Solid rocket ramjet adjusting device and engine propellant

Abstract

The invention discloses a solid rocket ramjet adjusting device and an engine propellant thereof. The engine propellant comprises the following components: 25-40 parts by mass of an oxidant, 15-30 parts by mass of an adhesive, 20-40 parts by mass of a metal powder fuel, 2-10 parts by mass of a combustion rate catalyst and 2-8 parts of an additive, wherein the oxidizing agent comprises perchlorate,such as ammonium perchlorate, magnesium perchlorate, lithium perchlorate, sodium perchlorate, barium perchlorate and calcium perchlorate. According to the invention, a flow adjusting range can be widened, working errors are reduced, and working stability and reliability are guaranteed.

Description

technical field [0001] The invention belongs to the technical field of engines, and in particular relates to a solid rocket ramjet adjusting device and the engine propellant used in the adjusting device. Background technique [0002] The solid rocket ramjet has a high specific impulse, can provide a long power range and maintain high-speed flight, has reliable combustion, compact structure, and is convenient for storage and maintenance. Cruise device. Modern missiles have high requirements on flying airspace and maneuverability. In order to adapt to the change of the air intake caused by the change of the outer trajectory, the gas flow must be effectively controlled to ensure that the solid rocket ramjet works near the design air-fuel ratio as much as possible. for optimum performance of the engine. At present, the main gas generator flow adjustment schemes include non-choked type, variable throat method and scroll valve method. The pressure of the afterburner of the non-...

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Problems solved by technology

The pressure of the afterburner chamber of the non-choked engine can be transmitted to the gas generator, and the gas flow can be adjusted according to the flight status, but its adjustment range is small and the adjustment ability is poor, so it is difficult to maintain a stable air-fuel ratio

The variable throat method uses the flow regulating valve to change the nozzle throat area of ​​the gas generator to adjust the gas flow, which can achieve a large flow adjustment range, but a large number of condensed phase particles in the combustion products of oxygen-poor solid propellants are prone to deposition , so that the nozzle of the gas generator is blocked, and the consequences are serious

In the vortex valve method, before the subsonic main flow of the gas generator enters the converging section of the clogged nozzle, the secondary gas flow (control flow) is injected radially into it to generate a control vortex, thereby realizing the gas flow adjustment, but this method Complex structure and immature technology

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