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Transient Aero-Thermal Mapping of Passive Thermal Protection System for Nose-Cap of Reusable Hypersonic Vehicle

DSpace at IIT Bombay

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Title Transient Aero-Thermal Mapping of Passive Thermal Protection System for Nose-Cap of Reusable Hypersonic Vehicle
 
Creator MAHULIKAR, SP
KHURANA, S
DUNGARWAL, R
SHEVAKARI, SG
SUBRAMANIAN, J
GUJARATHI, AV
 
Subject parameter influence
x-34
flowfield
ablation
design
aerothermodynamics
missile
 
Description The temperature field history of passive Thermal Protection System (TPS) material at the nose-cap (forward stagnation region) of a Reusable Hypersonic Vehicle (RHV) is generated. The 3-D unsteady heat transfer model couples conduction in the solid with external convection and radiation that are modeled as time-varying boundary conditions on the surface. Results are presented for the following two cases: (1) nose-cap comprised of ablative TPS material only (SIRCA/PICA), and (2) nose-cap comprised of a combination of ablative TPS material with moderate thermal conductivity and insulative TPS material. Comparison of the temperature fields of SIRCA and PICA [Case (1)] indicates lowering of the peak stagnation region temperatures for PICA, due to its higher thermal conductivity. Also, the use of PICA and insulative TPS [Case (2)] for the nose-cap has higher potential for weight reduction than the use of ablative TPS alone.
 
Publisher AMER ASTRONAUTICAL SOC
 
Date 2011-07-13T12:32:09Z
2011-12-26T12:47:52Z
2011-12-27T05:41:12Z
2011-07-13T12:32:09Z
2011-12-26T12:47:52Z
2011-12-27T05:41:12Z
2008
 
Type Article
 
Identifier JOURNAL OF THE ASTRONAUTICAL SCIENCES, 56(4), 593-619
0021-9142
http://dspace.library.iitb.ac.in/xmlui/handle/10054/3674
http://hdl.handle.net/10054/3674
 
Language en