Low-Profile SMA Hinge for Galling-Free Solar Panel Deployment
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Solution Overview
Problem
Current solar panel deployment hinges for small satellites in space are prone to cold welding and galling, leading to premature failure in harsh space conditions, limiting the surface area available for solar power collection.
Innovation Solution
A friction-less hinge system utilizing a pre-loaded shape memory alloy wire that provides a torsional biasing force for pivotal deployment, eliminating friction and preventing cold welding and galling by acting as both a connecting element and energy storage component.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional hinges are used for solar panel deployment in space, then the hinge structure provides mechanical support and pivoting motion, but the hinge surfaces suffer from cold welding and galling leading to premature failure
Solution Approach 1:
The patent replaces the traditional mechanical hinge system with a shape memory alloy (SMA) wire-based system. The SMA wire provides the necessary mechanical support and deployment force through its superelastic and shape memory properties, eliminating the need for traditional hinge joints with sliding surfaces that are prone to cold welding and galling in the vacuum of space.
Solution Approach 2:
The patent utilizes the temperature-dependent phase transformation properties of shape memory alloy wires. By controlling the temperature (through electrical heating or passive thermal effects), the SMA wire transitions between austenite and martensite phases, changing its mechanical properties from stiff to flexible, enabling controlled deployment and stowage of solar panels without mechanical contact.
2Area of stationary object
If solar panels are mounted directly onto the spacecraft body, then the structure is simple and compact, but the surface area available for solar power collection is limited by the spacecraft surface area
Solution Approach 1:
The patent divides the solar panel system into separable components: the solar panel array can be deployed away from the spacecraft body using SMA wire mechanisms. This segmentation allows the solar panels to achieve a larger effective collecting area in space while maintaining a compact configuration during launch, resolving the contradiction between surface area and structural simplicity.
3Area of stationary object
If hinge-mounted deployable solar panels are used, then the surface area for solar power collection is increased, but the hinges are susceptible to cold welding and galling in space conditions
Solution Approach 1:
The patent replaces the traditional mechanical hinge system with a shape memory alloy (SMA) wire-based system. The SMA wire provides the necessary mechanical support and deployment force through its superelastic and shape memory properties, eliminating the need for traditional hinge joints with sliding surfaces that are prone to cold welding and galling in the vacuum of space.
Solution Approach 2:
The SMA wire acts as an intermediary element that provides the deployment function without requiring direct mechanical contact between hinge surfaces. The wire transmits force and enables motion through elastic deformation and phase transformation, mediating the deployment process without the harmful friction and adhesion effects that plague traditional hinge systems.
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 hinge system enables robust and reliable deployment of solar panels with increased surface area exposure, maintaining stiffness and reducing the risk of cold welding and galling, thus enhancing the reliability and efficiency of solar power collection in space.
Implementation Method 1
at least one elongated wire may be included which extends through the first and second bores for both coupling the first and second frame portions together for pivoting movement relative to one another, and for providing a torsional biasing force
Implementation Method 2
The torsion of the shape memory alloy material used in the hinge system provides the stored force for deployment of the panel
Data Source
AI summary
The present disclosure relates to a reduced friction torsion component system that makes use of a first frame portion adapted to be coupled to, or integrally formed with, a first object, and forming a first bore, and a second frame portion adapted to be coupled to, or integrally formed with, a second object, and forming a second bore. The two bores are axially aligned and receive at least one elongated hinge component. The elongated hinge component operates to both couple the first and second frame portions together for pivoting movement relative to one another, and also provides a torsional biasing force to enable pivotal deployment from a first position to a second position of one of the first or second frame portions.