• Infrared and Laser Engineering
  • Vol. 52, Issue 12, 20230260 (2023)
Weibo Shi1, Haihao Sun1, Chunsheng Liu2, Shichang Liang1, and Anhua Shi1,*
Author Affiliations
  • 1Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • 2Beijing Institute of Electronic System Engineering, Beijing 100854, China
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    DOI: 10.3788/IRLA20230260 Cite this Article
    Weibo Shi, Haihao Sun, Chunsheng Liu, Shichang Liang, Anhua Shi. Analysis of the influence of aerodynamic heating in ascent stage on infrared radiation characteristics of high-speed aircraft in midcourse[J]. Infrared and Laser Engineering, 2023, 52(12): 20230260 Copy Citation Text show less

    Abstract

    ObjectiveInfrared radiation characteristics is the basis of midcourse infrared warning, detection, identification and track of high-speed aircraft. High-speed aircraft midcourse infrared radiation is closely related to surface temperature, which is related to ascent-stage aero-heating, space thermal radiation, heat-shield structure, and so on. In order to obtain high-speed aircraft’s midcourse infrared radiation in the complex environment background, it is necessary to study the influence of aero-heating, space thermal radiation, surface heat-shield radiating and structure heat conduction on the infrared radiation.MethodsTaking into account the influence of ascent-stage aero-heating, space thermal radiation, surface heat-shield radiating and structure heat conduction, making use of aerodynamic heating engineering computation model, space thermal heating computation model, and 1D multi-layer heat conduction computation method, the high-speed aircraft infrared radiation analysis technology is established, and high-speed aircraft midcourse temperature field and infrared radiation analysis is realized under the influence of aero-heating, space radiation heating, radiation heat dissipation, structure heat conduction, and so on.Results and DiscussionsThe computation temperature results match well with flight test results under typical working conditions (Fig.4-5), which verifies the validity of the computation model and methods. The ascent-stage aero-heating has a large effect on the midcourse surface temperature and infrared radiation (Fig.7-10). In the midcourse, the infrared radiation intensity in the wavelength range of 8-12 μm is notably larger than that of 3-5 μm. Therefore, choosing the wavelength range of 8-12 μm is more advantageous for high-speed aircraft midcourse detection (Fig.11).ConclusionsIn order to simulate the infrared radiation of the high-speed aircraft in midcourse flight, the temperature field and infrared radiation characteristics analysis technology is developed, considering the influence of ascent-stage aero-heating and so on. The technology is validated through comparison with flight test measurements. It is found that: the ascent-stage aero-heating has a large effect on the midcourse infrared radiation. In the midcourse, the infrared radiation intensity in the wavelength range of 8-12 μm is notably larger than that of 3-5 μm. Therefore, choosing the wavelength range of 8-12 μm is more advantageous for high-speed aircraft midcourse detection.
    $ \left\{ qw=hx(TwTr)hx=0LhxdxLhx=0.0296ρCpV(ρVx/μ)1/5Pr2/3Tr=T(1+rTγ12M2)rT=Pr3T=T+0.5(TwT)+0.22(TrT) \right. $(1)

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    $ \left\{ qbr=α(KnfmKn)qc+(KnKnc)qfmKnfmKncKnc=0.001Knfm=10 \right. $(2)

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    $ \left\{Missing \end{array}& & & \end{array}& & & \end{array}\end{array}\ S=\dfrac{{V}_{\infty }}{\sqrt{2RT{}_{\infty }}}\ \phi =\dfrac{\psi }{2}{{\rm{e}}}^{-{\eta }^{2}}\ \eta =S\mathrm{cos}\theta \ {\rm{erf}}(\eta )=\dfrac{2}{\sqrt{\pi }}{\displaystyle {\int }_{0}^{\eta }{{\rm{e}}}^{-{x}^{2}}{\rm{d}}x}\end{array}\right. $(3)

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    $ {q_{sun}} = {\alpha _s}{I_s}{A_{pro}} $(4)

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    $ {q_{earth}} = {\alpha _{IR}}{I_{earth}}{\varphi _{2\;{\rm{mm}}}} $(5)

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    $ \left\{ qref=αsαrIsφ3mmφ3mm=φ2mmcosΦ \right. $(6)

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    $ {\rho _s}{C_s}\frac{{\partial T}}{{\partial t}} = \frac{\partial }{{\partial y}}\left( {{k_s}\frac{{\partial T}}{{\partial y}}} \right) $(7)

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    $ {\rho '_s}{C'_s}\frac{{\partial T'}}{{\partial t}} = \frac{\partial }{{\partial y}}\left( {{{k'}_s}\frac{{\partial T'}}{{\partial y}}} \right) $(8)

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    $ T = T' $(9)

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    $ {\rho ''_s}{C''_s}\frac{{\partial T''}}{{\partial t}} = \frac{\partial }{{\partial y}}\left( {{{k''}_s}\frac{{\partial T''}}{{\partial y}}} \right) $(10)

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    $ T^{\prime}=T^{\prime \prime} $(11)

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    $ T'' = {T_b} $(12)

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    $ {\rm{d}}{I_\lambda } = \varepsilon \cdot {L_\lambda }\cos \vartheta \cos \varphi {\rm{d}}A{\rm{d}}\lambda $(13)

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    Weibo Shi, Haihao Sun, Chunsheng Liu, Shichang Liang, Anhua Shi. Analysis of the influence of aerodynamic heating in ascent stage on infrared radiation characteristics of high-speed aircraft in midcourse[J]. Infrared and Laser Engineering, 2023, 52(12): 20230260
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