Satellite Solar Panel Hold Down Release Mechanism
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Solution Overview
Problem
Conventional satellite solar panel deployment systems face challenges such as increased deployment faults, bulkiness, and reduced power harvesting due to accordion-style arrangements and mid-point attachments, which can lead to orbital debris and inefficient use of launch vehicle space.
Innovation Solution
A system with a satellite body featuring first and second solar arrays attached by corresponding hinge mechanisms, where the arrays are foldable and unrollable, with a hold down and release mechanism (HDRM) allowing controlled deployment from a stowed position to a planar configuration, reducing the need for multiple tie-down mechanisms and optimizing space usage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If accordion-style solar panel arrangement is used, then the solar panels can be stowed compactly against the satellite body, but the deployment reliability decreases due to increased coordination complexity of multiple tie-down mechanisms
Solution Approach 1:
The patent extracts and eliminates the need for multiple tie-down mechanisms by using a single HDRM that secures the entire solar array through a burn wire constraint. This removes the complex coordination requirements between multiple mechanisms while maintaining compact stowage capability.
Solution Approach 2:
The patent combines multiple tie-down functions into a single HDRM mechanism that secures the entire solar array at once. By merging the functions of multiple separate tie-down mechanisms into one unified system, the patent reduces coordination complexity while maintaining deployment reliability.
2Reliability
If multiple tie-down/release mechanisms are used to secure solar panel edges, then the solar panels can be securely restrained, but the device bulk increases and deployment fault risk increases
Solution Approach 1:
The patent combines multiple tie-down mechanisms into a single HDRM that secures the entire solar array. This merging reduces the overall device bulk and eliminates the coordination complexity between multiple mechanisms while maintaining secure restraint through the burn wire constraint.
Solution Approach 2:
The HDRM serves multiple functions simultaneously: it restrains the solar array during launch, provides a clean release mechanism via burn wire severing, and eliminates the need for multiple separate tie-down mechanisms. This multi-functionality reduces device bulk while maintaining restraint security.
3Ease of operation
If mid-point attachment is used for solar arrays, then folding against one side is enabled, but unused volume remains and effective panel size is reduced
Solution Approach 1:
Instead of attaching the solar array at the mid-point and folding against one side, the patent inverts the approach by attaching at the edge and folding against the satellite body. This inversion eliminates unused volume while maintaining folding capability and maximizes the effective panel size.
4Ease of operation
If tie-down mechanisms are released during deployment, then solar panels can unfold, but detached mechanisms may create orbital debris or damage the panel
Solution Approach 1:
The patent replaces the mechanical tie-down mechanism with a burn wire constraint that is severed by resistive heating. This substitution eliminates the need for mechanical release components that could detach and become orbital debris, while maintaining smooth deployment capability.
Solution Approach 2:
The burn wire undergoes a phase transition from solid to molten state through resistive heating, enabling clean severing without mechanical contact. This phase transition provides a debris-free release mechanism that maintains deployment capability while eliminating the risk of detached mechanical components becoming orbital debris.
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 enhances the reliability and efficiency of solar panel deployment, reduces bulk, and maximizes power harvesting by allowing controlled, fault-resistant expansion of solar panels in orbit, while minimizing the risk of debris creation.
Implementation Method 1
a burn wire configured to constrain the first solar array
Implementation Method 2
at least two burn resistors electrically coupled to the circuit board; selective severing of the burn wire by the burn resistors
Data Source
AI summary
The disclosed technology includes systems, methods, and mechanism configurations related to satellite solar panels, including stowing arrangements, deployment sequences, special purpose hinges, hold down and release mechanisms, and associated components for controlled deployment of the satellite solar panels.