Decompressive Extinguishing Plug Nozzle for Multi-Burn Solid Rocket Motors
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Solution Overview
Problem
Conventional solid rocket systems are limited to a single burn configuration, restricting their operational flexibility and suitability for applications requiring multiple burns, such as space missions where diverse orbit maneuvers are necessary.
Innovation Solution
A multiple burn solid rocket system incorporating a catalytic or spark igniter and a decompressive extinguishing plug nozzle that allows for the reignition of solid rocket fuel, enabling multiple burns by rapidly decompressing the combustion chamber and transitioning between active and sealed configurations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional solid rocket systems are used, then the system is simple and reliable, but it is limited to a single burn configuration
Solution Approach 1:
The nozzle is made dynamically variable through the inclusion of a movable plug that can shift position to change the throat area. This allows the nozzle to transition between different flow regimes (subsonic, sonic, supersonic) and enable multiple burn configurations from a single solid rocket motor, directly resolving the contradiction between operational flexibility and system complexity
Solution Approach 2:
The nozzle is segmented into distinct functional zones: a convergent section, a variable throat section with a movable plug, and a divergent section. This segmentation allows independent control of flow characteristics in different regions, enabling multiple burn modes while maintaining a relatively simple overall structure
2Duration of action of moving object
If a decompressive extinguishing plug nozzle is used, then multiple burns are enabled, but the device complexity increases
Solution Approach 1:
The movable plug is designed to respond automatically to combustion chamber pressure changes. When pressure increases during combustion, the plug shifts to open the throat; when pressure decreases or when extinguishment is desired, the plug returns to close the throat. This self-regulating mechanism enables precise burn duration control without requiring complex external actuation systems
Solution Approach 2:
The nozzle utilizes changes in the physical state and pressure of the combustion gases to control plug position and throat area. By manipulating pressure parameters and gas flow characteristics, the system achieves multiple burn modes and extinguishment without adding significant complexity to the nozzle structure
3Reliability
If the nozzle is kept sealed, then safety is improved, but the fuel cannot burn
Solution Approach 1:
The nozzle transitions dynamically between sealed and open states based on operational requirements. The movable plug can be positioned to seal the throat for safety/storage, or opened to allow combustion and thrust generation. This dynamic switching resolves the contradiction between safety and productivity by allowing the system to adapt its state according to needs
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
Enables multiple ignitions and extinguishments of the solid rocket fuel, enhancing operational flexibility and safety, particularly for space missions where multiple burns are required, while maintaining the reliability and cost-effectiveness of solid rocket systems.
Implementation Method 1
a catalytic igniter or a spark igniter capable of operating at combustion chamber temperatures
Implementation Method 2
an igniter configured to ignite the hydrogen gas and the oxygen gas... fuel located within the combustion chamber that is configured to be ignited by the igniter
Implementation Method 3
a decompressive nozzle that is configured to allow the fuel to burn in an active configuration and to extinguish the fuel in a decompressive configuration
Implementation Method 4
a variable mechanical throat defining a choked sonic flow when the decompressive extinguishing plug nozzle is in an active configuration
Data Source
AI summary
A system for multiple burns from a solid fuel rocket motor may extinguish rocket fuel after the rocket has been ignited. The motor may be extinguished via rapid decompression of the combustion chamber. The fuel may then be reignited by a suitable igniter, and the process of extinguishing and reigniting may be repeated, enabling multi-burn maneuvers. A decompressive extinguishing plug nozzle may extinguish solid rocket fuel after the rocket has been ignited and/or keep a rocket in a disarmed (zero thrust) state until the rocket is to be armed. The nozzle may include a plug that mostly impedes the opening of the nozzle and an outer cowl that is movable to rapidly decompress the combustion chamber. This rapid decompression extinguishes the solid rocket fuel. In some aspects, the fuel can be reignited and extinguished multiple times.