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 |
| Price | US$ 28,- |
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