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|Title: ||Transient Aero-Thermal Mapping of Passive Thermal Protection System for Nose-Cap of Reusable Hypersonic Vehicle|
|Authors: ||MAHULIKAR, SP|
|Keywords: ||parameter influence|
|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.|
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