Rocket-based combined cycle engine based on detonation and detonation principle and application method

Abstract

The invention discloses a rocket-based combined cycle engine based on the deflagration and detonation principle and an application method. The rocket-based combined cycle engine based on the deflagration and detonation principle comprises a center cone, a shell, a support and a fuel supply system. By forming a double-combustion-chamber and double-spray-pipe structure, the invention provides a non-completely closed circulating propellant supply system, a liquid rocket engine and a ramjet engine based on the detonation and detonation principle are organically combined, and the working requirements of low-speed starting, wide-speed-domain / airspace-range flight and ultra-supersonic-speed cruising can be met; the system has the characteristics of large specific impulse, strong robustness, high circulating thermal efficiency and compact layout.

Description

technical field [0001] The invention relates to the technical field of aerospace engines, more specifically, to a rocket-based combined cycle engine based on deflagration and detonation principles and an application method thereof. Background technique [0002] Combustion in nature can be divided into two categories, one is deflagration and the other is detonation. Deflagration combustion transfers the energy released by the reaction into the unburned mixture in front through heat conduction, molecular diffusion and turbulent transport mechanism, so as to realize the propagation of deflagration wave. The propagation speed of the deflagration wave is relatively slow, generally a few meters to tens of meters per second, and it propagates at subsonic speed relative to the reactant in front of it. The detonation combustion mainly relies on the detonation wave to organize the combustion. The detonation wave can be described as a strong shock wave with a chemical reaction that ca...

AI Technical Summary

Problems solved by technology

The invention patent with application publication number CN112228246A discloses a rocket-based detonation ram ram combined cycle engine and its use method and application. The propulsion is provided by a rotary detonation engine. The principle of the engine is to use the rotating detonation wave propagating in the circumferential direction to organize combustion. However, at a high Mach number (Ma>7), this type of engine may burn in advance and it is difficult to continue to use the rotating detonation wave. Tissue combustion, in practical applications, there are also problems such as shock wave forward interference to the intake port, thrust eccentric moment, and the size and direction of the lateral force component will change periodically, that is, the engine may produce periodic high-frequency vibrations and other problems

Oblique detonation ramjet propulsion can overcome the problem of combustion wave stagnation and does not require additional ignition. It is an engine based on oblique detonation shock waves, a new combustion organization, and is expected to realize air-breathing hypersonic propulsion with a Mach number of 9 and above. Technological breakthrough, but the engine has the disadvantage of relatively high starting speed (Ma>8) in practical application

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