Electric arc wind tunnel free flow-shock wave layer spatial resolution measurement device based on PLIF spectrum

A spatially resolved and free technology that can be used in measurement devices, machine/structural component testing, aerodynamic testing, etc.

Inactive Publication Date: 2021-06-25
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

The use of optical non-contact measurement methods is currently the main technical means for high-temperature gas flow diagnosis, but the current measurement methods based on emission spectra and laser absorption spectra generally can only obtain spatial point and line averaged flow field signals. However, planar laser-induced fluorescence spectroscopy can realize two-dimensional space resolution measurement, which provides a high-precision and comprehensive measurement method for thermal environment prediction, thermal protection structure design and assessment of refined thermal protection test system

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  • Electric arc wind tunnel free flow-shock wave layer spatial resolution measurement device based on PLIF spectrum

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Embodiment Construction

[0026] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, but not to limit the present invention. In addition, it should be noted that, for the convenience of description, only some structures related to the present invention are shown in the drawings but not all structures.

[0027] figure 1 It is a structural diagram of an arc wind tunnel free flow-shock layer spatial resolution measurement device based on PLIF spectrum in an embodiment of the present invention, including: a pump laser unit 4, a tunable laser unit 5, a beam splitter 6, and a wavelength meter 7 , energy meter 8, prism 9, optical path shaping unit 10, optical filter 11, data acquisition unit 12, data analysis terminal 13, signal synchronization delay generator 14.

[0028] The external arc heater 1 heats the incoming t...

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Abstract

The invention relates to an electric arc wind tunnel free flow-shock wave layer spatial resolution measurement device based on the PLIF spectrum. The device comprises a pump laser unit, a tunable laser unit, a beam splitter, a wavelength meter, an energy meter, a prism, an optical path shaping unit, an optical filter, a data acquisition unit, a data analysis terminal and a signal synchronization delay generator; an external arc heater heats an entered test medium to form high-temperature airflow; the high-temperature airflow is expanded and accelerated by an external spray pipe to form supersonic free flow at an outlet of the external spray pipe; the supersonic free flow is used for testing and examining a test model mounted at the downstream of the external spray pipe; and a free flow-shock wave layer transition area flow field is formed on the near wall surface of the test model. According to the device of the invention, spatial resolution and quantitative measurement of the flow field in the reentry process of an aircraft can be realized.

Description

technical field [0001] The invention relates to an arc wind tunnel free flow-shock layer space resolution measuring device based on PLIF spectrum, which is used for measuring space resolution parameters of high-enthalpy air flow field in ground simulation tests, and belongs to the research field of aircraft ground aerodynamic thermal tests. Background technique [0002] The arc wind tunnel is the main equipment for the thermal protection test and assessment of hypersonic aircraft. The aircraft is faced with severe aerodynamic heating: it includes complex dissociation and ionization processes, as well as thermodynamic translation, vibration, rotation, and electronic temperature changes, considering the impact of aircraft heat-resistant material ablation-catalysis-oxidation, aircraft heat-resistant materials and airflow The reentrant flow field in the interaction process is very complex, with strong non-equilibrium and non-uniform characteristics. For the research on the re-e...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 曾徽周凯朱旭闫宪翔欧东斌
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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