Morphing Modular Solar Array for Spacecraft Deployment
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Solution Overview
Problem
Current solar array technologies are costly, complex, and not modular, failing to optimize mass and volume performance, and are not scalable for smaller spacecraft applications, nor compatible with next-generation solar cells.
Innovation Solution
A Deployable Morphing Modular Solar Array (DMMSA) using a spring-powered Root Staging and Deployment Mechanism (RSDM) that deploys structural elements like daisy petals, increasing stiffness and natural frequency, and featuring Morphing Modular Solar Power Assemblies (DMMSPA) that morph from a flat to a V-configuration for improved performance and reduced manufacturing costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If current solar array technologies are used, then they can provide power for spacecraft, but they are costly, complex, and not modular
Solution Approach 1:
The solar array is divided into multiple modular petal assemblies that can be independently manufactured and assembled. Each petal assembly contains solar cells, structural elements, and deployment mechanisms as separate modules, enabling standardized production and reduced manufacturing complexity while maintaining system functionality.
Solution Approach 2:
The petal assemblies are designed as universal modules that can be used across different solar array configurations and spacecraft applications. The same basic petal assembly design serves multiple functions: power generation, structural support, and deployment, reducing overall system complexity and manufacturing costs.
2Weight of moving object
If current solar array technologies are used, then they can provide power, but they fail to optimize mass and volume performance
Solution Approach 1:
The solar array transitions from a flat two-dimensional panel configuration to a three-dimensional folded petal structure during deployment. This dimensional transformation allows the array to achieve higher power-to-volume ratios by utilizing spatial folding, while maintaining compact stowed volume and reducing overall mass.
Solution Approach 2:
The solar array employs dynamic structural elements that can change configuration between stowed and deployed states. The petal assemblies dynamically unfold and position themselves to optimize sunlight capture while minimizing volume during launch, achieving optimal mass and volume performance for the power output required.
3Adaptability or versatility
If current solar array technologies are used, then they can be deployed, but they are not scalable for smaller spacecraft applications
Solution Approach 1:
The solar array is segmented into discrete petal assemblies that can be selectively deployed based on power requirements. This modular segmentation enables scalability for different spacecraft applications by deploying only the necessary number of petal assemblies, reducing deployment mechanism complexity while maintaining adaptability.
Solution Approach 2:
The deployment mechanism is designed to allow partial deployment of petal assemblies based on mission requirements. This partial action capability enables the system to be scaled for smaller spacecraft by deploying fewer petal assemblies, reducing overall complexity while maintaining the ability to provide sufficient power when needed.
4Adaptability or versatility
If current solar array technologies are used, then they can function, but they are not compatible with next-generation solar cells
Solution Approach 1:
The petal assembly structure is designed as a universal platform that can accommodate various solar cell types and generations. The modular design with standardized mounting interfaces allows easy integration of next-generation solar cells without requiring changes to the overall structure or deployment mechanisms, maintaining ease of manufacture while ensuring compatibility.
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 DMMSA achieves lower costs, improved power-to-volume ratio, and scalability for smaller spacecraft, while being mechanically simple and compatible with future solar cells, enhancing the performance and utility of solar arrays.
Implementation Method 1
Each DMMSPA elastically morphs to a slight V-configuration once deployed. This elastic flexing of the DMMSPA panel to a V cross section increases the area moment of inertia of the panel by orders of magnitude and hence the petal assemblies deployed natural frequency accordingly.
Implementation Method 2
The array is notionally simple, it uses a spring powered Root Staging and Deployment Mechanism (RSDM) that fan deploys structural elements similar to daisy petals that each perform a sequential secondary deployment.
Data Source
AI summary
A Deployable Morphing Modular Solar Array (DMMSA) for deploying Deployable Morphing Modular Solar Power Assemblies (DMMSPAs) from a spacecraft is provided. The DMMSA comprises a Root Staging and Deployment Mechanism (RSDM) mounted to a spacecraft. A plurality of petal assemblies are rotatably secured to the RSDM with each petal assembly having at least DMMSPA secured thereon and each DMMSPA having a slight V-configuration. A launch restraint assembly stacks and sandwiches the petal assemblies prior to deployment with the launch restraint assembly pre-loading each petal assembly's one or more DMMSPA into a substantially flat configuration. Upon release of the launch restraint assembly, the stacked and sandwiched petal assemblies rotate relative to the spacecraft and each petal assemblies DMMSPA elastically morphs from the substantially flat configuration into the slight V-configuration.