Polarization imaging based supersonic/hypersonic flow field measurement method

A polarization imaging and hypersonic technology, which is applied in the direction of measuring devices, machine/structural component testing, instruments, etc., can solve the problems of quantitative measurement error and uneven light intensity of supersonic/hypersonic flow field, and achieve good anti-interference ability , high-precision effect

Active Publication Date: 2018-10-12
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0006] The present invention provides a method for measuring supersonic / hypersonic flow field based on polarization imaging to solve the technical problem that existing NPLS technology tends to produce large errors in the quantitative measurement of supersonic / hypersonic flow field due to the inhomogeneity of light intensity

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  • Polarization imaging based supersonic/hypersonic flow field measurement method
  • Polarization imaging based supersonic/hypersonic flow field measurement method
  • Polarization imaging based supersonic/hypersonic flow field measurement method

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[0040] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0041] Based on the existing NPLS-based technology, the present invention comprehensively utilizes the laser scattering characteristics of nanoparticles and polarization imaging technology, and rationally adjusts the polarization state of the incident ray polarization laser and the angular position between the polarization imaging system and the scattered light, and utilizes the polarization imaging system The polarization state of the nanoparticle scattering light in the supersonic / hypersonic flow field is measured, and the relationship between the particle scattering polarization state and the flow field parameters is used to realize the visualization and fine measurement of the flow field. A...

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Abstract

The invention discloses a polarization imaging based supersonic / hypersonic flow field measurement method. The method comprises the following steps: optimizing a line-biased laser light source for incident illumination such that the polarization degree of the incident line-biased laser is within a set threshold range; adjusting the polarization direction of the incident line-biased laser and the receiving angle of a polarization imaging system so as to make a scattering signal of nanoparticles at the imaging angle of the polarization imaging system strongest; using the polarization imaging system to image the supersonic / hypersonic flow field to obtain a polarization-related result of the scattered light signal of the nanoparticles, wherein the polarization-related result includes the polarization degree, the polarization angle, and the ellipsometric angle of the scattered light of the nanoparticles; and converting the density field of the supersonic / hypersonic flow field based on the polarization information to obtain density distribution of the supersonic / hypersonic flow field. The invention utilizes the polarization parameter information of the scattering signal of the nanoparticles to realize the visualization and fine measurement of the flow field, and has good anti-interference ability and high precision.

Description

technical field [0001] The invention relates to the technical field of flow field measurement, in particular to a method for measuring a supersonic / hypersonic flow field based on polarization imaging. Background technique [0002] The fine measurement of supersonic / hypersonic flow field is an important content of supersonic and hypersonic flow mechanism research. The aerodynamic performance of high-speed aircraft and the thermal protection of the aircraft surface are closely related to the supersonic / hypersonic flow structure outside the aircraft. It is necessary to study the flow structure through experiments to provide a basis for the design of the aircraft. [0003] Existing methods for supersonic / hypersonic flow structure measurement include schlieren, shadow, interference, particle image velocity field (PIV), filtered Rayleigh scattering (FRS) and laser-induced fluorescence (PLIF) and other methods (Fan Jiechuan. Modern Mobile Display Technology [M]. Beijing: National ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 何霖
Owner NAT UNIV OF DEFENSE TECH
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