Partially Flexible Solar Array Frame for Flat Deployed Panels
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Solution Overview
Problem
Existing solar array structures for satellites face challenges in achieving a lightweight, stiff, strong, and stable design that minimizes on-orbit attitude control disturbances while maintaining efficient power generation, as they need to balance volume and weight during launch and deployment.
Innovation Solution
The use of partially flexible solar array structures with a rectangular frame comprising two opposing rigid axial sides and two opposing flexible cross members, where the solar panels are curved during stowage by compressing the rigid sides and return to a flat configuration upon deployment, eliminating the need for spacers or ribs for stiffness during launch.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If solar array structures use rigid panels to provide strength and stiffness during launch, then structural strength is improved, but weight increases
Solution Approach 1:
The solar array structure transitions from a rigid configuration during launch to a flexible, deployable configuration in orbit. The panels are designed to be flexible enough to fold compactly during launch but can be deployed and stabilized in space, eliminating the need for heavy rigid structures that would otherwise be required to maintain strength throughout the mission.
Solution Approach 2:
The solar array is divided into multiple flexible panels that can be independently folded and deployed. This segmentation allows the structure to be compact during launch while providing sufficient total surface area when deployed, reducing the weight compared to a single large rigid panel.
2Weight of moving object
If solar array structures use thin panels to reduce weight, then weight is reduced, but structural strength deteriorates
Solution Approach 1:
The thin panels are designed to be flexible during launch but can be deployed and stabilized in orbit. The dynamic transition from folded to deployed state allows thin panels to provide sufficient structural strength when needed without the weight penalty of continuously rigid structures.
Solution Approach 2:
The patent employs flexible solar panels that can bend and fold during launch but maintain their integrity and provide structural strength when deployed. These thin flexible panels eliminate the need for heavy spacers or ribs while still providing the required strength for the mission.
3Strength
If solar array structures use spacers or ribs to support thin panels during launch, then structural strength is improved, but device complexity increases
Solution Approach 1:
The flexible panels themselves provide the necessary structural support through their deployment mechanism, eliminating the need for additional spacers or ribs. The panels transition from a folded state during launch to a deployed state in orbit, where they naturally maintain their shape and provide structural strength without extra components.
Solution Approach 2:
The patent removes the need for spacers or ribs by using flexible panels that can be deployed and stabilized without these additional support structures. This extraction of unnecessary components simplifies the overall device while maintaining the required structural strength.
4Volume of moving object
If solar array structures are designed to be compact for launch, then volume is reduced, but the ability to provide a flat stable surface deteriorates
Solution Approach 1:
The solar array structure is designed to be compact and flexible during launch but can be deployed into a stable, flat configuration in orbit. The dynamic transition allows the same structure to satisfy both the volume constraints during launch and the stability requirements during operation.
Solution Approach 2:
The solar array is divided into multiple flexible panels that can be folded compactly during launch but deployed to form a large, stable surface in orbit. This segmentation allows the structure to achieve both compact volume during transport and large stable surface area during operation.
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 design provides a lightweight, efficient, and stable solar array that maximizes power generation by ensuring the panels are flat and directly facing the sun post-deployment, while maintaining structural integrity and torsional rigidity, thus reducing on-orbit attitude control disturbances.
Implementation Method 1
two opposing flexible cross members, where the solar panels are curved during stowage by compressing the rigid sides and return to a flat configuration upon deployment
Data Source
AI summary
A solar array structure, such as for a spacecraft, uses thin solar array panels that, when in a stowed configuration, are stiffened by being bent or curved in one direction to be shaped like a section of a cylinder and placed within a rigid structural frame. As a curved solar panel is not as efficient as a flat panel directly facing the sun, the solar array panels are curved in their stowed configuration for launch only, but flatten after deployment by use of a partially flexible structural frame, where a rectangular frame is made of two opposing rigid sides and two opposing flexible sides, with a thin flexible solar panel attached to rigid sides only. The rigid sides are compressed during stowage to curve the panel before hold-down tensioning. The structure and panels return to their flat free state configuration after release.