Solar Array Hinge-Lock Mechanism for Low-Shock Deployment
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Solution Overview
Problem
Existing deployable solar arrays on artificial satellites are limited by the space required for hinges and locks, which reduces the area available for photovoltaic cells and do not efficiently manage kinetic energy during deployment.
Innovation Solution
A hinge-locking mechanism that includes a passive release beam and tapered pins to deploy solar panels without motors, maximizing the space for photovoltaic cells and converting kinetic energy into potential energy, while maintaining structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Area of moving object
If traditional hinge and lock mechanisms are used for deployable solar arrays, then the structural integrity during deployment is maintained, but the space required for these mechanisms reduces the area available for photovoltaic cells
Solution Approach 1:
The patent combines the hinge and lock functions into a single integrated hinge-lock mechanism. The hinge body contains a recess that receives a locking pin, which is actuated by a cam surface during deployment. This merging of functions eliminates separate hinge and lock components, reducing the space required on the solar array structure while maintaining both rotational movement and deployment locking capabilities.
Solution Approach 2:
The hinge-lock mechanism serves multiple functions: it acts as a hinge allowing rotational movement during stowage and deployment, and simultaneously functions as a lock that secures the solar array in its deployed position. The cam surface automatically actuates the locking pin during the deployment rotation, providing both movement facilitation and position securing without requiring separate mechanisms.
2Ease of operation
If motors are used to deploy solar panels, then controlled deployment is achieved, but the added complexity and space requirements reduce photovoltaic cell area
Solution Approach 1:
The hinge-lock mechanism is designed to deploy the solar array automatically using stored elastic potential energy from a spring. The spring is compressed during stowage and automatically releases during deployment, driving the cam surface to actuate the locking pin and rotate the solar panel into its deployed position. This self-service mechanism eliminates the need for external motors or complex control systems while maintaining controlled, orderly deployment.
Solution Approach 2:
The spring is pre-compressed during the stowage phase, storing elastic potential energy in advance of deployment. This preliminary action ensures that when deployment is initiated, the stored energy automatically drives the hinge-lock mechanism through the deployment rotation and locking sequence without requiring external power sources or control systems during the actual deployment event.
3Strength
If larger hinges are used to support bigger solar panels, then structural strength is improved, but the kinetic energy during deployment causes potential damage
Solution Approach 1:
The hinge-lock mechanism incorporates a cam surface that gradually actuates the locking pin during the deployment rotation. This cam-driven gradual locking provides a cushioning effect by distributing the locking force over the duration of the rotation rather than applying it abruptly at the end. This beforehand cushioning prevents sudden impacts and kinetic energy damage while the solar panel is being deployed, protecting the structural integrity of larger panels.
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-locking mechanism increases the power generation capacity of solar arrays by minimizing the space taken up by hinges, allowing for more photovoltaic cells and supporting high-power sensors like cameras and telescopes, while reducing potential damage during deployment.
Implementation Method 1
at least one spring operable to exert an extending force to push the tapered pin into a corresponding hinge bore
Implementation Method 2
converting kinetic energy into potential energy, while maintaining structural integrity
Data Source
AI summary
Artificial satellites are dependent on solar arrays to produce the power needed to support the functional components of the satellite. The present invention is directed to a hinge-locking mechanism designed to maximize the photovoltaic real estate of a solar array of an artificial satellite. The hinge-locking mechanism facilitates the deployment of the solar array upon the artificial satellite entering orbit. The hinge-locking mechanism utilizes a tapered pin with an internal spring resting against an asymmetrically oval shaped cam of a common pivot point. The hinge-lock trades kinetic energy of a solar panel for spring compression to permanently lock the solar array in place upon deployment while reducing the shock load and maximizing deployed stiffness.