Comparison of Strategies for Coupled Flow-Thermal Analysis of Thermal Protection System at Hypersonic Flight Condition

Wang, Ruixing; Wang, Zhaowei; Zheng, Hongwei; Song, Hongwei

doi:10.1007/s42405-019-00217-x

Cited by 10 publications

(1 citation statement)

References 33 publications

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“…The flexible inflatable reentry vehicle is expected to be widely used as a new type of reentry vehicle due to the advantage of its low ballistic coefficient. During the whole entry, descent, and landing (EDL) process, compared with the traditional reentry vehicle, the flexible reentry vehicle can decelerate at a higher altitude, which effectively reduces the surface heat flux of the vehicle, decreases the plasma density of the shock layer, and increases the communication possibility between ground and aerospace [1][2][3][4][5][6][7][8][9].…”

Section: Introductionmentioning

confidence: 99%

Multiphysics Mathematical Modeling and Flow Field Analysis of an Inflatable Membrane Aeroshell in Suborbital Reentry

Qiu

et al. 2022

Mathematics

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In the present study, a multiphysics mathematical model for reproducing the flow field characteristics of an inflatable aeroshell was developed to study the aerodynamic properties of the flow around a membrane reentry vehicle. Firstly, the configuration and flight sequence of a membrane reentry vehicle used in the experiment were introduced. Secondly, mathematical equations of multiphysics fields, such as the Navier–Stokes equations, the heat conduction equation, and the membrane deformation equation, were introduced and numerically solved. The variation characteristics of the flow properties during the aerodynamic heating of a membrane vehicle were studied and discussed in detail under the conditions of different flight altitudes. The results showed that for the membrane vehicle, the high-temperature flow field at the front of its capsule was in a state of thermal non-equilibrium with the decrease of flight altitude and its membrane deformation degree was proportional to the pressure. The translational temperature and electron number density of the plasma flow around the aeroshell remained at a relatively low level for the membrane vehicle so that the blackout phenomenon scarcely occurred during its atmospheric reentry.

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Section: Introductionmentioning

confidence: 99%

Multiphysics Mathematical Modeling and Flow Field Analysis of an Inflatable Membrane Aeroshell in Suborbital Reentry

Qiu

et al. 2022

Mathematics

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Efficient Aerodynamic Analysis of Air-Breathing Hypersonic Vehicle using Local Surface Inclination Method based on Unstructured Meshes

Lee

Kim

et al. 2021

Int. J. Aeronaut. Space Sci.

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Three-dimensional flow structures and heat transfer characteristics of compressible flow over a cylindrical cavity

Wang

et al. 2022

Aerospace Science and Technology

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Comparison of Strategies for Coupled Flow-Thermal Analysis of Thermal Protection System at Hypersonic Flight Condition

Cited by 10 publications

References 33 publications

Multiphysics Mathematical Modeling and Flow Field Analysis of an Inflatable Membrane Aeroshell in Suborbital Reentry

Multiphysics Mathematical Modeling and Flow Field Analysis of an Inflatable Membrane Aeroshell in Suborbital Reentry

Efficient Aerodynamic Analysis of Air-Breathing Hypersonic Vehicle using Local Surface Inclination Method based on Unstructured Meshes

Three-dimensional flow structures and heat transfer characteristics of compressible flow over a cylindrical cavity

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