Electrically Operated Propellant Initiators for Pulse Propulsion
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Solution Overview
Problem
Multiple pulse propulsion systems for projectiles face inefficiencies due to the use of inert barriers, which add weight and volume without contributing to thrust, and require multiple igniters for redundancy, complicating assembly and manufacturing.
Innovation Solution
A gas generation system utilizing electrically operated propellant initiators that act as non-inert barriers, allowing for individual ignition of propellant charges and eliminating the need for separate igniters, by using electrically operated propellant configured to transition between ignited and unignited states based on electrical input and pressure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If inert barriers are used to separate propellant charges in multiple pulse propulsion systems, then individual ignition of propellant charges is enabled, but weight and volume increase without contributing to thrust
Solution Approach 1:
The patent combines the barrier function and igniter function into a single component. The electrically operated propellant initiator serves both as the separation barrier between propellant charges and as the igniting mechanism, eliminating the need for separate inert barriers and standalone igniters.
Solution Approach 2:
The electrically operated propellant initiator performs multiple functions: it acts as a physical barrier to prevent premature ignition, serves as an igniter when electrically activated, and contributes to the total impulse of the motor. This multi-functional component replaces the traditional separate inert barrier and igniter assembly.
2Reliability
If inert barriers are used to separate propellant charges, then combustion gases are contained, but assembly and manufacturing complexity increases
Solution Approach 1:
The patent merges the barrier and igniter into a single integrated component, reducing the number of parts that need to be assembled. This integration simplifies the manufacturing process and reduces assembly complexity while maintaining effective combustion gas containment.
Solution Approach 2:
The patent changes the material state and properties of the barrier from inert to electrically operable propellant. This parameter change allows the barrier to transition from a passive structural element to an active igniting component, simplifying the overall system architecture.
3Reliability
If multiple separate igniters are used for redundancy in pulse propulsion systems, then ignition reliability is improved, but device complexity and weight increase
Solution Approach 1:
The electrically operated propellant initiator provides inherent redundancy through its electrical operation capability. The system can control ignition timing and sequence electrically, providing reliability without requiring multiple physical igniter components stacked together.
Solution Approach 2:
The patent replaces mechanical igniter systems with electrically operated propellant initiators. This substitution eliminates the need for complex mechanical igniter assemblies and allows for more reliable electrical control of ignition timing and sequencing.
4Reliability
If inert barriers are used in propulsion systems, then propellant charge isolation is achieved, but volume efficiency decreases
Solution Approach 1:
The patent combines the barrier and igniter functions into a single component that occupies minimal space. The electrically operated propellant initiator serves as both the isolation barrier and the ignition source, maximizing the volume available for propellant storage while maintaining charge isolation.
Solution Approach 2:
The patent changes the functional parameters of the barrier material from inert to electrically operable propellant. This transformation allows the barrier to become a productive component that contributes to thrust while maintaining the isolation function, thereby improving volume efficiency.
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
This solution enhances the efficiency of weight and volume usage in propulsion systems by allowing propellant charges to be ignited independently, reducing the need for additional igniters and simplifying assembly, while maintaining control over combustion characteristics.
Implementation Method 1
electrically operated propellant initiators that act as non-inert barriers, allowing for individual ignition of propellant charges
Implementation Method 2
electrically operated propellant configured to transition between ignited and unignited states based on electrical input and pressure
Implementation Method 3
the first propellant charge is operatively isolated from a second propellant charge by the first electrically operated propellant initiator
Data Source
Figure 1
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AI summary
A gas generation system for generating gases, such as for use as or as part of a rocket motor in propelling a projectile, includes two or more propellant charges and electrically operated propellant initiators operatively coupled to respective of the propellant charges, to initiate combustion in the propellant charges, wherein the propellant charges are operatively isolated from one another such that the propellant charges can be individually initiated and are not ignited due to gases generated from other of the propellant charges being combusted.