FIELD: heat insulation; aviation.
SUBSTANCE: invention relates to heat protection of predominantly hypersonic aircraft. Method consists in breaking the heat-shielding coating onto tiles and fixing them on the power skeleton of the aerodynamic surface (AS). Tiles are adjacent to each other in rows of one tile wide and the height from the leading edge to the side chord AS. Rows are perpendicular to either the bead chord or the leading edge (at an angle α). Rectangular tiles in each row are closed with trapezoidal tiles. Tile heights are multiples of the size c=a⋅tgα, where c – difference between the larger and smaller parallel sides of the trapezoidal tile. Smaller of these parties perform equal p, p+c or p+2⋅c, where p – the remainder of the division of the whole height of the row of tiles by c. Tiles in the row are arranged with a displacement to the tiles of the neighboring row by c or c/2.
EFFECT: technical result consists in simplifying the assembly technology and reducing the cost of producing tiles by reducing their number and the number of their sizes.
1 cl, 8 dwg
