Bottom row propellant transient pressure relief combustion instability characteristics test device

Abstract

The invention discloses a device for testing the transient-state pressure release combustion instability characteristic of a base bleed propellant. According to the device, a transparent observation window, an ignition combustion chamber, a temperature measuring component, a pressure release component and a pressure sensor are mounted on a main combustion chamber; the ignition combustion chamber is used for igniting an explosive bar to be tested; a micro thermoelectric couple is hermetically mounted on the temperature measuring component; when the pressure inside the main combustion chamber reaches the pressure resistance limit of the pressure release component, transient pressure release is achieved; when the pressure sensor is used for measuring the pressure change inside the main combustion chamber in the combustion process, a high-speed camera is used for shooting the combustion situation of the explosive bar to be tested through an optical path converter and the transparent observation window, and a thermocouple temperature measuring device is used for testing the solid-phase temperature distribution of the explosive bar to be tested; a data acquirer is used for acquiring and recording the output data of the pressure sensor, and the output data together with the images shot by the high-speed camera and the temperature measurement data measured by the thermocouple temperature measuring device are transmitted into a computer to be analyzed and processed. By adopting the device, the combustion velocity, the combustion state and the solid phase temperature distribution of the base bleed propellant under different initial pressure of release pressure and pressure drop velocities can be measured.

Description

technical field [0001] The invention belongs to the technical field of solid propellants, in particular to a device for testing the combustion instability characteristics of bottom-row propellant transient pressure relief. Background technique [0002] AP / HTPB composite propellants have been widely used in solid rocket motors and bottom exhaust range-extending technology of large-caliber artillery. In order to precisely control the trajectory of the rocket and improve its working flexibility, it is usually necessary to achieve thrust termination through the thrust reverser device. One of the most attractive methods is to use rapid pressure reduction to extinguish the propellant; and the AP / HTPB used in the bottom discharge bomb The moment the propellant exits the muzzle, the propellant will experience a transient pressure relief process that is worse than that of the rocket engine, which may cause combustion instability and affect the shooting accuracy of the projectile. ...

AI Technical Summary

Problems solved by technology

They used the ignition method of black powder to ignite the grain of the tested sample. For double-base propellants, this method is easy to achieve ignition, but practice shows that this method of ignition is unreliable for composite propellants.

Also, they failed to test temperature changes during propellant combustion

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