A fuselage of a fiber-reinforced composite material for an aircraft with a skin and with a multiplicity of circumferential stiffeners and only a small number of longitudinal stiffeners, the skin having a multiplicity of local reinforcements.
대표청구항▼
1. An aircraft fuselage of fibre-reinforced composite material, comprising: a skin including: a multiplicity of local reinforcements; anda backing structure for stiffening the skin, comprising: longitudinal stiffeners, andcircumferential stiffeners,wherein the skin includes a multiplicity of local r
1. An aircraft fuselage of fibre-reinforced composite material, comprising: a skin including: a multiplicity of local reinforcements; anda backing structure for stiffening the skin, comprising: longitudinal stiffeners, andcircumferential stiffeners,wherein the skin includes a multiplicity of local reinforcements,wherein two or more local reinforcements form a row disposed between adjacent circumferential stiffeners,wherein the local reinforcements extend in a longitudinal direction to a greater extent than in a circumferential direction of the fuselage,wherein in a plan view, the local reinforcements each have an oval shape,wherein in cross-section, the local reinforcements each have an elevation in the form of a bulge having a foot section disposed on a circumferential edge thereof,wherein a crown of the bulge extends towards a center region of the fuselage, andwherein the foot section of each adjacent local reinforcement merges flush into one another in a circumferential direction. 2. The fuselage in accordance with claim 1, wherein the multiplicity of local reinforcements are integral with the skin. 3. The fuselage in accordance with claim 1, wherein the multiplicity of local reinforcements are embodied as hollow bodies. 4. The fuselage in accordance with claim 1, wherein the multiplicity of local reinforcements have a foam core. 5. The fuselage in accordance with claim 1, wherein more longitudinal rows of local reinforcements are provided than longitudinal stiffeners. 6. The fuselage in accordance with claim 1, wherein 4, 8 or 12 longitudinal stiffeners are provided around the circumference of the fuselage and are arranged in diametrically opposed pairs. 7. The fuselage in accordance with claim 1, wherein each of the longitudinal stiffeners has two approximately parallel web sections connected by a flange. 8. A skin field of fibre-reinforced composite material having circumferential stiffeners and longitudinal stiffeners for an aircraft fuselage, comprising: a multiplicity of local reinforcements on an inner surface of the skin field, wherein two or more local reinforcements form a row disposed between adjacent circumferential stiffeners,wherein the local reinforcements extend in the longitudinal direction to a greater extent than in the circumferential direction of the fuselage,wherein in a plan view, the local reinforcements each have an oval shape,wherein in cross-section, the local reinforcements each have elevations in the form of a bulge having a foot section disposed on a circumferential edge thereof,wherein a crown of each bulge extends towards a center region of the fuselage, andwherein the foot section of each adjacent local reinforcement merges flush into one another in a circumferential direction. 9. An aircraft fuselage of fibre-reinforced composite material for an aircraft, comprising: a skin including: a multiplicity of local reinforcements; anda backing structure for stiffening the skin, comprising: longitudinal stiffeners, andcircumferential stiffeners,wherein the skin includes a multiplicity of local reinforcements,wherein two or more of the local reinforcements form a column disposed between adjacent longitudinal stiffeners,wherein the local reinforcements extend in a longitudinal direction to a greater extent than in a circumferential direction of the fuselage,wherein in a plan view, the local reinforcements each have an oval shape,wherein in cross-section, the local reinforcements each have elevations in the form of a bulge having a foot section disposed on a circumferential edge thereof,wherein a crown of each bulge extends towards a center region of the fuselage, andwherein the foot section of each adjacent local reinforcement merges flush into one another in the circumferential direction. 10. A skin field of fibre-reinforced composite material having circumferential stiffeners and longitudinal stiffeners for an aircraft fuselage, comprising: a multiplicity of local stiffeners on an inner surface of the skin field, wherein two or more local reinforcements form a column disposed between adjacent longitudinal stiffeners,wherein the local reinforcements extend in a longitudinal direction to a greater extent than in a circumferential direction of the fuselage,wherein in a plan view, the local reinforcements each have an oval shape, wherein in cross-section, the local reinforcements each have an elevation in the form of a bulge having a foot section disposed on a circumferential edge thereof,wherein a crown of each bulge extends towards a center region of the fuselage, andwherein the foot section of each adjacent local reinforcement merges flush into one another in the circumferential direction.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (7)
Gauthie, Laurent; Bernadet, Philippe, Aircraft including stiffener edge junctions and method for producing one such aircraft.
Maison, Serge; Meunier, Serge; Thibout, Cedric; Mouton, Luc; Payen, Herve; Vautey, Philippe; Coiffier-Colas, Carole; Delbez, Joel, Method for making parts in composite material with thermoplastic matrix.
Burpo, Steven J.; Renieri, Michael P.; Segobiano, Nicholas B.; Froeschner, Neal A., Method of making bead-stiffened composite parts and parts made thereby.
Dublinski Alexander C. (Northford CT) Fabian Edward J. (Derby CT) Ramey Philip J. (Milford CT) Toni Darryl M. (North Haven CT), Structural member having a stiffener bead therein and comprising plies of composite material extending for the full leng.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.