Engine jet flame characteristic test device and method in atmospheric absorption wave band

Abstract

The invention discloses an engine jet flame characteristic test device and method in the atmospheric absorption wave band. The device comprises a Fourier spectrometer, a high-temperature calibration black body and a thermal infrared imager, wherein the Fourier spectrometer, the thermal infrared imager and an engine to be tested are all located in the plane of an engine test bed, the Fourier spectrometer and the body of the engine to be tested are located on the same side of a nozzle of the engine to be tested, and the thermal infrared imager is located on the other side of the nozzle of the engine to be tested. The test method comprises the steps that first, the atmospheric transmissivity of a tested environment is calculated, and a lens of the Fourier spectrometer is selected, and the position of the thermal infrared imager is chosen; second, the high-temperature calibration black body is used for carrying out multi-point radiometric calibration; third, the test device is started, the Fourier spectrometer carries out data acquisition, and the thermal infrared imager acquires infrared image data; finally, atmospheric correction processing is carried out on the acquired data. According to the engine jet flame characteristic test device and method in the atmospheric absorption wave band, the path length of radiation transfer is fully reduced, absorption of atmosphere to jet flame radiation is reduced, high-precision atmospheric correction is achieved through dynamic data, and the precision of test data is improved.

Description

technical field [0001] The invention relates to a test device and test method for engine jet flame characteristics, in particular to a test device and test method for engine jet flame characteristics in the atmospheric absorption band, which uses an infrared spectrometer combined with a thermal imager to measure engine tail jet flame infrared radiation data The method is applicable to the test of engine jet flame characteristics in the gas absorption band, and belongs to the field of engine characteristic test. Background technique [0002] The infrared radiation characteristic of engine jet flame is the key basic data for applications such as early warning and monitoring. Compared with the target surface radiation, the jet flame radiation of the engine has strong particularity, and the research difficulties are mainly reflected in: First, the flow field formed by the incomplete combustion of the engine has strong uncertainty, and the gas-condensation two-phase coupling body...

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Problems solved by technology

Compared with the target surface radiation, the jet flame radiation of the engine has strong particularity, and the research difficulties are mainly reflected in: First, the flow field formed by the incomplete combustion of the engine has strong uncertainty, and the gas-condensation two-phase coupling body exists at the same time. Due to the energy level transition mechanism of emission, scattering, and absorption, the flow field formation and radiation transfer mechanism are extremely complex; second, the radiation of the engine jet is concentrated at 2.7 μm and 4.3 μm, which belongs to the strong atmospheric absorption band and is absorbed by water vapor and carbon dioxide in the atmosphere. It is impossible to carry out long-distance radiation measurement experiments on the ground, space-based measurement methods are not yet available, and the accumulation of relevant basic data is basically blank.

[0003] At home and abroad, space-borne, ball-borne and airborne measurement methods are mainly used, but the test cost and complexity are relatively large

The journal article "Comparison of calculated and measured radiation from a rocket motor plume" (AIAA, 2001) tried to carry out the measurement of the radiation characteristics of the liquid engine in the wide band of the 4-5μm atmospheric window, but the data of the 4.3μm absorption band could not be obtained;

[0004] The journal article "Experimental and Computational Research on Jet Infrared Radiation of Solid Rocket Motor" (Acta Astronautica Sinica, Issue 01, 2008) introduces the jet flame measurement scheme in a vacuum environment. The combustion chamber pressure of the ruler rocket engine and the infrared radiation intensity of the jet flow were measured. Since the vacuum environment cannot measure the 1:1 high-thrust engine, this method has limitations and cannot be applied to the characteristic measurement of the rocket main engine.

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