A gas-filled temperature measuring system for a solid engine

Abstract

The invention relates to an inflatable temperature measuring system for a solid engine, which is composed of an engine, an air supply system and a test system. The engine is fixed on the test bench, and the air supply system and the test system are located outside the engine; The valve, solenoid valve, and one-way valve are connected to the air inlet through the pipeline; the pressure sensor is matched with the pressure measuring hole, the thermocouple is matched with the temperature measuring hole, and the pressure sensor and the thermocouple are respectively connected with the computer; the non-contact temperature measuring device is fixed On the side of the transparent window, and the collection head is opposite to the transparent window, the non-contact temperature measuring device is connected with the computer. By filling high-pressure gas and reducing the cross-sectional area of ​​the outlet of the transparent window base, a plug can be formed at the outlet to generate a stable gas to protect the quartz glass of the transparent window, and to ensure sufficient light transmission in the cross-sectional area. The temperature of the combustion chamber of the engine can be measured by means of conventional and non-contact methods, and the simultaneous and accurate measurement of the same gas temperature by two different methods can be realized.

Description

technical field [0001] The invention relates to the technical field of solid rocket motor testing, in particular to an air-filled temperature measurement system for a solid rocket motor. Background technique [0002] The combustion chamber temperature of solid rocket motors is an important index parameter for the study of engine structure design, anti-ablation design and propellant combustion mechanism. The temperature and distribution of the propellant combustion flame are not only important parameters to characterize the characteristics of the flow field and the performance of the rocket engine, but also provide design guidance for predicting the physical and chemical process of the propellant combustion and establishing a reasonable mathematical and physical model. [0003] At present, the application of the device for measuring the temperature of a rocket engine using a thermocouple is relatively simple. It is only necessary to weld a temperature measurement base on the ...

AI Technical Summary

Problems solved by technology

However, the limitation of using this device for temperature measurement is that the general thermocouple can only measure the temperature below 2300 °C, it is difficult to measure the high temperature of the engine, and the thermocouple is easy to fuse

[0005] However, the disadvantage of the temperature measuring device is that the high-temperature gas generated when the engine is working will directly contact the glass surface, causing damage to the glass to a certain extent; the combustion products of the engine easily cover the transparent glass surface and hinder the collection of light waves, making the measured The temperature is not the real temperature of the gas, but the temperature of the window attachment

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