Deployable Solar Array Assembly for Low-Volume Stowage
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Solution Overview
Problem
The size and weight constraints of solar arrays in stowed positions for space equipment limit the volume available for other accessories and increase transportation costs, as they require significant space and weight when folded, restricting the payload capacity of vehicles transporting them to space.
Innovation Solution
A solar array design incorporating a combination of rigid composite panels and flexible solar panel modules, with a mast and hinge system that allows for compact stowage and efficient deployment, reducing the volume and weight requirements by arranging modules in a straight line and using cables for tension distribution, while maintaining a large active surface area.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If solar arrays are folded in an accordion-like fashion for stowage, then the solar arrays can be stored during launch and deployment, but the volume and weight constraints increase, limiting payload capacity and increasing transportation costs
Solution Approach 1:
The solar array is divided into multiple rigid composite panels that are hinged together, allowing the array to be segmented for compact stowage during launch and then deployed to form a large flat surface in orbit. Each panel can be independently positioned and secured.
Solution Approach 2:
The solar panels are configured to nest within or against the vehicle body during stowage, with panels arranged in a compact configuration that minimizes the volume occupied during transportation, similar to nested dolls.
2Power
If larger solar arrays are installed to enhance power generation, then more electrical power can be generated, but the volume and weight constraints of stowed position increase, restricting payload capacity
Solution Approach 1:
The solar array transitions from a static compact stowed configuration to a dynamic deployed configuration in orbit. The array can be adjusted and repositioned after deployment to optimize power generation while maintaining a compact stowed volume during launch.
Solution Approach 2:
The solar array utilizes the three-dimensional space available in orbit by deploying panels in multiple dimensions, forming a large flat surface that extends perpendicular to the vehicle body, thereby achieving large power generation capability without proportionally increasing stowed volume.
3Strength
If rigid composite panels are used for solar arrays, then structural strength and stability are improved, but the weight increases compared to flexible panels
Solution Approach 1:
The solar panels utilize rigid composite materials that combine high strength-to-weight ratio properties, providing the necessary structural strength for space deployment while minimizing weight. The composite structure includes multiple layers and reinforcement elements optimized for space applications.
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 reduces the volume and weight of the solar array in the stowed position, allowing for increased payload capacity and enabling larger solar arrays to be installed, which enhances power generation and reduces transportation costs.
Implementation Method 1
The solar arrays may include multiple panels supporting solar cells for generating electrical power
Data Source
AI summary
A solar array may include a first rigid composite solar panel including solar cells secured to a first substrate. The solar array may further include a second rigid composite solar panel including solar cells secured to a second substrate. The solar array may also include solar panel modules including solar cells secured to a flexible sheet of material. The solar panel modules may be coupled between the first composite solar panel and the second composite solar panel. The solar array may be configured to be retained in a stowed arrangement with the solar panel modules between the first rigid composite solar panel and the second rigid composite solar panel. The solar array further configured to be extended with an extendable arm until each of the first rigid composite solar panel, the second rigid composite solar panel and the solar panel modules are arranged in a substantially straight line.