Concept of active thermal protection system for three-layer structural-power scheme of hypersonic aircraft with discrete filler

The possibility of active thermal protection of the most heat-stressed areas of the surface of a supersonic aircraft, in particular the structural-power scheme of a wing, which is a three-layer shell with a filler with cone-shaped cells, has been studied by the numerical simulation method. The three-dimensional problem of hypersonic flow around the leading edge of the wing is solved. The obtained results were used as boundary conditions for solving the problem of internal coolant flow and conjugate heat transfer inside the wing structure. It has been established that the system of active thermal protection can be integrated into the structural-power scheme of the wing, based on the use of three-layer shells with a filler with cone-shaped cells.