2024-03-29T12:08:32Zhttps://eprints.lib.hokudai.ac.jp/dspace-oai/requestoai:eprints.lib.hokudai.ac.jp:2115/796472022-11-17T02:08:08Zhdl_2115_20045hdl_2115_139Aerodynamic heating of inflatable aeroshell in orbital reentryTakahashi, YusukeYamada, KazuhikoInflatable reentry vehicleAerodynamic heatingHypersonicDeformationCoupled analysis538The aerodynamic heating of an inflatable reentry vehicle, which is one of the innovative reentry technologies, was numerically investigated using a tightly coupled approach involving computational fluid dynamics and structure analysis. The fundamentals of a high-enthalpy flow around the inflatable reentry vehicle were clarified. It was found that the flow fields in the shock layer formed in front of the vehicle were strongly in a chemical nonequilibrium state owing to its low-ballistic coefficient trajectory. The heat flux tendencies on the surface of the vehicle were comprehensively investigated for various effects of the vehicle shape, surface catalysis, and turbulence via a parametric study of these parameters. In addition, based on the present results of the computational approach, a new heating-rate method was developed to calculate the heat flux of the nonequilibrium flow. It was demonstrated that the method could well-reproduce the heat flux on the inflatable reentry vehicle.ElsevierJournal Articleapplication/pdfhttp://hdl.handle.net/2115/79647https://eprints.lib.hokudai.ac.jp/dspace/bitstream/2115/79647/1/paper_titans_heatflux.pdf0094-5765Acta astronautica1524374482018-11enginfo:doi/10.1016/j.actaastro.2018.08.003© 2018. This manuscript version is made available under the CC-BY-NC-ND 4.0 license http://creativecommons.org/licenses/by-nc-nd/4.0/author