Deployable Solar Array Using Composite Membrane Tension
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Solution Overview
Problem
Existing solar array deployment methods for spacecraft, particularly for CubeSats, are limited by the size and packaging constraints, and lack sufficient structural rigidity and shielding, making it difficult to apply known methods due to the small size and limited space available.
Innovation Solution
A deployable solar array using a flexible, elongated rectangular sheet composed of a composite laminate with a predetermined pattern of graphite fiber plies that curls into a uniform radius of curvature, providing structural support and stability, and can be automatically deployed from a spool configuration, suitable for small spacecraft like CubeSats.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If rigid panels are used to mount solar cells, then structural rigidity is improved, but packaged volume and mass increase
Solution Approach 1:
The patent replaces rigid panels with a flexible membrane substrate that can be folded or rolled for compact packaging during launch, then deployed to provide a large solar collection area in space. The flexible membrane maintains structural integrity while enabling compact stowage, directly resolving the contradiction between rigidity and packaged volume.
Solution Approach 2:
The patent employs composite material structures for the flexible membrane assembly, combining multiple layers and materials to achieve both flexibility for packaging and sufficient structural rigidity for deployment and operation. This composite approach allows the membrane to withstand structural loads while maintaining compact packability.
2Volume of stationary object
If flexible membranes are used instead of rigid panels, then packaged volume is reduced, but structural rigidity decreases
Solution Approach 1:
The flexible membrane is designed with specific structural characteristics that allow it to provide sufficient rigidity when deployed while maintaining flexibility for compact packaging. The membrane's construction enables it to withstand operational loads without requiring thick rigid panels, thus reducing packaged volume while maintaining necessary strength.
Solution Approach 2:
The patent employs a deployable super-structure that transitions from a compact folded/rolled state during launch to an extended deployed state in space. This dynamic configuration allows the structure to provide maximum structural rigidity when needed for operations while minimizing packaged volume during transport.
3Strength
If a deployable super-structure is added to support flexible membranes, then structural rigidity is improved, but device complexity increases
Solution Approach 1:
The patent integrates the super-structure deployment mechanism with the flexible membrane assembly as a unified system. The super-structure and membrane are combined such that deployment of one facilitates deployment of the other, reducing overall system complexity while maintaining structural rigidity.
Solution Approach 2:
The deployable super-structure is designed to deploy automatically or with minimal actuation, utilizing the deployment force applied to the solar array itself to unfold and position the supporting structure. This self-deploying capability reduces the complexity of separate deployment mechanisms while ensuring structural rigidity is established.
4Strength
If discrete super-structures are used for deployment, then structural support is improved, but shielding and deployment simplicity worsen
Solution Approach 1:
The patent combines the super-structure with the solar array blanket as an integrated assembly rather than separate components. This merging provides continuous structural support and shielding across the entire array while simplifying deployment to a single unified action, eliminating the need for separate deployment mechanisms for discrete structures.
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 compact packaging, reduced mass, and efficient power generation with improved structural rigidity and shielding, allowing for reliable deployment and operation of solar arrays on small spacecraft, such as CubeSats, capable of handling stress and vibration frequencies.
Implementation Method 1
a composite laminate having a predetermined pattern of graphite fiber plies which impart a predefined tension in the planar surface of the sheet so that it curls into a planar sheet with a uniform radius of curvature along its major axis
Implementation Method 2
Solar photovoltaic arrays are commonly used to power spacecraft
Data Source
AI summary
The present disclosure provides, among other things, a deployable solar array comprising: an array of electromagnetic transducer devices such as photovoltaic devices; and a flexible, elongated, rectangular sheet for supporting the array of electromagnetic transducer devices composed of a composite laminate having a predetermined pattern of graphite fiber plies which impart a predefined tension in the planar surface of the sheet so that it curls into a planar sheet with a uniform radius of curvature along its major axis.