Abstract
Scramjets are essential for thrust generation in hypersonic air breathing cruise vehicles. One of the critical challenges in developing scramjet is their complex structural design due to intense thermal-structural loads experienced during hypersonic flight. Finite element based coupled thermal-structural analysis has been carried out to calculate temperature and strain field for designing a semi-monocoque scramjet structure. Multiple iterations of thermal-structural analysis have been carried out to estimate design parameters namely wall thickness, coating thickness, spacing and cross section of stiffeners to contain temperature, deformation and stress as well as minimize weight. It has been found that skin thickness of 1mm, coating thickness of 500µm, stiffener spacing of 3mm is most optimum for a scramjet flying at speed of Mach 7 at 30 km altitude with isolator air entry speed of Mach 2.2.
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Purwar, A., Mahapatra, D.R., Thakor, N., Priyamvada, K.S., Mukherjee, R. (2017). A Methodology for Coupled Thermal-Structural Analysis and Structural Design of Scramjet Combustor. In: Ben-Dor, G., Sadot, O., Igra, O. (eds) 30th International Symposium on Shock Waves 1. Springer, Cham. https://doi.org/10.1007/978-3-319-46213-4_40
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DOI: https://doi.org/10.1007/978-3-319-46213-4_40
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