Elastic Roll-Out Solar Array Boom Directional Control
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Solution Overview
Problem
Existing solar array technologies for spacecraft are complex, heavy, and costly due to the use of mechanical components like hinges, motors, and complex deployment mechanisms, which increase weight and reduce reliability, making it difficult to achieve high deployment force margins and efficient power production.
Innovation Solution
A simplified solar array design using a lightweight, one-part tubular rolled boom structure that self-deploys elastically via its own strain energy, eliminating the need for auxiliary actuators and reducing the number of mechanical parts, with a directionally controlled deployment system to ensure predictable and efficient deployment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If mechanical components like hinges, motors, and complex deployment mechanisms are used, then deployment force and reliability are improved, but weight and device complexity increase
Solution Approach 1:
The patent extracts and eliminates complex mechanical deployment mechanisms (motors, hinges, pulleys, springs) from the solar array system. The solution uses a simple pinned connection between rigid panels that allows natural elastic deployment without auxiliary actuators, removing the disturbing complex mechanical parts while maintaining deployment reliability through the inherent flexibility of the pinned joint configuration
Solution Approach 2:
The solar array structure serves itself by using the pinned connections between rigid panels to naturally accommodate thermal expansion and enable deployment without external mechanical actuators. The structure uses its own geometric configuration and material properties rather than relying on separate deployment mechanisms, making the system self-deploying and eliminating the need for complex mechanical service components
2Force
If mechanical components like hinges, motors, and complex deployment mechanisms are used, then deployment force margin is improved, but weight increases
Solution Approach 1:
The patent removes heavy mechanical deployment actuators (motors, springs, cables) from the system. The deployment force is generated naturally by the elastic deformation of the pinned panel structure itself during thermal cycling and deployment, eliminating the need for weighty auxiliary force-generating mechanisms while maintaining sufficient deployment force margin
Solution Approach 2:
The patent changes the fundamental parameter of how deployment force is generated - from active mechanical actuation to passive elastic deformation. By using pinned connections that allow natural flexing and thermal expansion, the system generates deployment force through material and structural parameter changes rather than mechanical force application, significantly reducing weight
3Ease of operation
If rigid panel substrates with hinges and mechanical deployment mechanisms are used, then deployment control is improved, but device complexity and cost increase
Solution Approach 1:
The patent extracts complex mechanical deployment control mechanisms (hinges, latches, actuators) from the system. Deployment control is achieved through the simple pinned connection geometry and the natural elastic response of the rigid panel structure, eliminating the need for complex mechanical control systems while maintaining predictable deployment behavior
Solution Approach 2:
The pinned panel structure controls its own deployment through the geometric constraints and elastic properties of the pinned joints. The structure self-regulates deployment through its inherent mechanical characteristics rather than requiring external control mechanisms, simplifying the system while maintaining operational control
4Volume of moving object
If flexible blanket substrates with complex deployment booms and hubs are used, then stowed volume is reduced, but device complexity and weight increase
Solution Approach 1:
The patent segments the solar array into multiple rigid panels connected by pinned joints, allowing the structure to fold into a compact stowed configuration without requiring complex deployment booms or hubs. The segmented panel structure naturally packs into a small volume while maintaining the simplicity of the pinned connection deployment mechanism
Solution Approach 2:
The patent removes complex deployment boom structures and central hubs from the system. The rigid panel segments with pinned connections self-assemble into the deployed configuration without requiring auxiliary boom structures, reducing device complexity while achieving compact stowed volume through the modular panel segmentation
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 significantly reduces complexity and weight while enhancing reliability and power production efficiency by leveraging internal strain energy for deployment, allowing for straightforward scaling and minimizing the need for additional mechanisms, thus addressing the challenges of high deployment force margins and cost reduction.
Implementation Method 1
The stowed roll is operable for storing elastic strain energy sufficient for powering deployment
Data Source
AI summary
A directionally-controlled roll-out elastically deployable solar array structure is disclosed. The structure includes one or more longitudinal elastic roll out booms that may be closed section or open section to allow for efficient rolled packaging onto a lateral mandrel. A flexible photovoltaic blanket is attached to a tip structure and to a lateral base support structure, but remains uncoupled from the longitudinal booms. The solar array system may be stowed simultaneously into a rolled package comprised of the roll out booms and the flexible planar blanket together, or onto independent rolls. Alternatively, the system may be stowed by rolling the booms, and accordion Z-folding the hinged flexible photovoltaic blanket into a flat stack. Structural deployment is motivated by the elastic strain energy of the roll out booms, and several methods of deployment direction control are provided to ensure a known, controlled, and unidirectional deployment path of the elastically unrolling booms.