Manifold Plenum Initiators for Selective Rocket Motor Ignition
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Solution Overview
Problem
Multi-motor thrust systems face challenges when the thrust system cannot be centered, and require complex ignition timing and thrust balancing for successful launch, particularly in non-centerline installations.
Innovation Solution
A propulsion system with a manifold having multiple plenums, where initiators are coupled to respective plenums to selectively ignite different combinations of rocket motors, allowing for flexible and balanced thrust distribution, including the use of annular and non-annular plenums with insulators and ignition material.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple initiators are used for multi-motor ignition, then ignition capability is improved, but system complexity increases due to complex ignition timing and thrust balancing requirements
Solution Approach 1:
The ignition system is segmented into multiple independent plenums, each capable of being activated by its own initiator. This allows selective ignition of different motor combinations without requiring complex coordinated timing across all motors, as each plenum operates independently to ignite its associated motors.
Solution Approach 2:
The system provides dynamic ignition control by enabling different combinations of motors to be ignited through selective activation of plenums. This dynamic capability allows the system to adapt thrust output to varying operational requirements without increasing ignition system complexity.
2Adaptability or versatility
If multi-motor thrust systems are used for non-centerline installations, then thrust flexibility is improved, but thrust balancing becomes more difficult
Solution Approach 1:
The thrust system is divided into multiple independently controllable motor groups, each associated with a specific plenum. This segmentation allows selective activation of motor combinations to achieve balanced thrust for non-centerline installations, simplifying the operation by enabling straightforward selection of appropriate motor groups rather than complex balancing procedures.
Solution Approach 2:
Different plenums can be activated to provide locally optimized thrust distribution. For non-centerline installations, specific plenums can be selected to ignite motors positioned to achieve the desired thrust balance, making the system adaptable to various installation configurations without complicating the balancing operation.
3Productivity
If selective activation of rocket motors is implemented, then thrust profile control is improved, but ignition system complexity increases
Solution Approach 1:
The ignition system is organized into multiple plenums that can be selectively activated to control thrust profiles. Each plenum serves as an independent control unit, allowing different thrust profiles to be achieved by selecting which plenums to activate rather than requiring complex timing coordination of a single ignition system.
Solution Approach 2:
The plenum-based ignition system provides multi-functionality by enabling a single ignition architecture to deliver multiple thrust profiles through selective plenum activation. This universal approach allows the same system to accommodate various operational requirements without increasing complexity.
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 balanced ignition of multiple rocket motors, providing flexible thrust profiles and reducing the complexity of ignition timing, while ensuring simultaneous or sequential ignition for stable propulsion.
Implementation Method 1
ignition material in respective of the plenums, configured to be ignited by the initiators
Data Source
AI summary
A power generation system includes a manifold having multiple plenums, capable of receiving multiple solid rocket motors. Initiators are coupled to the manifold, and are operatively coupled to respective of the plenums, to selectively fire different groups of the rocket motors coupled to respective of the plenums. The rocket motors act in parallel, to provide thrust in a single direction. The initiators may activate ignition charges that are in the plenums. The plenums may be annular plenums, which may be located in an annular manifold. The plenums may be lined with an insulator material. A cover may be used to cover the plenums, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors, with propellant grains and nozzles. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge.