DSpace
 

DSpace at IIT Bombay >
IITB Publications >
Article >

Please use this identifier to cite or link to this item: http://dspace.library.iitb.ac.in/jspui/handle/10054/3674

Title: Transient Aero-Thermal Mapping of Passive Thermal Protection System for Nose-Cap of Reusable Hypersonic Vehicle
Authors: MAHULIKAR, SP
KHURANA, S
DUNGARWAL, R
SHEVAKARI, SG
SUBRAMANIAN, J
GUJARATHI, AV
Keywords: parameter influence
x-34
flowfield
ablation
design
aerothermodynamics
missile
Issue Date: 2008
Publisher: AMER ASTRONAUTICAL SOC
Citation: JOURNAL OF THE ASTRONAUTICAL SCIENCES, 56(4), 593-619
Abstract: 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.
URI: http://dspace.library.iitb.ac.in/xmlui/handle/10054/3674
http://hdl.handle.net/10054/3674
ISSN: 0021-9142
Appears in Collections:Article

Files in This Item:

There are no files associated with this item.

View Statistics

Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.

 

Valid XHTML 1.0! DSpace Software Copyright © 2002-2010  Duraspace - Feedback