The thermal protection system of sharp nose-cones is an important subject in the investigation of reusable spacecraft. Transpiration cooling, with an ability to effectively reduce the temperature of the nose-cone, has been widely recognized as a promising thermal protection approach. However, the cooling effect at the stagnation point remains poor due to the extremely high heat flux and pressure there. The nose-cone with forward-facing cavity is a drag and heat reduction structure specifically designed for the stagnation region. It can reduce the heat flux and pressure there with the shutting effect of the sharp lip. Therefore, a new combined cooling structure is proposed in this paper: transpiration cooling with forward-facing cavity. It utilizes the cooling enhancement effect of the forward-facing cavity to solve the problem of low cooling efficiency at the stagnation region. Using a wedge-shaped nose cone as the physical model, the cooling performance of three structures, i.e., transpiration cooling, forward-facing cavity and transpiration cooling with the cavity, is studied and compared. The simulation results indicate that, using the new combined cooling structure, the maximum temperature of the nose-cone can be reduced by 16.8% compared with that of the traditional transpiration cooling, and the average circular surface temperature can drop by 64% compared with that on the pure nose-cone, confirming the feasibility and high efficiency of the new cooling structure.
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