Concept of an Active Thermal Protection System with a Three-Layer Design–Force Scheme and a Discrete Filler for a Hypersonic Aircraft

The possibility of active thermal protection for the most heat-loaded areas of the supersonic aircraft surface, in particular, the design–force scheme of the wing, i.e., is a three-layer shell with a filler consisting of cone-shaped cells, is investigated by numerical simulation. The three-dimensional problem of a hypersonic flow around the leading edge of the wing is solved. The obtained results are used as boundary conditions for solving the problem of an internal refrigerant flow and the conjugate heat exchange inside the wing structure. The active thermal protection system is found to be integrated into the design–force scheme of the wing, which is based on the use of three-layer shells with a filler consisting of cone-shaped cells.