A heat shield called the thermal protection system (TPS) is an important structure in
hypersonic vehicles as it prevents hot air from entering vehicles and potential impacts from …

The analysis, design, and development of planetary entry technologies rely heavily on
computational modeling due to limited ground and flight test data, which simulate the …

Abstract The Thermal Protection System (TPS) provides spacecrafts entering the
atmosphere with the thermal insulation from the aerothermodynamic heating. The design of …

The radiative heat flux imparted on the after-body of vehicles entering the Martian
atmosphere is simulated. The radiation is dominated by CO 2 bands emitting in the midwave …

Simulations of atmospheric entry of spacecraft and satellites require accurate knowledge of
thermo-physical properties such as heat capacity in a wide temperature range. However, the …

Accurate prediction of the gas-surface interaction during spacecraft reentry remains a
challenging problem for thermal protection system design. Attempts to model the surface …

This paper presents measurements and simulations of CO 4th Positive equilibrium radiation
obtained in the NASA Ames Research Center's Electric Arc Shock Tube (EAST) facility. The …

A multicomponent kinetic mechanism has been developed for the pyrolysis at low heating
rate of carbon/phenolic thermal protection material and a wood species. An experimental …

In this study, a probabilistic method was proposed for an aircraft's thermal protective layers.
The uncertainties of material properties, geometric dimensions, and incoming flow …

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率设计和可性sÍ 方法& 采用有限元方法计算系统热响应! 通过X 与数值模型对比X …