Spacecraft Separation Mechanism Using Dual Fusible Wires
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Solution Overview
Problem
Existing spacecraft separation mechanisms lack efficient and reliable methods for releasing mechanical joints using electrical signals, particularly for separating components like artificial satellites or solar cells from rockets.
Innovation Solution
A separation device utilizing two wires wound around upper and lower separation members that fuse upon electric current application, allowing the members to be displaced and released, accompanied by a trigger device and apparatus fixture separator for controlled separation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single wire is used to band the upper and lower separation members, then the structure is simple, but the separation reliability is insufficient
Solution Approach 1:
The single wire is divided into two separate wires (first wire and second wire) that are wound around the separation members at different positions. This segmentation provides redundant separation paths, ensuring that if one wire fails to separate, the other can still accomplish the separation function, thereby improving reliability while maintaining reasonable structural complexity.
Solution Approach 2:
The two wires are positioned at different locations on the separation members, creating local separation zones. This local quality distribution ensures that separation can occur at multiple points, providing backup separation capability and improving overall separation reliability without significantly increasing device complexity.
2Reliability
If two wires are used to band the separation members, then the separation reliability improves, but the device complexity increases
Solution Approach 1:
Both the first wire and second wire serve the same separation function but are positioned at different locations. This multi-functionality approach allows the system to achieve improved reliability through redundancy while keeping the overall device complexity manageable, as both components perform the same essential function rather than adding different complex subsystems.
Solution Approach 2:
The invention changes the parameter of wire quantity from one to two, and positions them at different locations on the separation members. This parameter change improves separation reliability by providing redundant separation paths, while the systematic arrangement of the two wires keeps the device complexity increase within acceptable limits.
3Manufacturing precision
If the wires are positioned close to each other, then the device structure is compact, but the separation control precision is reduced
Solution Approach 1:
The two wires are positioned at different locations on the separation members, creating distinct local separation zones. This spatial distribution of wires improves separation control precision by enabling localized separation at different positions, while the overall device volume increase is minimized through efficient spatial arrangement of the separation members and wires.
Solution Approach 2:
The wires are arranged in different spatial positions around the separation members, utilizing three-dimensional space effectively. This dimensional arrangement allows the wires to be sufficiently separated for precise control while maintaining a compact overall device volume through optimal spatial configuration.
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
Enables precise and controlled separation of spacecraft components using electrical signals, enhancing reliability and efficiency in space operations.
Implementation Method 1
a first wire wound around the upper separation member and the lower separation member to band the upper separation member and the lower separation member and fused by applying electric current; and a second wire wound around the upper separation member and the lower separation member at a position away from the first wire to band the upper separation member and the lower separation member and fused by applying electric current
Data Source
AI summary
A separation device is a separation device used for a spacecraft to release a mechanical joint by an electrical signal, including: an upper separation member; a lower separation member disposed on the upper separation member; and a first wire and a second wire wound around the upper separation member and the lower separation member and fused by applying electric current. The first wire and the second wire are disposed in the positions so that, in a state where the upper separation member or the lower separation member receives force in a direction away from each other, the upper separation member and the lower separation member are positionally displaced relatively by fusion of one of the first wire and the second wire, and banding by another one of the first wire and the second wire is released.