Rocket engine gas temperature testing method in consideration of multi-wavelength spectral radiation

Abstract

The invention discloses a rocket engine gas temperature testing method in consideration of multi-wavelength spectral radiation. On the basis of the Planck's law, through acquiring gas radiation spectrum wavelengths and corresponding spectral radiation intensity data, an actually-measured relationship curve between the gas spectrum wavelength and the spectrum intensity is matched with a Planck curve at different temperatures, and according to a matching degree, the actual temperature of the rocket engine gas is determined. The temperature capable of being tested can be as high as 5000K, which is far beyond a temperature measurement range of a thermocouple, and the method of the invention is more applicable to high-temperature measurement of the rocket engine gas. Hundreds of wavelengths and corresponding spectral radiation intensity data can be acquired, precision of fitting the wavelengths and the spectral radiation intensity data is improved, and the anti-interference ability is strong. Compared with a dual-wavelength temperature measurement method and an eight-wavelength spectrometer temperature measurement method, the gas temperature can be calculated more accurately, and applicability is stronger.

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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