Testing device for burning speed of propellant under tensile state

Abstract

The invention discloses a testing device for the burning speed of a propellant under the tensile state, which is used for measuring the burning rule of the propellant under the tensile state. A constant-temperature and constant-pressure box is fixed on a working rack; the part between the inner wall and the outer wall of the constant-temperature and constant-pressure box is filled with an insulating layer; symmetrical insulating water pipes are arranged on the inner side of the insulating layer; a propellant tensile device is fixed in the constant-temperature and constant-pressure box; and a nitrogen gas cylinder is positioned at one side of the working rack and is communicated with the constant-temperature and constant-pressure box by a pipeline. The temperature in the constant-temperature and constant-pressure box is controlled by heating or cooling so as to realize testing for the burning speed of the propellant under the tensile state at different temperatures; high-pressure inert gas of the nitrogen gas cylinder is inputted into the constant-temperature and constant-pressure box to adjust the pressure in the constant-temperature and constant-pressure box, so that the pressure is maintained at given pressure, and the burning speed of the propellant under the tensile state at different pressures can be tested; the tensile amount of a tensile screw rod is controlled to control the tensile amount of the propellant, so that the burning speed of the propellant under the different tensile states can be tested. The testing device disclosed by the invention is simple in structure, low in cost and convenient to install.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motors, and in particular relates to a propellant burning rate testing device in a stretched state. Background technique [0002] The solid propellant grain is not only the power source but also one of its structural components in the solid rocket motor. Therefore, the internal ballistic performance of the engine is closely related to the structural characteristics of the propellant grain. When the solid propellant grain is subjected to external loads, due to its low tensile modulus, large deformation will occur, and the engine pressure, thrust, working time, total stroke, etc. will change, and all of them are related to the change of solid propellant burning rate Relatedly, changes in the burning rate affect the gas generation rate inside the engine, thereby affecting the ballistic performance inside the engine. There are different methods for measuring the burning rate of solid propellants...

AI Technical Summary

Problems solved by technology

When the solid propellant grain is subjected to external loads, due to its low tensile modulus, large deformation will occur, and the engine pressure, thrust, working time, total stroke, etc. will change, and all of them are related to the change of solid propellant burning rate Related, changes in the burning rate affect the gas generation rate inside the engine, thereby affecting the ballistic performance inside the engine

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