Multi-Pulse Rocket Motor With Electric-Field Ignition
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Solution Overview
Problem
Conventional multi-pulse rocket motors face challenges such as complicated and costly barrier and igniter systems, potential nozzle clogging, and limited to two pulses, which can lead to combustion instability and manufacturing difficulties.
Innovation Solution
A rocket motor with an electrically operated propellant initiator featuring a pair of electrodes, including a ground plane electrode and an ignition electrode, configured to concentrate an electric field for igniting electrically operated propellant, ensuring operatively isolated and controlled combustion of propellant grains, thereby eliminating the need for complex barriers and enabling multiple pulses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional barrier and igniter systems are used to separate propellant grains in multi-pulse rocket motors, then propellant isolation is achieved, but device complexity and manufacturing cost increase significantly
Solution Approach 1:
The patent removes the complex barrier system entirely by using electrically operated propellant initiators with ground plane electrodes that directly ignite propellant grains without requiring physical separation barriers. This extracts the barrier component from the system while maintaining propellant isolation through controlled electrical ignition.
Solution Approach 2:
The ground plane electrode serves multiple functions: it provides electrical connection for ignition, acts as a barrier to prevent combustion gas transfer between pulses, and enables controlled initiation of individual propellant grains. This multi-functional approach eliminates the need for separate barrier and igniter systems.
2Reliability
If conventional barriers are used to separate propellant grains, then propellant isolation is achieved, but nozzle clogging and combustion instability occur due to barrier ejection or inversion
Solution Approach 1:
The patent eliminates the barrier component that causes ejection and inversion problems by using electrically operated initiators with ground plane electrodes. This removes the source of harmful factors while maintaining the necessary propellant isolation function.
Solution Approach 2:
The ground plane electrode acts as an intermediary that provides both electrical connection for ignition and physical separation between propellant grains without the drawbacks of conventional barriers. It mediates between the need for isolation and the need to avoid nozzle clogging.
3Adaptability or versatility
If conventional multi-pulse rocket motors are designed with barrier systems, then two-pulse operation is achieved, but the system is limited and cannot easily accommodate more pulses
Solution Approach 1:
The ground plane electrode design provides a universal solution that can accommodate any number of pulses by simply adding more electrodes and propellant grains. The same basic structure scales from two pulses to multiple pulses without requiring fundamentally different barrier configurations.
Solution Approach 2:
The patent uses segmented propellant grains with individual ground plane electrodes for each grain. This segmentation allows independent control of each pulse while using the same basic structural unit, making it easy to add or remove pulses as needed.
4Ease of operation
If conventional igniter systems are used for each propellant pulse, then individual pulse ignition is achieved, but manufacturing cost and complexity increase
Solution Approach 1:
The ground plane electrode serves as both the ignition source and the barrier structure, eliminating the need for separate igniter components. This universal component reduces manufacturing steps and costs while maintaining individual pulse ignition control capability.
Solution Approach 2:
The patent merges the barrier function and igniter function into a single ground plane electrode component. This consolidation reduces the number of parts that need to be manufactured and assembled, thereby reducing manufacturing complexity and cost.
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 provides efficient, controlled ignition and isolation of propellant grains, reducing manufacturing complexity and costs, while allowing for multiple propulsion pulses without nozzle clogging, enhancing operational reliability and flexibility.
Implementation Method 1
at least one pair of electrodes arranged to ignite the electrically operated propellant, the at least one pair of electrodes including a ground plane electrode and an ignition electrode at which an electric field is concentrated to ignite the electrically operated propellant
Implementation Method 2
initiate combustion of the at least one propellant grain
Data Source
Figure 1
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AI summary
A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.