An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. T
An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.
대표청구항▼
1. An aircraft fuselage frame comprising: a central frame element configured to be located within a perimeter of a fuselage, wherein the central frame element has an outer surface adjacent an outer skin of the fuselage and an inner surface extending entirely around an inner perimeter of the central
1. An aircraft fuselage frame comprising: a central frame element configured to be located within a perimeter of a fuselage, wherein the central frame element has an outer surface adjacent an outer skin of the fuselage and an inner surface extending entirely around an inner perimeter of the central frame element, and a continuous web connecting the outer surface to the inner surface and extending the entire circumferences of the outer and inner surfaces;a continuous area within the fuselage and uninterrupted by the aircraft fuselage frame, wherein the perimeter of the continuous area is defined by an entirety of the inner surface of the central frame, andlateral extensions projecting from opposite sides of the fuselage, wherein each of the lateral extensions is a portion of a respective longitudinal structure of a lifting surface extending from the fuselage,wherein upper surfaces of each of the lateral extensions are aligned with an upper region of the central frame element such that a line projected from either of the upper surfaces into the central frame element passes through the continuous web and does not intersect the inner surface of the central frame element; andwherein the central element and the lateral extensions are an integrated, single-piece component. 2. The aircraft fuselage frame according to claim 1, wherein the lateral extensions each include a lower edge which is aligned with and parallel to a straight portion of the inner surface of the upper position of the central frame element. 3. The aircraft fuselage frame according to claim 1 wherein the lateral extensions each include a connection to an extension arm. 4. The aircraft fuselage frame according to claim 1, wherein the central frame element and the lateral extensions are in a common cross section of the fuselage, wherein the cross section is in a plane perpendicular to an axis of the fuselage. 5. The aircraft fuselage frame according to claim 1, wherein a lower edge of the upper region of the central frame element is aligned along a line with a lower edge of each of the lateral extensions. 6. A fuselage comprising: fuselage frames each including a central frame element within a perimeter of the fuselage, wherein the central frame element in each of the fuselage frames is a beam including an outer surface adjacent an outer skin of the fuselage and an inner surface extending entirely around an inner perimeter of the central element;each of the central frame elements defines a respective continuous area uninterrupted by the respective fuselage frame, wherein the perimeter of the continuous area is defined by the inner surface of the beam of the central frame, andeach of the fuselage frames includes lateral extensions projecting outward from the fuselage and from the central frame element for the fuselage frame, wherein the lateral extensions are each a portion of a longitudinal structure of a respective lifting structure projecting from the fuselage;wherein each of the fuselage frames, including the central frame element and the lateral extensions, are an integrated, single-piece component;wherein in each of the fuselage frames, a line projected entirely through the lateral extensions extends through an upper region of the central frame element and does not intersect the inner surface of the central frame element; andwherein the outer skin of the fuselage extends continuously over the outer surfaces of the fuselage frames. 7. The fuselage according to claim 6, wherein the lateral extensions of each of the fuselage frames are a portion of a longitudinal structure of a torsion box for each of the respective lifting structures, wherein each of the lifting structures is configured to support at least one aircraft engine. 8. The fuselage according to claim 7, wherein the lateral extensions for each of the fuselage frames extend to the at least one aircraft engine. 9. The fuselage according to claim 7, wherein the lateral extensions for each of the fuselage frames include connections to an extension arm extending to the at least one aircraft engine. 10. The fuselage according to claim 9, further comprising pylon skins each covering the lateral extensions and the extension arms on a respective side of the fuselage. 11. An aircraft comprising the fuselage of claim 6. 12. The aircraft according to claim 11, wherein the outer skin of the fuselage extends in a longitudinal direction of the fuselage. 13. An aircraft comprising: a fuselage including a sequence of frames arranged along a longitudinal axis of the fuselage and each of the frames is in a respective plane substantially perpendicular to the longitudinal axis;each of the frames is an integral, single piece component which includes a central frame element and lateral extensions extending outward from opposite sides of the fuselage, wherein (i) the central frame element includes an outer surface adjacent a skin of the fuselage, an inner surface, and a web extending between the outer and inner surfaces, (ii) the inner surface defines a perimeter of an area within the central element and the area is uninterrupted by the frame, (iii) the web is continuous along the entirety of the outer and inner surfaces, and (iv) a line projected through an entirety of either of the lateral extensions extends through the web of the central frame element and does not intersect the inner surface of the central frame element; andaerodynamic lifting structures extending from opposite sides of the fuselage, wherein the lifting structures are arranged symmetrically with respect to the longitudinal axis, wherein the aerodynamic lifting structures each include at least one of the lateral extensions extending from each of the frames, and a skin covering the lateral extensions included in the aerodynamic lifting structure. 14. The aircraft as in claim 13 wherein the frames are arranged sequentially along the longitudinal axis and aligned with the aerodynamic lifting surfaces. 15. The aircraft as in claim 13 wherein the aerodynamic lifting structures further comprise supports for aircraft engines, and the supports are at the outer ends of the lateral extensions included in the aerodynamic lifting structure supporting the aircraft engine. 16. The aircraft as in claim 13 wherein the central frame element for each of the frames has a greater thickness along a portion aligned along a straight line with the lateral extensions for the corresponding frame. 17. The aircraft as in claim 16 wherein a lower edge of the portion having the greater thickness is aligned along the straight line with a lower edge of each of the lateral extensions. 18. The aircraft as in claim 16 wherein the portion having the greater thickness is an upper portion of the central frame element. 19. The aircraft as in claim 13 wherein the lateral extensions have outer ends at which are provided aircraft engine connections.
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이 특허에 인용된 특허 (6)
Barmichev, Sergey D.; Kirkbride, David W.; Sankrithi, Mithra M. K. V., Aircraft engine mounting system.
Lafont, Laurent; Saucray, Jean-Michel; Quiroz-Hernandez, Esteban; Antypas, Jerome; Bonnet, Mathieu; Journade, Frederic, Rear part of an aircraft including an engine support structure assembled so as to oscillate on the fuselage.
Clausen Charles C. (Seattle WA) Johnson Ronald C. (Fall City WA) Chee Wan T. (Bellevue WA) Schmidt Warren E. (Erie PA), Vibration isolating engine mount.
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