| 摘要 |
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.
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