Triangular Gore Solar Array Hub Deployment Mechanism
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Solution Overview
Problem
Solar arrays for spacecraft require a balance between minimal volume and weight during launch and maximum surface area and stiffness after deployment, which existing technologies struggle to achieve effectively.
Innovation Solution
A solar array design featuring triangular gores with a hub assembly that rotates during deployment, utilizing split timing gears, watchband connections, and tension cables to ensure stability and stiffness while minimizing volume and mass, and incorporating flex circuit power harnesses for efficient current collection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If a multi-panel solar array with triangular gores is folded for deployment about a hub, then the deployed area and deployed stiffness are maximized, but the volume and weight during launch increase
Solution Approach 1:
The solar array gores are nested within a cylindrical canister during launch, with each gore folded and stacked inside the canister volume. The spars and brackets are also contained within the canister, creating a compact nested configuration that minimizes launch volume while enabling full deployment later
Solution Approach 2:
The solar array transitions from a static folded configuration during launch to a dynamic deployed configuration in space. The hub assembly allows the gores to rotate and unfold, transforming the structure from a compact cylinder to a large flat array, enabling stiffness optimization at the operational phase
2Area of stationary object
If a multi-panel solar array with triangular gores is folded for deployment about a hub, then the deployed area is maximized, but the weight for launch increases
Solution Approach 1:
The solar array uses thin flexible gore structures that can be folded and stored compactly but provide large deployed area. The thin film nature of the gores reduces material weight while maintaining the required surface area for solar cell attachment and light capture
Solution Approach 2:
The compact nested storage configuration within the canister reduces the amount of structural material needed for the launch vehicle integration, thereby reducing overall launch weight while preserving the large deployed area capability
3Volume of moving object
If rectangular solar blankets are folded in an accordion arrangement, then the stowed volume is minimized, but the deployed stiffness decreases
Solution Approach 1:
The solar array is segmented into multiple triangular gores that are attached to a central hub, allowing each segment to be independently folded and stored while maintaining structural integrity. This segmentation enables compact stowing without compromising the overall deployed stiffness of the complete array
Solution Approach 2:
The accordion-folded gores transition dynamically from a compact folded state to a taut deployed state, where tension cables and spars provide structural support. The dynamic transformation allows the structure to achieve high stiffness in the deployed configuration while maintaining minimal volume during storage
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 design allows for reliable, efficient deployment with increased structural load capacity and stiffness, maintaining minimal volume and mass while maximizing surface area for current generation, and providing a stable structure for spacecraft power generation.
Implementation Method 1
Solar arrays are used for space vehicles and satellites to generate current for power. The capacity of the solar array to produce current is directly related to the exposed surface area of the array having solar cells thereon.
Data Source
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AI summary
A solar array including a solar array assembly, hub assembly, and wing assembly.