Solid rocket ramjet based on detonation combustion

Abstract

The invention discloses a solid rocket ramjet based on detonation combustion. The solid rocket ramjet comprises an outer shell, an inner core, an air inlet channel, an isolation section channel, a detonation combustion channel, a gas generator, a flow stabilizing ring cavity, a main fuel injection system, a rotary detonation combustion chamber, a tail spray pipe and other structures, wherein the air inlet channel, the isolation section channel and the detonation combustion channel are formed between the inner wall of the outer shell and the outer wall of the inner core; air captured by the air inlet channel is decelerated and pressurized in an isolation section and then enters the rotary detonation combustion chamber; the front portion of the inner core is of a hollow structure, the gas generator is arranged in the inner core, an oxygen-deficient solid propellant is combusted in the gas generator and forms fuel-rich gas, and the fuel-rich gas enters an expansion section of the isolation section channel through a main fuel injector, is fully mixed with fresh air and then is sprayed into the ring cavity of the rotary detonation combustion chamber; and the rotary detonation combustion chamber is provided with an ignition device, the tail spray pipe is installed at an outlet, chemical energy is converted into kinetic energy, and thrust is generated. The solid rocket ramjet has higher combustion efficiency and work performance.

Description

technical field [0001] The invention belongs to the technical field of aerospace power, in particular to a solid rocket ramjet based on detonation combustion. Background technique [0002] At present, the chemical energy engine used in the aerospace propulsion system, its internal combustion heat release process belongs to isobaric combustion. After decades of development, the power plant based on the isobaric combustion mode has been perfected day by day, and it is very difficult to greatly improve its propulsion efficiency. It is urgent to develop a new type of power propulsion device that meets the requirements of high speed and high efficiency. Compared with isobaric combustion, detonation combustion has the advantages of fast energy release rate, high thermal cycle efficiency, self-pressurization, short reaction zone, etc., and is close to constant volume combustion, which makes the power system based on detonation combustion have better propulsion performance. There i...

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Problems solved by technology

At the same time, the gas generator is used to pre-combust and gasify the solid fuel to solve the problem of low mixing efficiency of solid fuel and air

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