초록 ▼

The present invention provides a casing structure of low weight provided with a laminate stringer of high rigidity. The stringer has the form of a laminate with a plurality of metallic layers and at least one synthetic fiber layer, which is produced at least partially from Zylon fibers, provided bet

The present invention provides a casing structure of low weight provided with a laminate stringer of high rigidity. The stringer has the form of a laminate with a plurality of metallic layers and at least one synthetic fiber layer, which is produced at least partially from Zylon fibers, provided between two metallic layers.

대표청구항 ▼

1. Fuselage structure, in particular of an aircraft or a spacecraft, wherein a plurality of stringers is provided between a first and second frame on which frames an outer skin is fitted; wherein each of said plurality of stringers is adhesively bonded both to the first and second frame and to the o

1. Fuselage structure, in particular of an aircraft or a spacecraft, wherein a plurality of stringers is provided between a first and second frame on which frames an outer skin is fitted; wherein each of said plurality of stringers is adhesively bonded both to the first and second frame and to the outer skin at respective adhesive surfaces; wherein each of said stringers comprises a plurality of metallic layers and a respective synthetic fibre layer between each two metallic layers, which synthetic fibre layer is produced at least partially from poly(p-phenylene-2,6-benzobisoxazole) fibres. 2. Fuselage structure of claim 1 wherein said stringers have a Z shape including a first straight side portion, a middle region and a second straight side portion, which merge with one another by means of arcs of a circle; and wherein the respective second straight side portion is adhesively bonded to the outer skin. 3. Fuselage structure of claim 2, wherein said second straight side portion is shorter than said first straight side portion. 4. Fuselage structure of claim 1, wherein said stringers have a modulus of elasticity of between 90 and 100 GPa. 5. Fuselage structure of claim 1, wherein each of the plurality of metallic layers is produced from aluminum or an aluminum compound or an aluminum alloy. 6. Fuselage structure of claim 1, wherein the outer skin is produced from a laminate-like material combination that comprises a plurality of layers, which layers alternately consist of aluminum and a glass fibre laminate and are adhesively bonded.