Hybrid Fuel Valve Control for Flying Body Drive
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Solution Overview
Problem
Existing control and drive devices for flying bodies face challenges in controlling solid-fuel drives once ignited and liquid-fuel drives are complex and toxic, leading to inefficient fuel utilization and toxicity concerns.
Innovation Solution
A compact hybrid drive device combining a liquid or gaseous fuel component with a solid or paste-like fuel component, connected via a controllable valve, allowing for precise control of combustion and reignition, using a single combustion chamber for efficient fuel use and reduced toxicity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a solid-fuel drive is used, then the structure is simple and handling is uncomplicated, but the combustion cannot be controlled once ignited and fuel utilization is poor
Solution Approach 1:
The fuel supply is segmented into multiple separate hollow chamber bodies (first hollow chamber body for liquid/gaseous fuel, second hollow chamber body for solid/paste-like fuel) that can be independently controlled. This segmentation allows the combustion process to be divided into controllable stages, enabling selective feeding of fuel components to achieve precise combustion control while maintaining the simplicity of solid-fuel structure.
2Duration of action of moving object
If a liquid-fuel drive is used, then combustion time is longer and thrust control is accurate, but the structure is more complicated and the fuels are toxic
Solution Approach 1:
The invention merges the advantages of liquid-fuel drives (controllable combustion duration and thrust) with the advantages of solid-fuel drives (simple structure and low toxicity) by creating a hybrid system. The first hollow chamber body contains liquid or gaseous fuel component while the second hollow chamber body contains solid or paste-like fuel component, combining both fuel types in a unified combustion chamber to achieve extended combustion time with simplified structure.
3Duration of action of stationary object
If the whole fuel supply is combusted, then the drive operates continuously, but fuel utilization is inefficient and causes large fuel loss
Solution Approach 1:
The fuel feeding system is made dynamic through controllable fuel valves that regulate the flow of fuel components from the first and second hollow chamber bodies to the combustion chamber. This dynamic control enables the combustion process to be adjusted in real-time according to mission requirements, allowing continuous operation when needed while preventing fuel waste by stopping or reducing combustion when not required, thereby improving fuel utilization efficiency.
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 precise control and efficient use of fuels with reduced toxicity, improving mission profiles by allowing centralized control of combustion and reignition, effectively combining the advantages of solid and liquid fuel drives in a compact system.
Implementation Method 1
The first hollow chamber body and the second hollow chamber body are connected to one another via a controllable fuel valve in order to control a feed of the first component to the second hollow chamber body
Implementation Method 2
The second hollow chamber body is designed as a combustion chamber for the combustion of the first and second components of the fuel combination when fed into the second hollow chamber body in order to generate the respective hot gas streams
Implementation Method 3
A plurality of outlets are provided for the ejection of a respective hot gas stream that is suitable in each case for influencing a flight path of the flying body
Data Source
AI summary
Control and/or drive device for a flying body for ejecting hot gas streams of a combusted fuel combination of at least a first and second component. Device includes a first hollow chamber body structured and arranged to contain first component, a second hollow chamber body structured and arranged to contain second component, a controllable fuel valve arranged between first hollow chamber body and second hollow chamber body to control feed of first component to second hollow chamber body, and a plurality of outlets structured and arranged to eject respective hot gas streams for influencing a flight path of flying body. Second hollow chamber body is formed as a combustion chamber for combusting the at least first and second components within second hollow chamber body to generate respective hot gas streams, and plurality of outlets are connected to the second hollow chamber body.