Powder fuel support plate ejection rocket-based combined cycle engine based on HAN unit propellant

A technology for ejecting rockets and propellants, used in rocket engine devices, machines/engines, jet propulsion devices, etc., can solve problems such as engine performance degradation, and achieve the effects of improving reliability, reducing negative mass, and inhibiting dissociation

Pending Publication Date: 2022-01-18
EAST CHINA UNIV OF SCI & TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problem that the fuel dissociation of the rocket-based combined cycle power system in the scramjet mode causes the performance of the engine to decrease, the present invention proposes a powder-fuel strut ejector rocket-based combined cycle ba...

Method used

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  • Powder fuel support plate ejection rocket-based combined cycle engine based on HAN unit propellant
  • Powder fuel support plate ejection rocket-based combined cycle engine based on HAN unit propellant
  • Powder fuel support plate ejection rocket-based combined cycle engine based on HAN unit propellant

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Embodiment

[0025] During the start-up process of the aircraft, the engine is in the ejection state and supplied according to the equivalent ratio of the aluminum powder and the complete decomposition product of the hydroxylamine nitrate propellant. The HAN-based single-component rocket engine adopts catalytic starting, and the direct injection into the front bed and the rear bed The propellant can realize the stable work of the HAN-based single-component rocket engine. As the speed of the aircraft increases, when the flight speed reaches 2 Ma, the engine enters the sub-combustion ramming mode, and the propellant flow rate of the HAN-based monopropellant rocket engine begins to decrease gradually. At this time, the single-component rocket engine is shut down, and aluminum powder and ram air are burned in the combustion chamber. When the flight speed is greater than 5Ma, the engine enters the scramjet mode, and the aircraft enters the adjacent space. The HAN-based monocomponent rocket engi...

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Abstract

The invention relates to a support plate ejection rocket-based combined cycle power engine based on a unit propellant. The support plate ejection rocket-based combined cycle power engine comprises an air inlet channel, a central support plate single-component rocket, a powder fuel supply system, a nitric acid hydroxylamine-based propellant supply system, a high-pressure air source, a combustion chamber and a spray pipe. A nitric acid hydroxylamine single-component propellant which is good in normal-temperature storage performance and can be rapidly catalyzed and started at normal temperature is used as a propellant of a support plate rocket in an engine, the structure of a support plate rocket system is simplified, and the reliability of the engine is improved; the aluminum powder is adopted to replace traditional hydrocarbon fuel, the density specific impulse of the engine is improved, the fuel dissociation phenomenon in a scramjet mode is overcome, and the engine performance is maintained. According to the engine, mode conversion in a flight process is achieved by adjusting the flow of a nitric acid hydroxylamine-based propellant.

Description

technical field [0001] The invention belongs to the technical field of aerospace power, and relates to a powder fuel strut ejector rocket-based combined cycle engine based on HAN unit propellant. Background technique [0002] The rocket-based combined cycle power system is a propulsion system that combines rocket engines and ramjet engines. Its working process includes four modes: ejection mode, sub-combustion mode, supercombustion mode and rocket mode. Adjusting the working mode of the engine can give full play to the respective advantages of the rocket engine and the ramjet engine, so that the aircraft is always in the best thermal cycle state under different flight parameters, and has both high specific impulse and high thrust-to-weight ratio. [0003] The rocket-based combined cycle power system mainly realizes the mutual conversion between different modes by controlling the oxygen-fuel ratio of the launch rocket during the working process. At present, its propulsion sys...

Claims

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Application Information

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IPC IPC(8): F02K9/08F02K9/26F02K9/32F02K9/34F02K9/95
CPCF02K9/08F02K9/26F02K9/32F02K9/34F02K9/95Y02E20/16
Inventor 胡旭黄永民李缮彤周秀爽朱小飞
Owner EAST CHINA UNIV OF SCI & TECH
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