The structural design loop for scramjet combustor has been established, and multiple iterations of coupled structural analysis have been performed to study the effect of thermal barrier coating and stiffeners on temperature and deformation experienced by scramjet walls. The results of the thermal-structural analysis clearly show reduction in metal skin temperature by using thermal barrier coating which is in confirmation with works by Clarke [14] and Cao [15]. This work also demonstrates the effectiveness of stiffener in reducing total deformation of scramjet; this is also in agreement with work by Killackey [16], Zuchowski [17] and Antonin et al. [18]. Thus, the agreement of results of the performed thermal-structural analysis with literature establishes the capability of coupled thermal-structural analysis methodology outlined in this work. Other important aspects like selection of suitable material and thermal barrier coating for scramjet application have also been discussed. The same structural design methodology loop can also be extended for the thermal-structural design of the entire hypersonic vehicle.
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