Shell-type structure for light aircraft

Claim 2

An aircraft structural element for connection to other structural elements comprising a first skin made of resin-preimpregnated reinforcing fabric, a second skin made of resin-preimpregnated reinforcing fabric, and a cellular core, said first skin, said second skin and said cellular core cured together in a mold in the ultimate shape of the structural element, said cellular core interrupted at zones destined to form junctions with other elements, the skins of the element at each such zone bonded together to form zones of engagement for the connecting lugs or flanges of other elements.

Claim 3

An aircraft structural part comprising structural elements including an upper element, a lower element, a front spar, and a rear spar, each of said structural elements including a first skin made of resin-preimpregnated reinforcing fabric, a Second skin made of resin-preimpregnated reinforcing fabric, and a cellular core, said first skin, said second skin, and said cellular core cured together in a mold in the ultimate shape of said structural element, each said skin having an overlength extending beyond the periphery of said cellular core, said overlengths being bonded together to constitute connecting lugs or flanges adapted to facilitate subsequent connection by bonding with said structural elements adjacent thereto, said overlengths of said upper and lower elements extending relatively forwardly and rearwardly of said upper and lower elements, and said overlengths of said spars extending relatively above and below said spars, said overlengths extending forwardly of said upper and lower elements bonded to form a T-shaped joint, said overlengths extending rearward of said upper and lower elements bonded respectively to said overlengths of said rear spar extending above and below said rear spar, said overlengths extending above and below said front spar bonded respectively to upper and lower zones of engagement formed respectively in said upper and lower elements by interrupting said cores in said upper and lower elements at their forward portions and bonding said first and second skins to each other at such interruption in said upper and lower elements.

Claim 4

An aircraft structural part comprising structural elements including an upper element, a lower element, a front spar, and a rear spar, each of said structural elements including a first skin made of resin-preimpregnated reinforcing fabric, a Second skin made of resin-preimpregnated reinforcing fabric, and a cellular core, said first skin, said second skin, and said cellular core cured together in a mold in the ultimate shape of said structural element, each said skin having an overlength extending beyond the periphery of said cellular core, said overlengths being bonded together to constitute connecting lugs or flanges adapted to facilitate subsequent connection by bonding with said structural elements adjacent thereto, said overlengths of said upper and lower elements extending relatively forwardly and rearwardly of said upper and lower elements, and said overlengths of said spars extending relatively above and below said spars, said overlengths extending forwardly of said upper and lower elements bonded to form a T-shaped joint, said overlengths extending rearward of said upper and lower elements bonded respectively to said overlengths of said rear spar extending above and below said rear spar, said overlengths extending above and below said front spar bonded respectively to upper and lower zones of engagement formed respectively in said upper and lower elements by interrupting said cores in said upper and lower elements at their forward portions and bonding said first and second skins to each other at such interruption in said upper and lower elements.

Claim 5

A structural part according to claim 2, characterized in that a nose-piece edging of polyurethane foam is bonded to said T-shaped joint and outer surfaces of adjacent overlengths in a position astride said T-shaped joint.