Spacecraft Panel Deployment Using Flexible Members
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Solution Overview
Problem
Current deployment systems for satellites face challenges in increasing the size of deployed components without adding weight or requiring more storage space, leading to insufficient power generation from solar panels and communication capabilities, and often fail to deploy panels flatly, affecting energy capture and functionality.
Innovation Solution
A method and apparatus that involve a spacecraft with a deployment system comprising folded panels, flexible members, and an interface system, which moves panels from a folded configuration to a deployed configuration using extended flexible members, allowing for larger panels to be stored and deployed efficiently, reducing weight and storage constraints.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the size of deployed panels is increased to generate more power and provide enhanced communication capabilities, then the power generation and communication capabilities are improved, but the weight and storage space requirements increase
Solution Approach 1:
The panel deployment system is divided into multiple independent flexible members (booms) that can be deployed sequentially. Each flexible member is a separate structural element that supports panel sections, allowing the system to scale power generation capability by deploying individual booms rather than requiring a monolithic large structure, thus managing weight incrementally
Solution Approach 2:
The patent transitions from storing panels in a compact folded state within the satellite body to deploying them in an extended three-dimensional configuration outside the satellite. The flexible members unfold from a stowed position to form a deployed structure that occupies more spatial volume, enabling larger panel surface area without proportionally increasing stored volume requirements
2Adaptability or versatility
If the size of deployed panels is increased to provide enhanced communication capabilities, then the communication capability is improved, but the storage space requirements increase
Solution Approach 1:
The deployment system uses dynamically deployable flexible members that transition from a compact stowed configuration during launch to an extended deployed configuration in orbit. This dynamic transformation allows the communication panels to achieve a large deployed size for enhanced capability while maintaining a small stowed size that fits within the satellite's limited storage space
Solution Approach 2:
The flexible members and panel structures are designed to nest within each other during stowage, with smaller components fitting inside larger ones. This nested configuration minimizes the storage volume required during launch, while the same structures expand to provide large deployed surface areas for communication capabilities
3Device complexity
If traditional deployment systems are used, then the satellite structure is simple, but the panels cannot be deployed flatly, affecting energy capture and functionality
Solution Approach 1:
The patent employs flexible members (booms) as the primary deployment structure instead of rigid traditional mechanisms. These flexible booms can bend and conform during deployment to accommodate the panel structures, allowing the panels to achieve a flat deployed configuration through the flexibility of the supporting members rather than requiring complex rigid positioning mechanisms
Solution Approach 2:
The flexible members are designed to deploy panels to a flat configuration through their own structural properties and deployment mechanics, without requiring additional active control systems or complex positioning mechanisms. The flexibility of the booms allows them to naturally conform to the panel shapes and achieve proper orientation for optimal energy capture
Data Source
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AI summary
A method and an apparatus for deploying a group of panels are described. An apparatus comprises a group of panels in a folded configuration against a side of a spacecraft, a group of flexible members connected to the group of panels, and an interface system associated with the group of panels and the group of flexible members. The interface system is configured to move the group of panels from the folded configuration to a deployed configuration when the group of flexible members is extended from the spacecraft.