An orthotropic material model is implemented in a three-dimensional material response code, and numerically studied for charring ablative material. Model comparison is performed using an iso-Q sample geometry. The comparison is presented using pyrolysis gas streamlines and time series of temperature at selected virtual thermocouples. Results show that orthotropic permeability affects both pyrolysis gas flow and thermal response, but orthotropic thermal conductivity essentially changes the thermal performance of the material. The effect of orthotropic properties may have practical use such that the material performance can be manipulated by altering the angle of orthotropic orientation
The thermo-physical parameters of the pyrolysis layer in charring material play a fundamental role i...
Re-entry of a spacecraft occurs at hypersonic regime where flow field is extremely complex. High tem...
Charring thermal protection systems have been used to protect hypersonic vehicles from high heat ...
An orthotropic material model is implemented in a three-dimensional material response code, and nume...
Using an ablative thermal/material response code, the importance of three-dimensionality for modelin...
During hypersonic atmospheric entry, spacecraft are exposed to enormous aerodynamic heat. To prevent...
During hypersonic atmospheric entry, spacecraft are exposed to enormous aerodynamic heat. To prevent...
Sample geometry is very influential in small charring ablative articles where 1D assumption might no...
Charring ablators remain the premium choice for space exploration missions that involve atmospheric ...
When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and frictio...
When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and frictio...
Charring thermal protection systems have been used to protect hypersonic vehicles from high heat loa...
This study demonstrates that coupling of a material thermal response code and a flow solver with non...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76855/1/AIAA-2008-3805-224.pd
Re-entry of a spacecraft occurs at hypersonic regime where flow field is extremely complex. High tem...
The thermo-physical parameters of the pyrolysis layer in charring material play a fundamental role i...
Re-entry of a spacecraft occurs at hypersonic regime where flow field is extremely complex. High tem...
Charring thermal protection systems have been used to protect hypersonic vehicles from high heat ...
An orthotropic material model is implemented in a three-dimensional material response code, and nume...
Using an ablative thermal/material response code, the importance of three-dimensionality for modelin...
During hypersonic atmospheric entry, spacecraft are exposed to enormous aerodynamic heat. To prevent...
During hypersonic atmospheric entry, spacecraft are exposed to enormous aerodynamic heat. To prevent...
Sample geometry is very influential in small charring ablative articles where 1D assumption might no...
Charring ablators remain the premium choice for space exploration missions that involve atmospheric ...
When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and frictio...
When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and frictio...
Charring thermal protection systems have been used to protect hypersonic vehicles from high heat loa...
This study demonstrates that coupling of a material thermal response code and a flow solver with non...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76855/1/AIAA-2008-3805-224.pd
Re-entry of a spacecraft occurs at hypersonic regime where flow field is extremely complex. High tem...
The thermo-physical parameters of the pyrolysis layer in charring material play a fundamental role i...
Re-entry of a spacecraft occurs at hypersonic regime where flow field is extremely complex. High tem...
Charring thermal protection systems have been used to protect hypersonic vehicles from high heat ...