A test device and test method for solid propellant burning rate/burning temperature

Abstract

The invention discloses a test device for burning rate / burning temperature of solid propellants and a test method thereof. The device comprises a constant volume burner body, plugs one and two, an ignition electrode arranged on the plug one and The pressure relief valve, and the temperature sensor and pressure sensor arranged on the plug 2; the constant volume burner body is a cylindrical chamber structure, one end of the constant volume burner body is connected to the plug 1 through a thread, and the other end is connected to the plug through a thread. First two, the constant volume burner body is provided with a clamping device, and the propellant grain is fixed in the clamping device, and a data acquisition and processing unit is also provided outside the constant volume burner body, and the data acquisition and processing unit is respectively connected with the pressure sensor , Temperature sensor connection. The invention satisfies the requirements of propellant energy quantitative testing, can simulate the high-pressure environment of solid propellant application, and can obtain the burning rate data and burning temperature data of the propellant under the high pressure state, thereby providing a comparative advantage for the development of the propellant. Solid design input.

Description

technical field [0001] The invention relates to a burning rate / burning temperature test device, in particular to a solid propellant burning rate / burning temperature test device and a test method thereof under airtight conditions, belonging to the field of solid propellant combustion performance testing. Background technique [0002] As a halon alternative fire extinguishing technology, the solid propellant fire extinguishing technology is a kind of solid reactant as a propellant, through a controlled rapid reaction, a large amount of inert gas products (such as nitrogen, water vapor and CO 2 etc.) to drive the release of the fire extinguishing medium to achieve the effect of extinguishing a fire. This technology has been widely used in the field of fire extinguishing in small spaces in aircraft equipment due to its fast response speed, small footprint, storage at normal pressure, rich inert medium, and release of fire extinguishing medium within 100ms. However, the solid pr...

AI Technical Summary

Problems solved by technology

However, since the test of the airtight explosive device requires complex processing of the experimental data, and the test method is based on the theory of gunpowder combustion, it needs to go through a series of assumptions and simplifications, which brings certain errors

In addition, at present, empirical formulas are generally used to correct the heat loss of the closed blaster test, without considering the influence of pressure and radiation heat transfer changes in the propellant combustion stage on the heat loss process, less consideration is given to the heat transfer between the gas and the inner wall of the closed blaster, and Influence of Heat Loss on the Propellant Flame Temperature in a Sealed Exploser

The literature "Study on Measuring Propellant Burning Velocity at High Pressure by Closed Burner Method" pointed out that although the working time of the closed burner is very short, the pressure loss caused by the loss of heat dissipation is very large, even reaching 30% at low pressure

Moreover, through a large number of experimental comparisons, the average heat loss correction method, the reverse heat loss correction method, and the heat transfer calculation heat loss correction method are not very accurate and have large errors.

Therefore, there is a large difference between the burning rate calculated based on the heat dissipation loss and the actual

In the patent "a dynamic burning rate test device for propellant" (CN104048563B), the method of measuring the burning rate of solid propellant by using a closed detonator is introduced in detail, but the burning rate is not calculated using the burning temperature as an input parameter

[0007] Therefore, from the technical information retrieved so far, there is no public report about using the combustion temperature of the propellant under airtight conditions as an input parameter to calculate the conduction combustion rate.

Images