Networked Spacecraft Initiation System for Mixed HDRMs
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Solution Overview
Problem
Current spacecraft systems lack a networked initiation system capable of controlling both non-energetic and energetic hold-down and release mechanisms (HDRMs) efficiently, with existing solutions primarily designed for energetic devices only.
Innovation Solution
A networked initiation system that includes a control unit, interface bus, and both non-energetic HDRMs with internal firing capacitors and energetic HDRMs with initiators, allowing for two-way communication and scalable deployment of various HDRMs, including pyro valves, to manage the release of stowed elements on spacecraft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a networked initiation system is designed for both non-energetic and energetic HDRMs, then versatility and adaptability are improved, but device complexity increases due to the need to accommodate different activation mechanisms
Solution Approach 1:
The initiation system employs a universal control unit that can interface with both non-energetic HDRMs (using fuse wire or link wire mechanisms) and energetic HDRMs (using explosive or pyrotechnic mechanisms) through a common interface bus. This multi-functional capability allows a single system to control diverse release mechanisms without requiring separate dedicated systems for each type, thereby improving versatility while managing complexity through standardized interfaces.
2Ease of operation
If traditional separate control systems are used for non-energetic and energetic HDRMs, then device complexity is reduced, but adaptability and ease of operation deteriorate due to inability to uniformly manage different device types
Solution Approach 1:
The control unit is designed with universal control logic that can issue appropriate activation commands to both non-energetic and energetic HDRMs through the interface bus. This unified control approach allows operators to manage diverse HDRM types through a single interface, significantly improving ease of operation while maintaining the ability to adapt to different device requirements through configurable control parameters.
Solution Approach 2:
The interface bus serves as an intermediary communication channel between the control unit and various HDRM types. This mediator component translates control commands into appropriate activation signals for different HDRM technologies, enabling uniform management of diverse devices without requiring complex point-to-point control wiring or multiple specialized control units.
3Ease of manufacture
If existing initiation systems are used, then reliability may be maintained for energetic devices, but productivity and ease of manufacture deteriorate due to lack of integrated solutions for mixed HDRM systems
Solution Approach 1:
The initiation system provides an integrated solution that combines control capabilities for both non-energetic and energetic HDRMs in a single unified architecture. This integration simplifies the manufacturing and deployment process by eliminating the need to design, test, and install separate control systems for different HDRM types, thereby improving ease of manufacture and overall productivity in spacecraft assembly operations.
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 efficient and flexible control of both non-energetic and energetic HDRMs, reducing complexity and weight while allowing for easy addition or removal of devices, enhancing scalability and reliability in spacecraft operations.
Implementation Method 1
A non-energetic HDRM is one that typically utilizes an activation mechanism such as a fuse wire or link wire that heats and weakens on command from a control unit when an amount of electrical current passes through the wire, thereby causing it to melt and break.
Data Source
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AI summary
One aspect of the present invention involves a networked initiation system having one or more non-energetic hold-down and release mechanisms ("HDRMs"), a control unit and an interface bus connected between all of the HDRMs and the control unit. Other aspects of the present invention involve networked initiation systems having one or more of each of non-energetic HDRMs, energetic HDRMs and other (generic) energetic devices. The systems also include a control unit and an interface bus connected between all of the HDRMs and/or energetic devices and the control unit. The system may be used on a spacecraft for holding various elements in place on the spacecraft during launch, and then activating the HDRMs and/or energetic devices at selected points in time after launch to release the elements for movement, e.g., into orbit or beyond.