STS Forebody Material Selection Method Using Integrated Aerothermodynamic Optimization Approach

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

• Periodical: Advanced Materials Research (Volumes 488-489)
• Pages: 1103-1108
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.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

References

[1] Martin, F., et al., Ceramic Matrix Composites-the Key material for Reentry from Space to Earth, in Basic Research and Technologies for Two-Stage-to-Orbit Vehicles. 2005, Collaborative Research Centres 253, 255 and 259.

[2] Hirschel, E.H., Heat Loads as Key Problems of Hypersonic Flight. Zeitschrift fur Flugwissenschaften and Weltraumforschung (ZFW), 1992. 16(6): pp.349-356.

[3] Perrier, P.C. and E.H. Hirschel, Vehicle Configuration and Aerothermodynamic Challenges, in AGARD. 1997. p. C2-1 - C2-16.

[4] Fay, J.A. and F.R. Riddell, Theory of Stagnation Point Heat Transfer in Dissociated Air. Journal of Aeronautical Sciences, 1958. 25(2): pp.73-85.

DOI: 10.2514/8.7517

[5] Hirschel, E.H. Aerothermodynamics of Radiation Cooled Surfaces. in Aerothermodynamics and Propulsion Integration for Hypersonic Vehicles (AGARD-R-813). 1996. VKI, Belgium: AGARD (NATO).

[6] Hu, D., A. Sarosh, and D.Y. Feng, An Improved Particle Swarm Optimizer for Parameteric Optimization of Flexible Satellite Controller. Journal of Applied Mathematics and Computations, 2011: p.21.

DOI: 10.1016/j.amc.2011.03.055

[7] Sarosh, A., D. Yun-Feng, and M. Adnan, A Configurational Aerothermodynamics Methodology for Derivation of Baseline Configuration on Elliptical Cone-Wedge Integrated Waverider, in International Conference on Aerospace Engineering and Information Technology (AEIT 2011). 2011, International Industrial Electronics Publishers, Hong Kong, ISBN 978-988-19116-3-6: Beijing, China.