Combustion flow stabilizing device of solid propellant and solid engine combustion generator

Abstract

The invention discloses a combustion flow stabilizing device of a solid propellant and a solid engine combustion generator. The combustion flow stabilizing device of the solid propellant comprises a fuel gas flow guide channel, and a plurality of fuel gas holes are arranged on the fuel gas flow guide channel in an array mode; wherein the fuel gas flow guide channel is arranged in an inner hole of the solid propellant, and a flow guide gap is formed between the fuel gas flow guide channel and the wall of the inner hole of the solid propellant; and fuel gas generated by combustion of the solid propellant flows into the fuel gas flow guide channel through the flow guide gap and the fuel gas holes and is guided to a spray pipe of the solid engine through the fuel gas flow guide channel. The fuel gas flow guide channel is arranged in the inner hole of the solid propellant, the fuel gas generated during combustion of the solid propellant is guided to the spray pipe of the solid engine through the fuel gas flow guide channel, the erosion combustion influence of the solid propellant can be effectively restrained, it is ensured that the combustion speed of the solid propellant is stable, and the thrust output stability of the solid engine can be improved.

Description

technical field [0001] The invention relates to the technical field of solid motors, in particular to a solid propellant combustion stabilizing device and a solid motor combustion generator. Background technique [0002] Solid rocket motors are widely used due to their simple structure and high reliability. In order to meet the stable thrust output requirements of solid motors, a certain configuration of inner-porous solid propellants is usually used. Restricted by its own structural characteristics, the inner-porous solid propellant often erodes and burns during the combustion process of the propellant, which disturbs the designed combustion law of the solid propellant, resulting in a large deviation between the actual thrust output and the theoretical value. Erosion combustion specifically refers to the influence of the gas flow state parallel to the solid propellant combustion surface on the charge burning rate. In general, erosive combustion results in an increase in t...

AI Technical Summary

Problems solved by technology

Especially under micro-scale conditions, the erosion and combustion of the inner-porous solid propellant is more obvious, which seriously affects the stability of the thrust output of the solid engine

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