Using an ablative thermal/material response code, the importance of three-dimensionality for modeling ablative test-article is addressed. In particular, the simulation of the pyrolysis gas flow inside a porous material is presented, using two different geometries. The effects of allowing the gas to flow out of the side wall are especially highlighted. Results show that the flow inside the test-article is complex, and that the 0D or 1D assumption made in most Material Response (MR) codes might not be valid for certain geometries
This study demonstrates that coupling of a material thermal response code and a flow solver with non...
The present thesis provides a description of historical and current modeling methods with recent dis...
The present thesis provides a description of historical and current modeling methods with recent dis...
An orthotropic material model is implemented in a three-dimensional material response code, and nume...
Sample geometry is very influential in small charring ablative articles where 1D assumption might no...
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...
Charring ablators remain the premium choice for space exploration missions that involve atmospheric ...
Re-entry of a spacecraft occurs at the hypersonic regime where the flow field is extremely complex: ...
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...
Re-entry of a spacecraft occurs at hypersonic regime where flow field is extremely complex. High tem...
When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and frictio...
An orthotropic material model is implemented in a three-dimensional material response code, and nume...
When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and frictio...
This study demonstrates that coupling of a material thermal response code and a flow solver with non...
The present thesis provides a description of historical and current modeling methods with recent dis...
The present thesis provides a description of historical and current modeling methods with recent dis...
An orthotropic material model is implemented in a three-dimensional material response code, and nume...
Sample geometry is very influential in small charring ablative articles where 1D assumption might no...
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...
Charring ablators remain the premium choice for space exploration missions that involve atmospheric ...
Re-entry of a spacecraft occurs at the hypersonic regime where the flow field is extremely complex: ...
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...
Re-entry of a spacecraft occurs at hypersonic regime where flow field is extremely complex. High tem...
When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and frictio...
An orthotropic material model is implemented in a three-dimensional material response code, and nume...
When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and frictio...
This study demonstrates that coupling of a material thermal response code and a flow solver with non...
The present thesis provides a description of historical and current modeling methods with recent dis...
The present thesis provides a description of historical and current modeling methods with recent dis...