Paper Title:

STS Forebody Material Selection Method Using Integrated Aerothermodynamic Optimization Approach

Periodical Advanced Materials Research (Volumes 488 - 489)
Main Theme Key Engineering Materials II
Edited by Wu Fan
Pages 1103-1108
DOI 10.4028/www.scientific.net/AMR.488-489.1103
Citation Ali Sarosh et al., 2012, Advanced Materials Research, 488-489, 1103
Online since March, 2012
Authors Ali Sarosh, Dong Yun-Feng, Dimitar Kamarinchev
Keywords Carbon-Silicon Carbide, Integrated Aerothermodynamics, Optimization, SHWAMIDOF-FI Tool, STS Forebody, TIPSO Algorithm
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Abstract

Ceramic matrix composites have been recommended for space applications. Accordingly, in this paper, a material selection method for the forebody of a space transportation system is demonstrated. The methodology is based on mass-model coupled aerothermodynamic design of a highly-integrated forebody-inlet system that uses the multidisciplinary optimization capability of the TIPSO (Two-steps Improved PSO) algorithm. The design optimization and hence material parameters are evolved using the newly developed SHWAMIDOF-FI tool. This paper focuses on validating the selection of carbon composite material by optimizing the configuration parameters for integrating a cone-derived forebody into planar wedge surfaces and an inlet-isolator assembly, so as to form a mixed internal-external compression system. Surface temperature, thermal conductivity, tensile strength and emissivity are used as primary parameters for selection of a forebody material. The optimization results validate that a carbon fibre reinforced carbon and silicon carbide (C/C-SiC) dual matrix composite is best suited for the application