Vortex Thruster System Multi-Level Thrust Control
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Solution Overview
Problem
Existing rocket combustion engines face challenges in achieving efficient combustion while managing thermal stress and weight constraints, often requiring complex and costly propellant injectors and regenerative coolant channels.
Innovation Solution
A vortex thruster system that includes a catalyst bed, monopropellant injectors, and a vortex combustion chamber, allowing for controlled delivery of monopropellant at varying flow rates and the introduction of a secondary propellant to generate multiple thrust levels, while minimizing thermal loading.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If complete combustion is achieved through thorough mixing of fuel and oxidizer, then combustion efficiency is improved, but thermal stress on rocket engine hardware increases
Solution Approach 1:
The combustion process is segmented into two distinct stages: first, monopropellant decomposes in a catalyst bed to produce hot gas; second, this hot gas mixes with secondary propellant in a vortex combustion chamber. This segmentation allows complete combustion to occur in controlled stages rather than simultaneously, reducing peak thermal stress on hardware while maintaining combustion efficiency.
Solution Approach 2:
The patent introduces an intermediary substance (decomposed monopropellant producing hot gas) that mediates between the fuel and oxidizer. This hot gas acts as a thermal buffer, enabling complete combustion while distributing thermal load more evenly, thereby reducing intense thermal stress on engine components.
2Productivity
If complex propellant injectors are used to achieve high mixing rates and combustion efficiencies, then combustion efficiency is improved, but manufacturing cost and complexity increase
Solution Approach 1:
The decomposed monopropellant serves a dual function: it acts as both the oxidation source and the mixing medium for the secondary propellant. This self-service approach eliminates the need for complex multi-component injector systems, simplifying manufacturing while maintaining high combustion efficiency through natural vortex-induced mixing.
Solution Approach 2:
The patent utilizes vortex flow dynamics and fluid mechanics to achieve thorough mixing of propellants. By inducing rotational flow in the combustion chamber, the system achieves high mixing rates through pneumatic principles rather than mechanical injector complexity, reducing manufacturing难度 while improving combustion efficiency.
3Temperature
If regenerative coolant channels are included to remove heat from rocket hardware, then thermal management is improved, but system weight and size increase
Solution Approach 1:
The patent converts the thermal energy that would otherwise be harmful waste heat into a useful resource. The decomposed monopropellant generates hot gas that naturally provides thermal management by controlling combustion temperature profiles, eliminating the need for separate heavy coolant systems while maintaining effective thermal control.
4Adaptability or versatility
If multiple thrust levels are generated through varying propellant flow rates, then operational versatility is improved, but system complexity increases
Solution Approach 1:
The system achieves multiple thrust levels by changing operational parameters (propellant flow rates) rather than changing physical hardware configurations. By adjusting the flow rates of monopropellant and secondary propellant, the system provides versatile thrust control while maintaining relatively simple valve and injector hardware.
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 vortex thruster system efficiently generates multiple thrust levels, optimizing combustion efficiency and controlling thermal loads, thereby addressing the weight and cost concerns of traditional rocket engines.
Implementation Method 1
a catalyst bed configured to decompose the monopropellant into a decomposed monopropellant
Implementation Method 2
a vortex combustion chamber configured to receive the decomposed monopropellant from the catalyst bed, wherein the decomposed monopropellant is delivered into the vortex combustion chamber
Data Source
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AI summary
Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.