Review on active thermal protection and its heat transfer for airbreathing hypersonic vehicles

Zhu, Yinhai; Peng, Wei; Xu, Ruina; Jiang, Pei-Xue

doi:10.1016/j.cja.2018.06.011

Cited by 217 publications

(40 citation statements)

References 153 publications

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“…When the vehicle re-enters into the atmosphere, it would encounter a serious aerodynamic environment (1) , and many active and passive concepts have been proposed and studied in order to decrease the drag force around the tip of the vehicle, as well as the combustion chamber inter walls (2) . The design of the thermal protection system is very critical for the vehicles (3) .…”

Section: Introductionmentioning

confidence: 99%

Influences of lateral jet location and its number on the drag reduction of a blunted body in supersonic flows

Liao

et al. 2020

Aeronaut. j.

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The analysis of the aerodynamic environment of the re-entry vehicle attaches great importance to the design of the novel drag reduction strategies, and the combinational spike and jet concept has shown promising application for the drag reduction in supersonic flows. In this paper, the drag force reduction mechanism induced by the combinational spike and lateral jet concept with the freestream Mach number being 5.9332 has been investigated numerically by means of the two-dimensional axisymmetric Navier-Stokes equations coupled with the shear stress transport (SST) k-ω turbulence model, and the effects of the lateral jet location and its number on the drag reduction of the blunt body have been evaluated. The obtained results show that the drag force of the blunt body can be reduced more profoundly when employing the dual lateral jets, and its maximum percentage is 38.81%, with the locations of the first and second lateral jets arranged suitably. The interaction between the leading shock wave and the first lateral jet has a great impact on the drag force reduction. The drag force reduction is more evident when the interaction is stronger. Due to the inclusion of the lateral jet, the pressure intensity at the reattachment point of the blunt body decreases sharply, as well as the temperature near the walls of the spike and the blunt body, and this implies that the multi-lateral jet is beneficial for the drag reduction.

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Section: Introductionmentioning

confidence: 99%

Influences of lateral jet location and its number on the drag reduction of a blunted body in supersonic flows

Liao

et al. 2020

Aeronaut. j.

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“…In particular, thermal management technology is urgently required for advanced aerospace vehicles, including supersonic combustion ramjet (scramjet) and rocket engines. These vehicles are designed to sustain high heat fluxes, and require a regenerative cooling system to dissipate the huge heat load [4][5][6]. In regenerative cooling systems, supercritical hydrocarbon fuel is employed as a coolant, prior to use as a propellant.…”

Section: Introductionmentioning

confidence: 99%

Experiments on Heat Transfer of Supercritical Pressure Kerosene in Mini Tube under Ultra-High Heat Fluxes

et al. 2020

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Heat transfer of supercritical-pressure kerosene is crucial for regenerative cooling systems in rocket engines. In this study, experiments were devoted to measure the heat transfer of supercritical-pressure kerosene under ultra-high heat fluxes. The kerosene flowed horizontally in a mini circular tube with a 1.0 mm inner diameter and was heated uniformly under pressures of 10–25 MPa, mass fluxes of 8600–51,600 kg/m2 s, and a maximum heat flux of up to 33.6 MW/m2. The effects of the operating parameters on the heat transfer of supercritical-pressure kerosene were discussed. It was observed that the heat transfer coefficient of kerosene increases at a higher mass flux and inlet bulk temperature, but is little affected by pressure. The heat transfer of supercritical-pressure kerosene is classified into two regions: normal heat transfer and enhanced heat transfer. When the wall temperature exceeds a certain value, heat transfer is enhanced, which could be attributed to pseudo boiling. This phenomenon is more likely to occur under higher heat flux and lower mass flux conditions. In addition, the experimental data were compared with several existing heat transfer correlations, in which one of these correlations can relatively well predict the heat transfer of supercritical-pressure kerosene. The results drawn from this study could be beneficial to the regenerative cooling technology for rocket engines.

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“…In order to protect the aircraft from damage under aerothermodynamic loads, design of the nose cap is particularly important. Accurate response prediction is the basis of nose cap design [3,4]. There is strong coupling among hypersonic flow field, heat transfer, and deformation of the nose cap.…”

Section: Introductionmentioning

confidence: 99%

Thermo-Structural Behaviour Prediction of the Nose Cap of a Hypersonic Vehicle Based on Multifield Coupling

Sun

Yang

2020

International Journal of Aerospace Engineering

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The analysis of thermo-structural behaviour is crucial to the nose cap of a hypersonic vehicle under aerothermodynamic loads. Considering chemical nonequilibrium of the flow field, heat transfer, and deformation of the structure, a fluid-thermal-structural coupling model of the typical nose cap was established. The coupling relation between the flow field and nose cap was analyzed. The results show that the fluid-thermal-structural model can effectively predict the response of the nose cap under a hypersonic environment. The highest temperature and the peak of maximum principal stress appear at the front of the nose cap at an initial stage. As time goes on, the highest temperature increases gradually and the peak of maximum principal stress decreases after reaching a certain value. The position of the peak of maximum principal stress gradually moves to the inside of the nose cap and eventually stabilizes. With the increase in the Mach number, the highest temperature and the peak of maximum principal stress of the nose cap increase. The fluid-thermal-structural coupling model can provide guidance for the optimal design of the nose cap of a hypersonic vehicle.

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Review on active thermal protection and its heat transfer for airbreathing hypersonic vehicles

Cited by 217 publications

References 153 publications

Influences of lateral jet location and its number on the drag reduction of a blunted body in supersonic flows

Influences of lateral jet location and its number on the drag reduction of a blunted body in supersonic flows

Experiments on Heat Transfer of Supercritical Pressure Kerosene in Mini Tube under Ultra-High Heat Fluxes

Thermo-Structural Behaviour Prediction of the Nose Cap of a Hypersonic Vehicle Based on Multifield Coupling

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