Two-Pulse Gas Generator with Nested Propellants
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing gas generators for missiles lack the capability to efficiently produce both low thrust, long duration and high thrust, short duration patterns, which are essential for terminal guidance and trajectory control.
Innovation Solution
A two-pulse gas generator with a pressure vessel containing an outer tubular propellant and an inner columnar propellant, isolated by a barrier membrane, where the inner propellant is ignited first for end-surface burning, and the outer propellant is ignited later to break the membrane and enable simultaneous inner-surface and end-surface burning, generating distinct thrust patterns.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a single propellant configuration is used in the gas generator, then the structure is simple, but only one thrust pattern can be produced
Solution Approach 1:
The gas generator is segmented into two distinct propellant regions: an inner propellant (low thrust, long duration) and an outer propellant (high thrust, short duration). This segmentation allows each region to be optimized for specific thrust requirements, enabling the system to produce two extreme thrust patterns by selectively burning one or both propellants.
Solution Approach 2:
The inner propellant is nested within the outer propellant, creating a concentric dual-propellant configuration. The barrier membrane separates these nested propellants, allowing independent control of each. This nested structure enables versatile thrust patterns while maintaining a compact overall generator design.
2Reliability
If the barrier membrane is made strong to maintain isolation, then propellant isolation is reliable, but the membrane cannot break to enable outer propellant ignition
Solution Approach 1:
The barrier membrane exhibits local quality differentiation: it is designed with non-uniform thickness or material properties, being stronger in most regions to maintain reliable propellant isolation, but with a specific weak portion that can be selectively broken. This allows the membrane to simultaneously provide reliable isolation and controlled breakage for sequential propellant ignition.
3Productivity
If the inner propellant side surface is exposed to combustion space, then burning area increases, but side-surface burning cannot be prevented
Solution Approach 1:
The side surface of the inner propellant is extracted from the combustion space by introducing a barrier membrane that isolates it. This allows the inner propellant to burn only at its forward end surface, providing controlled burning area and preventing unwanted side-surface combustion, while the outer propellant's inner surface remains exposed for additional burning area when needed.
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 allows for a compact gas generator that can produce two extreme thrust patterns, enabling low thrust, long duration and high thrust, short duration capabilities, enhancing missile guidance and control.
Implementation Method 1
progressing end-surface burning of the inner propellant
Implementation Method 2
progressing inner-surface burning of the outer propellant and end-surface burning of the outer propellant at the same time
Data Source
AI summary
A gas generator includes an outer propellant, an inner propellant arranged inside the outer propellant, and a barrier membrane which isolates the outer propellant from the inner propellant. A forward end surface of the inner propellant faces a combustion space. A side surface of the inner propellant is isolated from the combustion space.