Multi-target-line dynamic combustion performance testing system for solid propellant

Abstract

The invention discloses a multi-target-line dynamic combustion performance testing system for a solid propellant, which comprises a combustion chamber and gas distribution unit, a test and control unit and a data collecting and processing unit, wherein the combustion chamber and gas distribution unit comprises a combustion chamber, a constant-temperature tank, a high-pressure nitrogen cylinder, a buffer nitrogen cylinder, a relevant valve pipeline, a nitrogen booster pump and a multi-target-line explosive support used for fixing a sample to be tested, wherein one end of the multi-target-line explosive support is provided with an ignition wire connecting post, a ground wire connecting post and 6 to 10 target line connecting posts in the combustion chamber; and the data collecting and processing unit is used for dispatch and control of all function blocks of the testing and controlling unit, analysis and processing of tested data and data management. The testing system can reflect the change of the combustion speed of the solid propellant with the change of pressure by stages, and belongs to the range of testing of dynamic combustion speed; and the traditional target line method and the underwater acoustic emission method can only test the static combustion speed in a single constant-pressure condition, therefore, the testing system disclosed by the invention can obtain a conclusion closer to the actual combustion condition of the solid propellant in a solid-propellant rocket engine.

Description

Solid propellant multi-target line quasi-dynamic combustion performance test system technical field The invention relates to a testing system for quasi-dynamic combustion performance of solid propellant. Background technique The burning rate of solid propellant refers to the distance that the solid phase disappears along the normal direction of the solid propellant surface per unit time, referred to as the burning rate of solid propellant. It determines the energy release rate of solid propellants, and is also the core parameter for calculating other combustion properties of solid propellants (burning rate pressure index, burning rate temperature sensitivity coefficient, erosion ratio, etc.). Regardless of the changes in the pressure, initial temperature, air velocity and other influencing factors during combustion, they will eventually be reflected in the changes in the burning rate. In addition, it also directly affects the ballistic performance, flight speed and workin...

AI Technical Summary

Problems solved by technology

At present, the commonly used solid propellant burning rate test method can only test the burning rate of samples with a single pressure and temperature. When testing the burning rate pressure index and burning rate temperature sensitivity coefficient, it is necessary to repeat the operation dozens or even dozens of times. The cycle is long, so a simple, efficient, and fast method for testing the combustion performance of solid propellants is needed to shorten the production cycle of solid propellants

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