Interlayer ablation carbonization controllable experimental device for double-pulse solid rocket engine

Abstract

The invention belongs to the field of rocket engines, and particularly relates to an interlayer ablation carbonization controllable experimental device for a double-pulse solid rocket engine. The interlayer ablation carbonization controllable experimental device for the double-pulse solid rocket engine comprises a three-way combustion chamber cavity, an end combustion charging assembly, a spray pipe assembly and an interlayer ablation fixing assembly; the spray pipe assembly and the interlayer ablation fixing assembly are respectively in threaded connection with two opposite through holes, andthe end combustion charging assembly is in threaded connection with the other through hole; after a grain in the end combustion charging assembly is ignited, fuel gas passes through the combustion chamber cavity and is discharged through the spray pipe assembly, and meanwhile, the fuel gas in the combustion chamber cavity makes direct contact with an interlayer ablation test piece fixed on the interlayer ablation fixing assembly. The interlayer ablation carbonization controllable experimental device for the double-pulse solid rocket engine provided by the invention can simulate the working environment of the real double-pulse solid rocket engine, the type, the structure size and the working pressure of a propellant in the end combustion charging assembly can be adjusted, and the controllability of single-side ablation of an interlayer is realized.

Description

technical field [0001] The invention belongs to the field of rocket engines, and in particular relates to a controllable experimental device for ablation and carbonization of interlayers of double-pulse solid rocket engines. Background technique [0002] The solid rocket motor is a jet propulsion device that ejects high-speed gas flow to generate reaction force and moves forward. It is mainly composed of front head, combustion chamber, propellant charge, nozzle, ignition device and other components. With the advantages of low cost and reliable operation, it is an advanced solid power device for rocket missile weapons. However, traditional solid rocket motors still lack flexibility in terms of energy management, ballistic optimization, and controllability, which hinders further use and development. For this reason, a concept of a double-pulse solid rocket motor (referred to as a double-pulse motor) was proposed. This motor uses an isolation device to separate the combustion ...

AI Technical Summary

Problems solved by technology

[0004] With the widespread use of high-energy propellants and the design of high-specific impulse engines, the combustion chamber of solid rocket motors needs to withstand large thermal loads and internal pressure loads for a long time during the working process. Therefore, as a soft-pulse double-pulse engine The core component, the design of the interlayer isolation device is very important. Insufficient thickness, poor quality or insufficient strength of the interlayer will lead to the destruction of the structural integrity of the second pulse grain and the interlayer system, or the premature ignition of the second pulse grain, causing Deflagration accidents; on the contrary, the redundant design of the interlayer structure will cause the negative mass of the engine to increase, which will seriously affect the working performance of the engine

The double-layer double-pulse solid rocket motor has a large diameter and long working time, and the I-pulse charge mostly adopts the form of inner hole, wing column, star-hole charge, etc., resulting in a large mass of the I-pulse charge. The cost of designing and researching the compartment type pulse isolation device is relatively high for the ground static experiment of the pulse engine

Images