The connection of a rudder unit on the fuselage of an aircraft frequently leads to an inhomogeneous flow of forces in the connecting region between the rudder unit and the fuselage or even to an offset of the flow of forces relative to the centroidal axis, e.g., due to multiple-bolt connections. Thi
The connection of a rudder unit on the fuselage of an aircraft frequently leads to an inhomogeneous flow of forces in the connecting region between the rudder unit and the fuselage or even to an offset of the flow of forces relative to the centroidal axis, e.g., due to multiple-bolt connections. This is extremely disadvantageous with respect to static considerations. One embodiment of the present invention proposes a connection for a rudder unit on an aircraft fuselage, in which the flow of forces resulting from the connection between the rudder unit spars and the fuselage frames extends in a largely homogenous fashion from the rudder unit spars to the fuselage frames and into the fuselage. The connecting elements are advantageously arranged within the rudder unit and the fuselage in such a way that no additional enveloping aerodynamic fairings are required that would result in an additional increase in the aerodynamic drag.
대표청구항▼
The invention claimed is: 1. A connection for a rudder unit on a fuselage of an aircraft, wherein the connection comprises: rudder unit spars, and fuselage frames; an aerodynamic groove; wherein the rudder unit spars are part of the rudder unit; wherein the fuselage frames are part of the fuselage;
The invention claimed is: 1. A connection for a rudder unit on a fuselage of an aircraft, wherein the connection comprises: rudder unit spars, and fuselage frames; an aerodynamic groove; wherein the rudder unit spars are part of the rudder unit; wherein the fuselage frames are part of the fuselage; wherein the rudder unit is supported by connecting the rudder unit spars and the fuselage frames to one another without a bolt fairing structure; wherein a flow of forces resulting from the connection between the rudder unit spars and the fuselage frames extends in an essentially homogenous fashion from the rudder unit spars to the fuselage frames and into the fuselage; wherein the fuselage extends upwardly to form projections substantially along opposing sides of a base portion of the rudder unit such that the projections of the fuselage form the groove for the base portion of the rudder unit, the projections having an outer width corresponding with an outer width of the rudder unit; wherein the groove has an upper taper that is situated at a connecting point between the fuselage structure and the rudder unit wherein a fuselage skin comprises the aerodynamic groove which corresponds to a rudder unit profile and is skin-stressed with frames, stringers, and extends up to the upper taper of an aft fuselage section. 2. The connection of claim 1, further comprising: a rudder unit profile; and wherein the rudder unit profile is part of the rudder unit; wherein the aerodynamic groove is part of the fuselage and has a groove profile; and wherein the groove profile corresponds to the rudder unit profile. 3. The connection of claim 2, wherein the groove is realized in the same fashion as the part of the fuselage situated thereunder up to the upper taper. 4. The connection of claim 1, wherein the rudder unit spars and the fuselage frames overlap one another in pairs; and wherein the rudder unit spars and the fuselage frames are connected to one another at mutual overlaps. 5. The connection of claim 1, wherein the fuselage frames have an upper region and a lower region; wherein the fuselage frames contain a rearwardly directed offset in their upper region, and wherein the offset corresponds to a connecting angle of the rudder unit spars on the lower region of the fuselage frames such that the rudder unit spars and the fuselage frames extend essentially parallel above the offset. 6. The connection of claim 1, wherein the fuselage frames and the rudder unit spars include an angle; and wherein a region formed due to the angle between the fuselage frames and the rudder unit spars is at least partially filled out by a connecting element. 7. The connection of claim 1, wherein the connection between the rudder unit spars and the fuselage frames is adapted as a clip; and wherein a bracket connection is realized with a single or double-sided clip. 8. The connection of claim 1, wherein the rudder unit spars protrude into a groove at a first location and are connected to the fuselage frames at the first location. 9. The connection of claim 8, wherein the fuselage frames protrude into the rudder unit at a second location and are connected to the rudder unit spars at the second location. 10. The connection of claim 1, wherein the flow of forces resulting from the connection between the rudder unit spars and the fuselage frames extends within a rudder unit profile. 11. The connection of claim 1, wherein essentially no offset of the flow of forces relative to a centroidal axis occurs in the components that support the rudder unit. 12. The connection of claim 1, wherein the connection between the rudder unit spars and the fuselage frames is separable. 13. The connection of claim 1, wherein the aircraft is a commercial aircraft; and wherein the commercial aircraft has a primarily cylindrical pressurized cabin. 14. An aircraft, comprising: a connection for a rudder unit on a fuselage of the aircraft, an aerodynamic groove; wherein the rudder unit includes rudder unit spars; wherein the fuselage includes fuselage frames; wherein the rudder unit is supported by connecting the rudder unit spars and the fuselage frames to one another without a bolt-fairing structure; wherein a flow of forces resulting from the connection between the rudder unit spars and the fuselage frames extends in an essentially homogenous fashion from the rudder unit spars to the fuselage frames and into the fuselage, wherein the fuselage extends upwardly to form projections substantially along opposing sides of a base portion of the rudder unit such that the projections of the fuselage form the groove for the base portion of the rudder unit, the projections having an outer width corresponding with an outer width of the rudder unit; wherein the groove has an upper taper that is situated at a connecting point between the fuselage structure and the rudder unit wherein a fuselage skin comprises the aerodynamic groove which corresponds to a rudder unit profile and is skin-stressed with frames, stringers, and extends up to the upper taper of an aft fuselage section.
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이 특허에 인용된 특허 (4)
Larson Robert J. (Seattle WA 4), Aircraft vertical fin-fuselage structural integration system.
Buttgereit Volker (c/o Daimler Benz Aerospace Airbus GmbH ; Patent Dept. 21129 Hamburg DEX) Hempel Joachim (c/o Daimler Benz Aerospace Airbus GmbH ; Patent Dept. 21129 Hamburg DEX) Kiekebusch Burckha, Body tail unit for a commercial aircraft.
Weber, Frank; Schoenfeldt, Olaf, Method for installing a dome-shaped pressure bulkhead in a rear section of an aircraft, and device for carrying out the method.
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