Gas self-pressurization hybrid rocket engine

Abstract

The invention provides a gas self-pressurization hybrid rocket engine which comprises an oxidizing agent storage box, an oxidizing agent control valve, a check valve, an oxidizing agent injector, a spray pipe, a flow regulating valve, a poor-oxygen gas generator, a filter and a pressure reducer. A sealing piston is arranged in the oxidizing agent storage box. The sealing piston divides an inner cavity of the oxidizing agent storage box into two sealed cavities, an oxidizing agent is placed in one sealed cavity, one end of the poor-oxygen gas generator is a sealed end, the other end of the poor-oxygen gas generator is provided with the spray pipe, a grain is poured at the position of the sealed end, and the flow regulating valve is arranged in a cavity of the poor-oxygen gas generator in which a grain is not poured. The flow regulating valve divides the cavity in which a grain is not poured into two cavities, and the cavity close to the spray pipe is a secondary combustion chamber. According to the gas self-pressurization hybrid rocket engine, self-pressurization can be achieved, and the complexity of an oxidizing agent supply system can be simplified greatly.

Description

technical field [0001] The invention belongs to the field of engine design, in particular to a gas self-supercharging hybrid rocket engine. Background technique [0002] At present, solid-liquid hybrid rocket engines generally use a combination of liquid oxidant and solid fuel, which consists of a liquid oxidant storage tank, a liquid pipeline delivery system, a high-pressure gas cylinder or a turbo pump, an oxidant injector, a solid fuel combustion chamber, and a nozzle, etc. Partial composition. The working process of the solid-liquid hybrid rocket engine is: the oxidant is atomized through the injector and enters the pre-combustion chamber or gasification chamber upstream of the main fuel under the extrusion of the high-pressure cylinder or the drive of the turbo pump. Diffusion combustion is carried out with fuel pyrolysis gas in the channel, and finally high-temperature gas is generated and discharged through the nozzle to generate thrust. [0003] Traditional solid-l...

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Problems solved by technology

[0003] Traditional solid-liquid hybrid rocket engines use hydrocarbons such as HTPB and PE as fuel, add a small amount or no metal powder, and have low fuel density; in the process of diffusion combustion, the flow parameters and local mixing ratios at different positions on the combustion surface are different , will cause the difference in the fuel retreat rate, resulting in low combustion efficiency and difficulty in fully exerting the specific impulse performance; in the process of thrust adjustment, due to the large change in the oxygen-fuel ratio, the engine performance also changes greatly; in addition, affected by the solid fuel combustion surface Due to the limitation of the retreat rate, in order to obtain the required thrust, the traditional solid-liquid hybrid rocket engine usually adopts a porous and multi-segment charge structure. The charge structure is complex, the volume filling fraction is low, and it is easy to produce more residual charge

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