Multi-Layer Propellant Grain for Rocket Motor Pressure Stability
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Solution Overview
Problem
Existing propellant manufacturing methods for rocket motors and gas generators face challenges in reducing the mass of the pressure vessel while maintaining combustion pressure stability and increasing propellant load, as recesses like slots and star perforations either increase combustion pressure or reduce the amount of propellant that can be mounted.
Innovation Solution
A propellant manufacturing method and apparatus that utilize three types of propellants with different burning rates, where the first propellant is placed on the internal wall, the second propellant is placed between the first and third propellants, and the third propellant is placed on the inner side surface, with all propellants being simultaneously hardened, allowing for controlled combustion and reduced pressure vessel mass.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If propellant is shaped with recesses (slots or star perforations), then combustion pressure stability is improved, but the amount of propellant that can be mounted is reduced
Solution Approach 1:
The propellant is divided into multiple layers with different burning rates (first propellant layer with lower burning rate, second propellant layer with higher burning rate). This segmentation allows different regions to contribute differently to combustion, maintaining pressure stability while maximizing total propellant quantity without requiring recesses.
Solution Approach 2:
Different portions of the propellant are assigned different burning rates based on their location and function. The first propellant layer (lower burning rate) is positioned to control initial combustion, while the second propellant layer (higher burning rate) supplements combustion as the first layer depletes, optimizing both pressure stability and propellant utilization.
2Quantity of substance
If propellant is shaped in simple cylindrical form, then the amount of propellant that can be mounted is maximized, but combustion pressure stability deteriorates
Solution Approach 1:
The propellant is divided into multiple layers with different burning rates (first propellant layer with lower burning rate, second propellant layer with higher burning rate). This segmentation allows different regions to contribute differently to combustion, maintaining pressure stability while maximizing total propellant quantity without requiring recesses.
Solution Approach 2:
Different portions of the propellant are assigned different burning rates based on their location and function. The first propellant layer (lower burning rate) is positioned to control initial combustion, while the second propellant layer (higher burning rate) supplements combustion as the first layer depletes, optimizing both pressure stability and propellant utilization.
3Stability of the object's composition
If multi-layered propellant structure is implemented, then combustion pressure stability is improved, but manufacturing complexity increases
Solution Approach 1:
The propellants are prepared in advance as separate formulations with controlled viscosities. The second propellant formulation is prepared with lower viscosity specifically for injection purposes, and the injection is timed to occur substantially simultaneously with extrusion of the first propellant, simplifying the overall manufacturing process.
Solution Approach 2:
The second propellant formulation (low viscosity gel, liquid or paste) is injected into the passageway defined by the first propellant layer using fluid injection techniques. This hydraulic/pneumatic method allows precise placement of the second layer without complex mechanical assembly, reducing manufacturing 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
This approach maintains stable combustion pressure, reduces the mass of the pressure vessel, and allows for a higher propellant load without the need for recesses, enhancing the performance of rocket motors and gas generators.
Implementation Method 1
A rocket motor or gas generator using solid propellant may be used for a missile or the like. The combustion pressure generated by the combustion gas varies depending on the area of the combusting surface on which the propellant is combusted.
Implementation Method 2
The manufacturing method includes simultaneously and completely hardening the first propellant, the second propellant, and the third propellant.
Data Source
AI summary
A propellant manufacturing method for manufacturing a propellant including a propellant grain having a first surface on which combustion starts upon ignition and a second surface to be coupled to a wall surface that prevents combustion. The manufacturing method includes placing a portion of first propellant having a first burning rate in a first space containing a first position on the second surface; and placing a portion of second propellant having a second burning rate higher than the first burning rate in a second space containing a second position on the first propellant. The method further includes placing a portion of third propellant having a third burning rate higher than the second burning rate in a third space containing a third position on the first propellant. The method further includes completing the propellant grain by simultaneously hardening the entireties of the first propellant, the second propellant, and the third propellant.