FIELD: aviation equipment.
SUBSTANCE: group of inventions relates mainly to the heat-proof front edges of the wings of aerospace vehicles. Leading edge structure includes a plurality of removable modules attached, for example, to the front spar of the wing. Each removable module is made in the form of a hollow box structure (HBS) having at least one shelf part located along one end of the HBS. There are many first and second fasteners for installing the HBS on the specified front spar. Plurality of first fasteners are used to fasten one end of the HBS to the first end portion of the front spar. Many second fasteners containing pointed pins with nuts serve for fastening the other end of the HBS, located opposite the said shelf part, to the second (opposite to the first) end part of the front spar.
EFFECT: technical result of the group of inventions is aimed at improving the manufacturability and efficiency of the modular principle in the repair, replacement and operation of the front edges of the wings of super- and hypersonic aerospace vehicles.
20 cl, 20 dwg
