Segmented Solid Rocket Propellant Grain Design
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Solution Overview
Problem
Existing solid rocket propellant grains either produce high thrust with short burning time or low thrust with long burning time, making it difficult to achieve intermediate values without changing the propellant material or combustion chamber design significantly.
Innovation Solution
A solid rocket propellant grain design featuring a combination of first and second type layers, where the first type layer is completely filled with solid propellant and has an inhibited lateral surface, and the second type layer has recesses in the solid propellant with a non-inhibited lateral surface, allowing for a cylindrical shape with interconnected layers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a cylindrical grain with a core channel along its entire length is used, then high thrust is achieved, but burning time becomes short
Solution Approach 1:
The grain is divided into multiple longitudinal segments separated by transverse slots, creating a segmented core channel structure. This segmentation allows the burning front to progress through multiple paths simultaneously, extending burning time while maintaining high thrust through the distributed combustion zones.
Solution Approach 2:
The invention introduces transverse slots that extend the burning path from a single axial dimension to multiple radial dimensions. The burning front progresses both axially through the core channel and radially through the slots, creating a multi-dimensional combustion pattern that extends burning time without sacrificing thrust.
2Duration of action of moving object
If a grain without a core channel with inhibited outer surface is used, then low thrust is achieved, but burning time becomes long
Solution Approach 1:
The grain structure incorporates transverse slots that segment the propellant mass into multiple combustion zones. This segmentation creates multiple burning fronts that progress simultaneously, increasing the overall burning rate and thrust while maintaining extended burning time through the distributed combustion paths.
Solution Approach 2:
The transverse slots introduce radial combustion paths in addition to axial burning, creating a multi-dimensional combustion pattern. This allows the burning front to progress through multiple directions simultaneously, increasing thrust while maintaining long burning time through the extended combustion path.
3Power
If propellant material or combustion chamber dimensions are changed to obtain intermediate thrust and operating time values, then intermediate performance is achieved, but design complexity increases
Solution Approach 1:
The grain structure uses simple transverse slots cut through the propellant mass to create segmented combustion zones. This segmentation approach provides intermediate thrust and burning time characteristics without requiring complex propellant formulations or combustion chamber redesign, maintaining design simplicity while achieving performance flexibility.
Solution Approach 2:
The invention modifies local regions of the grain by introducing transverse slots at specific positions and depths. This local modification creates varied burning paths and combustion zones that provide intermediate performance characteristics without requiring changes to the overall propellant material or combustion chamber design.
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 design enables the achievement of intermediate thrust and operating time values without altering the propellant material or combustion chamber design, providing a wide range of propellant burning areas and thrust profiles, thus allowing for more flexible rocket motor operation.
Implementation Method 1
a solid propellant material with an inhibited lateral surface... a non-inhibited lateral surface... providing a wide range of propellant burning areas and thrust profiles
Data Source
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AI summary
The subject of the invention is a solid rocket propellant grain comprising frontal surfaces and a lateral surface, characterised in that it comprises a first type layer which is completely filled in cross-section with a solid propellant material with an inhibited lateral surface (101a), and a second type layer which has at least one recess (103) in a solid propellant material with a non-inhibited lateral surface (101b), wherein at least one second type layer is surrounded by the first type layer on both sides.