Supersonic Nozzle Propellant Injection for Thrust Augmentation
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Solution Overview
Problem
Traditional rocket propulsion systems face inefficiencies due to static nozzle construction, which limits pressure regime efficiency and leads to under or over-expansion of combustion materials at varying altitudes, causing thrust direction variations and potential engine damage, and existing high-pressure fed engine cycles are complex and costly.
Innovation Solution
A rocket propulsion system with a supersonic nozzle featuring a convergent and divergent section, and a propellant injection system that injects propellant into the annular region of the divergent section, allowing for augmented and active purge modes to manage pressure and thrust direction, including bipropellant injection and heat transfer systems to optimize thrust generation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a static nozzle construction is used, then the engine structure is simple, but the pressure regime efficiency is limited and thrust direction varies at different altitudes
Solution Approach 1:
The patent applies dynamics by transitioning from a static nozzle to a dynamic system where propellant is injected into the divergent section to actively control pressure and thrust direction. The injection system allows the nozzle to adapt its effective geometry and pressure distribution in real-time, enabling optimization across varying altitude conditions rather than being fixed for a single design point.
Solution Approach 2:
The patent changes physical parameters by injecting propellant into the divergent section to modify the local pressure and flow characteristics. This parameter change allows the system to adjust the expansion ratio and thrust vector dynamically, effectively adapting to different ambient pressure conditions at various altitudes without changing the physical nozzle geometry.
2Power
If propellant is injected into the divergent section to augment thrust, then thrust generation is improved, but pressure control complexity increases
Solution Approach 1:
The patent applies universality by using the same propellant injection system for multiple functions: augmenting thrust, controlling pressure distribution, and managing thrust direction. The injection system serves as a multi-functional actuator that can operate in different modes (thrust augmentation, pressure control, or combination) depending on flight conditions, reducing the need for separate dedicated systems for each function.
3Productivity
If high-pressure fed engine cycles are used, then thrust efficiency is improved, but system complexity and cost increase
Solution Approach 1:
The patent applies self-service by using a portion of the engine's own propellant and exhaust flow to control the pressure regime and augment thrust. The injected propellant is drawn from the same propellant supply as the main combustion, and the system uses its own exhaust gases as the medium into which propellant is injected, creating a self-contained control system that doesn't require external actuators or complex high-pressure feed systems.
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 system achieves efficient thrust generation across varying altitudes by dynamically managing propellant injection and pressure, reducing engine damage and improving operational efficiency compared to traditional systems.
Implementation Method 1
a propellant pressure created from the propellant entering the annular region of the supersonic divergent section is greater than or equal to an annular region pressure created by other combustion sources
Implementation Method 2
a supersonic rocket nozzle defined by a convergent section, a throat, and a supersonic divergent section
Data Source
AI summary
A rocket propulsion system that may include a supersonic rocket nozzle with a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant where a portion of the propellant may be selectively injected, combusted, and expanded in the supersonic nozzle generating an additional thrust. In examples, the heated propellant may be used to power a pump system to feed the rocket engine.