Staged supercharged combustion solid rocket motor

Abstract

The invention discloses a staged pressurized combustion solid-propellant rocket engine. The staged pressurized combustion solid-propellant rocket engine comprises a front primary combustion chamber, arear primary combustion chamber, a pressurization chamber and a main combustion chamber which are successively connected with each other along an axial direction, wherein the rear end of the main combustion chamber is connected with an injection pipe; an outer pressurization channel and an inner pressurization are arranged in the pressurization chamber; the inner pressurization channel is axiallyconnected with the front primary combustion chamber and the main combustion chamber so as to pressurize the gas flow passing through the inside of the inner pressurization channel; the inner pressurization channel is axially connected with the rear primary combustion chamber through the front primary combustion chamber; the outer pressurization channel is axially connected with the rear primary combustion chamber and the main combustion chamber so as to pressurize the gas flow passing through the inside of the outer pressurization channel and convey the gas flow to the main combustion chamber; two pressurized gas flows are mixed and combusted. Through the staged pressurized combustion solid-propellant rocket engine, a fuel-rich propellant and an oxygen-rich propellant are used for respectively carrying out primary combustion; the combustion temperature and the pressure are kept in a low controllable range; the mass of housings and heat insulation layers of the primary combustion chambers can be reduced to a great extent; greater propulsive force can be obtained after carrying out pressurized secondary combustion.

Description

technical field [0001] The invention belongs to the field of aerospace science and technology, and in particular relates to a staged pressurized combustion solid rocket motor. Background technique [0002] At present, the working method adopted by the solid rocket motor is to solidify the oxidant and propellant in a certain proportion in advance into an integral propellant grain. After the propellant is ignited, high-temperature and high-pressure gas is generated, which is fully burned in the combustion chamber. Then, it is discharged through the nozzle to generate the power required for aircraft flight or attitude adjustment. [0003] With the development of aerospace technology, solid rocket motors are also constantly improving. The current research and development trend of solid rocket motors is to pursue high energy density, high energy performance and higher mass ratio, which refers to the ratio of propellant mass to engine mass. However, since the oxidant and the pr...

AI Technical Summary

Problems solved by technology

However, since the oxidant and the propellant are solidified together, the gas generated by the combustion of the propellant will generate a very high temperature, which will have a great impact on the engine's adiabatic structure, negative mass, and combustion instability.

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