Telescoping Boom Solar Array for Spacecraft Stowage
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Solution Overview
Problem
Existing deployable solar panel systems for spacecraft face challenges in compact stowage and efficient deployment, requiring innovative solutions to minimize mass and maximize power generation while ensuring structural integrity and protection during transit and operation.
Innovation Solution
The design incorporates telescoping booms formed from multiple tubes that nest within each other for stowage and extend end-to-end for deployment, with solar panels secured to these booms, allowing for a protective cover and efficient expansion to maximize surface area, and utilizing pivotable connecting arms for compact stacking and deployment mechanisms.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Area of moving object
If telescoping booms are used to maximize solar panel deployment area, then the solar panel surface area is improved, but the device complexity increases
Solution Approach 1:
The booms are constructed using telescoping tubes that nest within one another during stowage, with each tube containing the next smaller tube. This nesting arrangement allows the booms to be compact when not in use while extending to full length when deployed, thereby achieving large solar panel surface area without proportionally increasing device complexity.
2Volume of moving object
If solar panels are collapsed between booms for compact stowage, then the volume of moving object is improved, but the reliability of protection during transit deteriorates
Solution Approach 1:
The booms are designed to position themselves around the collapsed solar panel in a manner that provides protective cushioning during stowage and transit. The telescoping tube structure and boom configuration create a protective envelope around the solar panel before deployment, preventing damage during launch and transit while maintaining compact volume.
3Weight of moving object
If multiple tubes telescope for boom construction, then the weight of moving object is improved, but the manufacturing precision requirements worsen
Solution Approach 1:
The booms are segmented into multiple telescoping tubes of varying lengths, with each tube being a separate manufacturable component. This segmentation allows for optimized weight distribution and reduced overall boom mass while enabling standard manufacturing processes for each tube segment, thereby balancing weight reduction with manageable manufacturing precision requirements.
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 configuration enables a lightweight, cost-effective, and efficient deployment of large solar panels, minimizing mass moment of inertia and parasitic mass, while providing a protective cover during stowage and maximizing power generation upon deployment.
Implementation Method 1
A solar panel is secured to the first and second booms for receiving solar energy and converting it to electrical power
Data Source
AI summary
A solar panel assembly for a spacecraft includes a bracket and first and second booms each having a first end secured to the bracket and a second end extending away from the bracket. Each boom is formed from a plurality of tubes that telescope between a stowed condition nested within one another and a deployed condition aligned end-to-end with one another. A solar panel is secured to the first and second booms for receiving solar energy and converting the solar energy to electrical power. The solar panel has a stowed condition collapsed between the first and second booms and a deployed condition extending in a plane between the first and second booms.