Multi-pulse Gas Generator Barrier Membrane Deformation Control
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Solution Overview
Problem
Existing multi-pulse gas generator devices face challenges in stably supplying propellant combustion gas due to uneven pressure distribution and flow rate variations across the barrier membrane, leading to inefficient combustion gas expulsion.
Innovation Solution
A multi-pulse gas generator device with a barrier membrane featuring concavely-deformable and convexly-deformable portions, where the flow rate of combustion gas from the igniter charge is controlled to differ based on the location of exhaust holes and conduit shapes, ensuring consistent deformation and buckling of the membrane for stable gas supply.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a barrier membrane is used to separate propellants, then propellant separation and controlled combustion are improved, but uneven pressure distribution and flow rate variations occur across the membrane
Solution Approach 1:
The barrier membrane is designed with locally differentiated properties through concavely-deformable portions (with lower rigidity) and convexly-deformable portions (with higher rigidity). This local quality variation allows different regions of the membrane to deform differently under pressure, creating multiple buckling modes that distribute pressure more evenly across the membrane surface while maintaining effective propellant separation.
2Ease of manufacture
If exhaust holes are arranged uniformly, then manufacturing simplicity is improved, but flow rate uniformity across the membrane deteriorates
Solution Approach 1:
The exhaust holes are arranged to correspond with the locally differentiated membrane structure, with holes positioned over both concavely-deformable and convexly-deformable portions. This arrangement allows the membrane to deform into multiple buckling modes during operation, creating more uniform flow distribution across the exhaust holes while maintaining a relatively simple overall hole pattern that is feasible to manufacture.
3Strength
If the barrier membrane is made rigid, then structural stability is improved, but deformation and buckling control for stable gas supply deteriorates
Solution Approach 1:
The barrier membrane incorporates regions of different rigidity: concavely-deformable portions with lower rigidity that facilitate easy deformation and buckling for stable gas supply, and convexly-deformable portions with higher rigidity that provide structural support. This local differentiation allows the membrane to achieve both structural stability and controlled deformation behavior simultaneously.
Solution Approach 2:
The barrier membrane is designed to transition from a static rigid structure to a dynamic structure that can deform and buckle in multiple modes during operation. The concavely-deformable portions are specifically designed to deform under pressure, creating dynamic buckling patterns that stabilize gas flow, while the convexly-deformable portions maintain overall structural integrity.
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 controlled deformation and buckling of the barrier membrane allow for stable and efficient supply of combustion gas from the second propellant, enhancing the overall performance of the multi-pulse gas generator device by managing pressure and flow rates effectively.
Implementation Method 1
configured to be concavely deformed by a pressure caused by combustion gas of the second propellant and/or the combustion gas of the igniter charge
Implementation Method 2
a plurality of concavely-deformable portions configured to be concavely deformed by a pressure caused by combustion gas
Implementation Method 3
The igniter device is configured to produce combustion gas of igniter charge to ignite the second propellant
Data Source
AI summary
A multi-pulse gas generator includes a pressure vessel, first and second propellants, a barrier membrane that separates the first propellant and the second propellant, an igniter device that produces combustion gas of igniter charge, and an igniter charge combustion gas exhaust device having exhaust holes configured to exhaust the combustion gas of the igniter charge against the second propellant. The barrier membrane includes: a concavely-deformable portion; and a convexly-deformable portion. A flow rate of the combustion gas of the igniter charge exhausted against a portion of the second propellant located outside of the concavely-deformable portion is larger than that of the combustion gas of the igniter charge exhausted against a portion of the second propellant located outside of the convexly-deformable portion.