Aerodynamic instability of an inflatable aeroshell in suborbital re-entry

Takahashi, Yusuke; Ohashi, Tatsushi; Oshima, Nobuyuki; Nagata, Yasunori; Yamada, Kazuhiko

doi:10.1063/5.0009607

Cited by 8 publications

(1 citation statement)

References 35 publications

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“…Inflatable heat shields use flexible air-tight chambers that are folded before inflation, then deploy and rigidise under internal gas pressure. Flexible thermal protection layers based on commercial materials are wrapped onto the chambers to maintain an acceptable structural temperature [11,12,13,14,15,16,17,18,19,20,21,22,23]. The foldable mechanisms utilise umbrella-like designs where a skirt made of flexible thermal protection materials is bounded onto rigid deployable ribs.…”

Section: Introductionmentioning

confidence: 99%

Deployable self-regulating centrifugally-stiffened decelerator (DESCENT): Design scalability and low altitude drop test

Roberts

et al. 2021

Aerospace Science and Technology

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Section: Introductionmentioning

confidence: 99%

Deployable self-regulating centrifugally-stiffened decelerator (DESCENT): Design scalability and low altitude drop test

Roberts

et al. 2021

Aerospace Science and Technology

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Coupled surface-volume pyrolysis effects of carbon-phenolic resin composites under hyperthermal non-equilibrium flows

Cui

Zhao

et al. 2022

Physics of Fluids

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Thermal protection system (TPS) is essential for the safe and reliable flying of any high-speed aircraft. Carbon fiber-reinforced phenolic resin (PR) composite is one of the most important matrix candidates for ablative materials, the microscopic understanding of the pyrolysis process of PR, however, still remains poor. The usual numerical approach is based on volumetric pyrolysis while neglecting the influence of external hyperthermal surrounding. A surface-volume coupled reactive molecular dynamics (RMD) model is established in this work to simulate complicated heat /mechanics /chemistry multi-physical field coupled pyrolysis problem. The pyrolysis process of carbon fiber-PR composite is investigated in the presence of vacuum and hyperthermal gas impacts, and compared with the volumetric pyrolysis simulation only. The consideration of the surface-volume coupling reveals many unique features beyond the volumetric pyrolysis, which include the generation of different pyrolysis products and the dependence of the effective mass diffusivity of pyrolysis gases on impinging gases in the presence of hyperthermal non-equilibrium environment. With detailed revelation of the evolutions of PR solid phase and pyrolysis gaseous products, the work is of great help in improving the microscopic pyrolysis mechanisms, especially the 'blowing gas effect', a key phenomenon for improved understanding of the complicated hypersonic boundary layer flow.

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Numerical simulation of thermochemical non-equilibrium flow-field characteristics around a hypersonic atmospheric reentry vehicle

Qiu

Bowen

et al. 2022

Physics of Fluids

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A multi-physics thermochemical nonequilibrium model is established to study the flow characteristics of the plasma sheath around an atmospheric reentry demonstrator (ARD). This model includes the tight coupling of Navier-Stokes equations, 54 chemical reactions of air, and a four-temperature model. The processes of dissociation, ionization, and the internal energy exchanges of air components were successfully simulated during the aerodynamic heating of the reentry vehicle. The distributions of plasma sheath temperature, the molar fraction of air species, stagnation pressure, surface pressure, and electron number density around the reentry vehicle were obtained at different flight altitudes. Additionally, to validate the numerical model developed in this study, the flow characteristics of the Radio Attenuation Measurement-C-II (RAM-C-II) vehicle are also simulated and then compared with corresponding experimental data. They show good consistency in general. It is found that when the vehicle is at a high flight altitude, there is a strong thermochemical non-equilibrium phenomenon around the vehicle. However, the plasma sheath tends to be in local thermal equilibrium at a low flight altitude. The distance from the shock layer to the stagnation point decreases with a decrease in reentry altitude from 90 to 65 km, but increases with a decrease from 65 to 40 km. The electron number density in the shock layer is maximum. The distribution of the electron number density in the wake region differs significantly at different flight altitudes.

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Aerodynamic instability of an inflatable aeroshell in suborbital re-entry

Abstract: Recurrence analysis and time extrapolation of a confined turbulent jet using modal decomposition Physics of Fluids 32, 075115 (2020);

Cited by 8 publications

References 35 publications

Deployable self-regulating centrifugally-stiffened decelerator (DESCENT): Design scalability and low altitude drop test

Deployable self-regulating centrifugally-stiffened decelerator (DESCENT): Design scalability and low altitude drop test

Coupled surface-volume pyrolysis effects of carbon-phenolic resin composites under hyperthermal non-equilibrium flows

Numerical simulation of thermochemical non-equilibrium flow-field characteristics around a hypersonic atmospheric reentry vehicle

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