Rolling Flex Hinge Antenna Deployment Without Overstretch
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Solution Overview
Problem
Large spaceborne antennas require mechanisms to transition from a compact collapsed form to a fully deployed shape without exceeding the final locked dimension, ensuring no overstretching of components and maintaining precise geometry.
Innovation Solution
The use of a rolling flex hinge system, comprising first and second hinge bodies connected by a flexible strap arrangement and locking linkages with magnets, allows for rotation between stored and deployed positions while locking in place without exceeding the final locked dimension.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If traditional hinges are used to deploy antenna sections, then the antenna can transition from collapsed to deployed form, but the hinge may exceed the final locked dimension causing overstretching of components
Solution Approach 1:
The hinge transitions from a static connection to a dynamic rolling mechanism that adapts its effective length during deployment. The rolling flex hinge bodies allow the connection point to move dynamically, ensuring the deployment dimension increases precisely to the locked dimension without exceeding it, thereby preventing component overstretching while maintaining manufacturing precision.
Solution Approach 2:
The hinge mechanism changes its effective length parameter during deployment through rolling motion. By controlling the rolling distance and incorporating locking linkages with magnets, the system ensures the effective length reaches exactly the locked dimension without overshooting, resolving the contradiction between achieving full deployment and maintaining dimensional accuracy.
2Volume of moving object
If multiple thick panels are folded back and forth, then the antenna can be compacted, but gaps may form between adjacent panels during deployment
Solution Approach 1:
Multiple hinge mechanisms are merged into a synchronized deployment system where all panels fold and unfold together. The rolling flex hinge design ensures that adjacent panels maintain consistent angular relationships during folding, preventing gaps from forming while achieving compact volume when deployed.
Solution Approach 2:
The antenna structure is segmented into multiple deployable panels connected by independent rolling flex hinges. Each hinge operates independently but follows the same rolling mechanism, allowing precise control over panel positioning during folding and deployment, thereby maintaining panel alignment and preventing gaps while achieving compact storage.
3Strength
If the antenna structure is made stiff in deployed shape, then spacecraft maneuvering is enabled, but the deployment mechanism becomes more complex
Solution Approach 1:
The structure transitions from a flexible folded state to a stiff deployed state through dynamic rolling hinge mechanisms. The rolling flex hinges provide the necessary movement during deployment, while the locking linkages with magnets create rigid joints in the deployed configuration, achieving structural stiffness without requiring permanently complex mechanisms.
Solution Approach 2:
The deployment mechanism uses self-locking features where magnets automatically engage the locking linkages when panels reach their deployed position. This self-service locking mechanism creates stiff joints without requiring external actuators or complex control systems, maintaining structural rigidity while minimizing deployment mechanism complexity.
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 solution enables the deployment of antenna sections without gaps and maintains stiffness in the deployed position, preventing overstretching of components and ensuring precise alignment.
Implementation Method 1
a flexible strap arrangement coupling the first hinge body and second hinge body together to permit rolling contact therebetween
Implementation Method 2
Each locking linkage may comprise a first magnet carried by the first linkage, and a second magnet carried by the second linkage. The first and second magnets couple together to lock the first and second hinge bodies when the first and second antenna sections are in the deployed position.
Implementation Method 3
The set screw contacts the dowel pin when the first and second antenna sections are in the deployed position
Data Source
AI summary
A spaceborne antenna for a satellite may include antenna sections for the satellite, and at least one rolling flex hinge rotatably coupling first and second antenna sections together and permitting rotation between a stored position and a deployed position. The first and second antenna sections may be stacked in the stored position and extended in end-to-end relation in the deployed position. The at least one rolling flex hinge may include a first hinge body coupled to an end of the first antenna section, a second hinge body coupled to an end of the second antenna section, and a flexible strap arrangement coupling the first hinge body and second hinge body together to permit rolling contact therebetween. At least one locking linkage may be coupled between the first and second hinge bodies to lock the first and second hinge bodies when the first and second antenna sections are in the deployed position.