System for testing ultrasonic dynamic burning rate of solid propellant

Abstract

The invention discloses a system for testing ultrasonic dynamic burning rate of a solid propellant, comprising a burning chamber, a gas distribution unit and a testing and controlling unit, wherein an ultrasonic transmitting and receiving unit is arranged at the top or bottom of the burning chamber; the ultrasonic transmitting and receiving unit is composed of an ultrasonic probe and a coupling medium; the coupling medium is a cylinder; two end surfaces of the coupling medium are respectively closely contacted with a working surface of the ultrasonic probe and a sample of the solid propellant; and the testing and controlling unit is used for controlling initial temperature and pressure of the burning chamber, detecting temperature and pressure of the burning chamber, and real-time burning parameters of the solid propellant, controlling the ultrasonic waves of the ultrasonic probe for transmitting fixed frequencies, receiving echoes from a burning surface of the solid propellant, and collecting and processing data. The system can test parameters such as static burning rate, dynamic burning rate, burning rate pressure indexes, burning rate temperature sensitivity coefficients and the like; and the testing efficiency of the system is dozens of times than that of a static testing apparatus.

Description

Ultrasonic dynamic burning rate test system for solid propellants technical field The invention relates to a testing system for measuring the burning rate of solid propellants by an ultrasonic pulse echo method, which is used for measuring the dynamic burning rate of solid propellants and belongs to the technical field of testing instruments. Background technique The classic solid propellant static burning rate measurement methods such as the target line method and the acoustic emission method have been adopted by many scientific research institutes and production units due to their long history of development, mature technology, and detailed national standards. main method. However, they can only measure the average burning rate of the solid propellant, and cannot accurately measure the instantaneous burning rate of the solid propellant sample at each moment during the combustion process and the change of the burning rate during the combustion process, that is, the dynami...

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Problems solved by technology

Although this type of method can measure the dynamic burning rate of solid propellants, its application range is limited. When the solid propellant has a large combustion smoke, it is difficult to accurately distinguish the combustion surface, so it cannot be accurately measured.

This type of method is also unable to measure the influence of inhomogeneity (such as glue block) or defects (such as cracks, bubbles, etc.) in the internal physical and chemical structure of the solid propellant on the burning rate.

The engine method is to fill the solid propellant into a full-scale or scaled-down solid rocket motor and ignite it for a test run. Although this method can obtain comprehensive and accurate internal ballistic performance parameters, its measurement has high cost, low efficiency, and long cycle time. , low security and other deficiencies

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