Multi-Pulse Rocket Motor Combustion Gas Supply Control
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Solution Overview
Problem
Existing multi-pulse rocket motors face challenges in achieving high mobility during terminal guidance due to limitations in propellant length, initial thrust, and structural weight, as well as issues with barrier membrane durability and igniter strength, particularly in unseparated thruster types.
Innovation Solution
A combustion gas supply control device is developed for unseparated thruster type multi-pulse rocket motors, utilizing a barrier membrane to isolate propellants and control combustion gas flow, ensuring efficient combustion gas supply at desired timings and reducing structural weight by independent igniter structures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If the first propellant and second propellant are arranged in axial direction with limited rocket motor length, then the rocket motor fits equipment and storage constraints, but the first propellant cannot have enough length resulting in small initial burning area and insufficient initial thrust
Solution Approach 1:
The patent transitions from axial arrangement to radial arrangement of propellants. The first propellant is positioned at the center and the second propellant surrounds it radially, allowing the first propellant to achieve sufficient length along the axial direction for adequate initial burning area, while the overall rocket motor length remains constrained by the radial configuration of the two propellants.
2Device complexity
If the barrier membrane is made thin and flexible to isolate propellants, then the structure is simplified and weight reduced, but breakability and durability at the time of second igniter operation become uncertain
Solution Approach 1:
The barrier membrane is designed with non-uniform thickness, being thinner at locations away from the second igniter and thicker near the second igniter where mechanical stress and thermal effects are more intense during operation. This local variation in thickness optimizes both the flexibility needed for isolation and the durability required withstanding second igniter operation.
3Length of moving object
If the first igniter and second igniter are arranged in series in axial direction, then the structure is compact, but the igniters have long and thin cantilever structure requiring strengthening that increases structural weight
Solution Approach 1:
The patent positions the first igniter and second igniter at different radial locations rather than arranging them in series axially. The first igniter is located to ignite the first propellant at the center, while the second igniter is positioned radially outward to ignite the second propellant. This radial separation eliminates the need for long cantilever structures and reduces igniter weight.
4Device complexity
If the second propellant is arranged on outer periphery of first propellant to share nozzle, then the structure is simplified, but the barrier membrane must withstand high-temperature combustion gas and high pressure from first propellant combustion
Solution Approach 1:
The barrier membrane is designed as a specialized intermediary component between the first propellant combustion chamber and the second propellant. It incorporates heat-resistant and pressure-resistant properties, and is strategically positioned to manage the interface between the two propellant systems, allowing the nozzle to be shared while protecting the second propellant zone from excessive thermal and mechanical stress.
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 enhances mobility by ensuring efficient combustion gas supply and reducing structural weight, improving the durability and breakability of the barrier membrane, and maintaining igniter strength, thus addressing the limitations of existing rocket motor designs.
Implementation Method 1
a barrier membrane (10) which isolates the first propellant (4) and the second propellant (5) from each other
Implementation Method 2
combustion of a first propellant (4) and then, after a certain period of time has passed, combusting a second propellant (5)... the second propellant (5), until starting to be burned, needs to withstand high-temperature combustion gas and high pressure generated as a result of combustion of the first propellant (4)
Data Source
AI summary
A combustion gas generator has: a motor case; a first propellant loaded within the motor case to burn at a first pulse; a second propellant loaded within the motor case to burn at a second pulse subsequent to the first pulse; a front motor head fixed to a front portion of the motor case and having a combustion gas exhaust hole; and a rear motor head fixed to a rear portion of the motor case and having a combustion gas exhaust hole. A combustion gas supply control device prevents combustion gas of the first propellant at the first pulse from flowing into the combustion gas exhaust hole of the front motor head and supplies combustion gas of the second propellant at the second pulse to the combustion gas exhaust hole of the front motor head.