Method for testing multi-target line quasi dynamic combustion performance of solid propellant

Abstract

The invention discloses a method for testing the multi-target line quasi dynamic combustion performance of a solid propellant, comprising the following steps: (1) testing static burning rates of a solid propellant to be tested under various pressures from low pressure to high pressure, so as to obtain the relation curve of the average combustion rate and pressure, the relation curve of the maximum effective combustion rate and the test pressure, and the relation curve of the minimum effective combustion rate and the test pressure; (2) performing a combustion pressurization test for a solid propeller sample under a close state, so that the pressure reaches the pressure range to be tested; (3) drilling 6-10 target holes on the covered solid propeller sample, and enabling the target lines and an ignition wire to pass through the target holes; (4) predetermining an initial pressure and an initial temperature, igniting the solid propeller sample in a close combustion chamber, and recording the fusing time of each target line during the combustion procedure of the solid propeller sample; and (5) obtaining the dynamic relation of the combustion length, pressure, temperature and time during the combustion procedure of the solid propeller via analysis, and calculating the combustion rate, combustion rate pressure index and combustion rate temperature sensitive coefficient of the solid propeller sample in a certain pressure range. The method disclosed by the invention is suitable for fast detecting performance, controlling quality and the like for each batch of products during the production procedure of the solid propeller, and can shorten the research and production period of the solid propeller and reduce the cost.

Description

technical field [0001] The invention relates to a method for testing the burning rate of a solid propellant. Background technique [0002] 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 working stability of the rocket engine. Therefore, the burning rate of solid propellant is on...

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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