An aircraft having a variable geometry for adapting the flight characteristics to different flight situations includes a fuselage with a pair of wings projecting on both sides of the fuselage in the transverse direction (y), each of which wings has an inner wing section arranged stationarily with re
An aircraft having a variable geometry for adapting the flight characteristics to different flight situations includes a fuselage with a pair of wings projecting on both sides of the fuselage in the transverse direction (y), each of which wings has an inner wing section arranged stationarily with respect to the fuselage and an outer wing section adjacent thereto and pivotable about a pivot axis. The pivot axis is oriented in a direction deviating from the longitudinal direction (x) of the aircraft by a maximum of 40°.
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1. An aircraft having a variable geometry for adapting the flight characteristics, comprising: a fuselage;a pair of wings projecting on both sides from the fuselage in transverse direction, wherein each of wings of the pair of wings has an inner wing section arranged stationarily with respect to the
1. An aircraft having a variable geometry for adapting the flight characteristics, comprising: a fuselage;a pair of wings projecting on both sides from the fuselage in transverse direction, wherein each of wings of the pair of wings has an inner wing section arranged stationarily with respect to the fuselage and an outer wing section adjacent to the inner wing section, the outer wing section is configured to be pivotable about a pivot axis, wherein the pivot axis is oriented in a direction deviating from a longitudinal direction of the aircraft by a maximum of 40°, and is substantially oriented in said longitudinal direction, wherein when the outer wing sections are in an unpivoted state; anda course of a leading edge of the outer wing sections is offset backward with respect to a course of a leading edge of the inner wing sections and a course of the trailing edge of the outer wing sections is offset backward with respect to a course of the trailing edge of the inner wing sections in such a manner that the leading edges of the outer and inner wings are offset at the pivot axis and the trailing edges of the outer and inner wings are offset at the pivot axis, wherein the outer wing sections are completely aft the inner wing sections. 2. The aircraft of claim 1, wherein the pivot axis is oriented in a direction deviating from a longitudinal direction of the aircraft by a maximum of 20°. 3. The aircraft according to claim 1, further comprising: a control device configured to actuate automatic pivoting of the outer wing sections during flight due to an actuation command or in dependence on at least one flight condition parameter. 4. The aircraft according to claim 1, wherein the pivoting movement is achieved by utilizing aerodynamic forces acting during flight on the outer wing sections. 5. The aircraft according to claim 1, further comprising: a stabilizing mechanism arranged in a region of the pivot axes and configured to lock the outer wing sections in the non-pivoted state against undesired pivoting by aerodynamic forces. 6. The aircraft according claim 1, wherein pivoting is achieved with a pivoting angle of at least 110°. 7. The aircraft of claim 6, wherein pivoting is achieved with a pivoting angle of at least 120°. 8. The aircraft according to claim 1, further comprising: a stabilizing mechanism configured to lock free ends of the outer wing sections in a pivoted state. 9. The aircraft according to claim 1, wherein the pivot axes are arranged such that the wingspan of the aircraft is substantially halved by a pivoting movement. 10. The aircraft according to claim 1, wherein in a non-pivoted state, the wings have a positive leading edge sweep or a positive trailing edge sweep. 11. The aircraft of claim 1, wherein the inner wing sections each include an inner aileron and the outer wing sections each include an outer aileron. 12. An aircraft having a variable geometry for adapting the flight characteristics, comprising: a fuselage;a pair of wings projecting on both sides from the fuselage in transverse direction, wherein each of wings of the pair of wings has an inner wing section arranged stationarily with respect to the fuselage and an outer wing section adjacent to the inner wing section, the outer wing section is configured to be pivotable about a pivot axis, wherein the pivot axis is oriented in a direction deviating from a longitudinal direction of the aircraft by a maximum of 40°, and is substantially oriented in said longitudinal direction;a stabilizing mechanism arranged in a region of the pivot axes and configured to lock the outer wing sections in the non-pivoted state against undesired pivoting by aerodynamic forces; andaerodynamically effective control elements arranged on the outer wing sections, wherein the aerodynamically effective control elements are control flaps or rudders,wherein the aerodynamically effective control elements and the stabilizing mechanism are actuatable in such a manner that the outer wing sections pivot due to aerodynamic forces acting on the outer wing sections, andwherein the aerodynamic forces are the exclusive forces acting to pivot the outer wing sections in a direction of the pivot, wherein the outer wing sections are completely aft the inner wing sections. 13. The aircraft according to claim 12, wherein the stabilizing mechanism is actuatable by a control device to deactivate or at least reduce a locking effect. 14. A method comprising: changing a geometry of an aircraft having fixed inner wing sections coupled to hinged outer wing sections during a flight by adjusting control flaps or rudders arranged on the outer wing sections in such a manner that pivoting of the outer wing sections between a pivoted and non-pivoted state is achieved utilizing aerodynamic forces acting on the outer wing sections of the aircraft, and wherein the aerodynamic forces are the exclusive forces acting to pivot the outer wing sections in a direction of the pivot, wherein the outer wing sections are completely aft the inner wing sections.
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이 특허에 인용된 특허 (12)
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