A Method for Measuring Rocket Engine Gas Temperature Considering Multi-Wavelength Spectral Radiation

Abstract

The invention discloses a rocket engine gas temperature testing method considering multi-wavelength spectral radiation. The invention is based on Planck's law, by collecting gas radiation spectral wavelength and corresponding spectral radiation intensity data, the actual measurement of gas spectral wavelength and spectral intensity The relationship curve is matched with the Planck curve at different temperatures, and the actual temperature of the rocket engine gas is determined according to the matching degree; the test temperature of the present invention can reach up to 5000K, which is far beyond the temperature measurement range of the thermocouple, and is more suitable for rockets High-temperature measurement of engine gas; the invention can collect hundreds of wavelengths and corresponding spectral radiation intensity data, improves the accuracy of wavelength and spectral radiation intensity data fitting, and has strong anti-interference ability. Compared with dual-wavelength temperature measurement method and 8-wavelength spectrometer temperature measurement, it can calculate the gas temperature more accurately and has stronger applicability.

Description

technical field [0001] The invention relates to a method for testing the gas temperature of a rocket engine, belonging to the technical field of temperature measurement, in particular to a method for testing the temperature of a rocket engine gas considering multi-wavelength spectral radiation. Background technique [0002] Rocket engine gas temperature has important reference value in the research of propellant combustion mechanism, engine structure design and engine anti-ablation design. Gas temperature, on the one hand, is an important energy parameter of rocket engine propellant, which provides design guidance for propellant formula adjustment; on the other hand, it is the main reference basis for characterizing flow field characteristics and internal ballistic performance of rocket engine; The important parameters of the ablation performance of the thermal insulation layer in the rocket engine provide the design basis for the thermal protection of the engine. However, ...

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Problems solved by technology

This dual-wavelength temperature measurement method still has certain defects: (1) the dual-wavelength temperature measurement method can only select two specific wavelength intervals, and cannot characterize the relationship between spectral radiation and temperature in other bands; (2) this method mainly Measurement of propellant condensed phase products (mainly Al 2 o 3 ), ignoring the influence of a large number of gas-phase products on the spectral radiation, it can only be applied to specific types of propellants; (3) This method requires the user to measure the spectral radiation and gas temperature of other propellants in advance, so as to fit The relationship between spectral radiation and temperature is applied to the measurement of unknown propellant combustion temperature. The process is cumbersome and cannot be further applied.

The disadvantages of this method are: (1) The spectrometer can only collect the spectral radiation intensity data of 8 wavelengths, the data is less, and it is easily interfered by the radiation spectrum of the non-measurement object; (2) This method needs to pre-assume the emission of the measured object rate model, when the actual emissivity model of the measured target does not match the assumed situation, the error is very large

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