft face challenges in packaging, weight, and deployment due to complex hubs and fragile photovoltaic materials, which require additional support and can degrade over time, leading to thermal issues.
Innovation Solution
A hubless, lightweight solar array design featuring a base layer membrane tensioned by a central hoop and supported by a collapsible perimeter structure, allowing for automatic and passive deployment without motors or complex mechanisms, using a flexible base layer with radial folds and a tensioning element to apply circumferential tension for deployment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If complex hub mechanisms with many moving parts are used to deploy solar arrays, then deployment capability is achieved, but device complexity increases and reliability decreases
Solution Approach 1:
The patent removes the complex hub mechanism entirely from the solar array deployment system. Instead of using a central hub with multiple moving parts to unfold the array, the invention employs a simple tensioning element that pulls the solar array panels into deployment position, eliminating the need for complex mechanical hubs while maintaining deployment functionality.
Solution Approach 2:
The solar array deployment system uses a tensioning element that automatically deploys the array without requiring complex control mechanisms. The tensioning element self-regulates the deployment process by applying force to unfold the panels and maintain them in the deployed position, reducing the need for external control systems and complex mechanisms.
2Strength
If foam backer material is used to support fragile photovoltaic materials in stowed configuration, then structural support is provided, but thermal problems occur and material degradation increases over time
Solution Approach 1:
The patent replaces the foam backer material with a deployable structure that does not require long-term thermal management. The solar array is designed to be deployed from a compact stowed configuration using a tensioning element, eliminating the need for foam backer material that would otherwise be required to support fragile photovoltaic materials during stowage. This approach avoids the thermal degradation issues associated with foam materials while providing adequate support during the stowed phase.
3Volume of moving object
If rolled or folded solar arrays are packaged to fit launch vehicle fairing, then compact stowed configuration is achieved, but deployment requirements become more severe
Solution Approach 1:
The solar array is divided into multiple panels that can be folded or rolled into a compact configuration for launch. Each panel is connected in a sequence that allows them to unfold systematically when deployed. The tensioning element applies force to unfold the panels in order, transforming the compact stowed configuration into the deployed array configuration without requiring complex mechanical mechanisms.
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
The solution enables a stiffer, stronger solar array that can withstand high-G missions, maintain thermal performance, and deploy compactly, reducing the need for foam backer materials and minimizing degradation, while providing high power-to-weight and power-to-volume ratios at a lower cost.
Implementation Method 1
a tensioning element configured to apply circumferential tension about a central node of the base layer
Implementation Method 2
a base layer membrane tensioned by a central hoop tension member
Data Source
AI summary
Provided herein are various enhancements for solar arrays and photovoltaic systems for spacecraft, vehicles, and other applications. In one example, an assembly includes a base layer having a generally circular shape and comprising a plurality of gores interspersed by radial folds. The assembly includes a photovoltaic array coupled to the gores, and a tensioning element configured to apply circumferential tension about a central node of the base layer. The assembly includes a structural element disposed about an outer perimeter of the base layer against which the circumferential tension is conveyed for deployment of the base layer from a stowed configuration into a deployed configuration.