A mathematical model of the thermochemical destruction of carbon fiber-reinforced plastic in the presence of surface roughness and composite ablation is refined based on known theoretical results. It is shown that mass loss through rough surface ambiguously influences the intensity of heat exchange processes in thermal protective material. Results of numerical calculations are compared with known data
Carbon/carbon composites are usually used as a thermal protection material in the nose cap and leadi...
This paper is concerned with modeling of ablation behavior of carbon-carbon composites used in hot s...
A unique numerical method has been developed for solving one-dimensional ablation heat transfer prob...
A mathematical model of the thermochemical destruction of carbon fiber-reinforced plastic in the pre...
The thermochemical destruction of a carbon fiber-reinforced polymer when affected by a high enthalpy...
Roughness of heat-shield materials has been studied in the frame of aerodynamics and the laminar-tur...
Durant la phase de descente d'un véhicule de rentrée atmosphérique, des pressions et flux de chaleur...
Charring ablators remain the premium choice for space exploration missions that involve atmospheric ...
Hypervelocity heat protection, surface heat shielding, and internal temperature rise of Teflon, phen...
Surface ablation and in-depth temperature distribution of the charring material are the key properti...
peer reviewedHigh-fidelity models have been developed in the recent years to predict the response of...
During the atmospheric entry of a blunt body, a bow shock wave is generated on the nose of the vehic...
A numerical analysis of the nonstationary heat and mass exchange in the heat-resistant composite mat...
Re-entry of a spacecraft occurs at hypersonic regime where flow field is extremely complex. High tem...
Ablating thermal protection system (TPS) materials have been used in many reentering spacecraft and ...
Carbon/carbon composites are usually used as a thermal protection material in the nose cap and leadi...
This paper is concerned with modeling of ablation behavior of carbon-carbon composites used in hot s...
A unique numerical method has been developed for solving one-dimensional ablation heat transfer prob...
A mathematical model of the thermochemical destruction of carbon fiber-reinforced plastic in the pre...
The thermochemical destruction of a carbon fiber-reinforced polymer when affected by a high enthalpy...
Roughness of heat-shield materials has been studied in the frame of aerodynamics and the laminar-tur...
Durant la phase de descente d'un véhicule de rentrée atmosphérique, des pressions et flux de chaleur...
Charring ablators remain the premium choice for space exploration missions that involve atmospheric ...
Hypervelocity heat protection, surface heat shielding, and internal temperature rise of Teflon, phen...
Surface ablation and in-depth temperature distribution of the charring material are the key properti...
peer reviewedHigh-fidelity models have been developed in the recent years to predict the response of...
During the atmospheric entry of a blunt body, a bow shock wave is generated on the nose of the vehic...
A numerical analysis of the nonstationary heat and mass exchange in the heat-resistant composite mat...
Re-entry of a spacecraft occurs at hypersonic regime where flow field is extremely complex. High tem...
Ablating thermal protection system (TPS) materials have been used in many reentering spacecraft and ...
Carbon/carbon composites are usually used as a thermal protection material in the nose cap and leadi...
This paper is concerned with modeling of ablation behavior of carbon-carbon composites used in hot s...
A unique numerical method has been developed for solving one-dimensional ablation heat transfer prob...