Rotary-wing aircraft
View Patent ↗A rotary-wing aircraft ( 100 ), comprising at least four rotors ( 110 ), which are disposed on girder elements ( 120 a , 120 b ), wherein said rotors ( 110 ) and girder elements ( 120 a , 120 b ) are disposed such that a free field of vision (S) is defined along a longitudinal axis (L) of said rotary-wing aircraft ( 100 ) at least between two terminal rotors.
1. A rotary-wing aircraft ( 100 ), comprising:
at least four rotors ( 110 ), which are disposed on girder elements ( 120 a , 120 b ),
wherein said rotors ( 110 ) and girder elements ( 120 a , 120 b ) are disposed such that a free field of vision (S) is defined along a longitudinal axis (L) of said rotary-wing aircraft ( 100 ) at least between two terminal rotors;
wherein the girder elements ( 120 a , 120 b ) provide a straight-line connection between the rotors on each side of the longitudinal axis (L);
wherein the girder elements ( 120 a , 120 b ), when viewed from a top view of the aircraft, are disposed in a closed V-shape arrangement symmetrically with respect to the longitudinal axis (L); and
wherein the girder elements connect at a point of intersection with the longitudinal axis.
2. The rotary-wing aircraft according to claim 1 ,
wherein the free field of vision (S), originating from a point near the center of gravity of the aircraft, has an extension with respect to the longitudinal axis of more than ±15° in both the horizontal and the vertical planes.
3. The rotary-wing aircraft according to claim 1 ,
wherein said rotary-wing aircraft further comprises at least one strut element ( 130 ) for bracing said girder elements ( 120 a , 120 b ).
4. The rotary-wing aircraft according to claim 3 ,
wherein said at least one strut element ( 130 ) is configured in the shape of an X.
5. The rotary-wing aircraft according to claim 3 ,
wherein the connections between said at least one strut element ( 130 ) and said girder elements ( 120 a , 120 b ) are releasably and/or rotatably configured.
6. The rotary-wing aircraft according to claim 1 ,
further comprising a body element ( 140 ) with at least one mounting for accommodation of at least one optical and/or sensor element.
7. The rotary-wing aircraft according to claim 6 ,
wherein said at least one mounting is adjustably disposed in proximity to the center of gravity of said rotary-wing aircraft.
8. Use of the rotary-wing aircraft according to claim 6 for environment capture, the use comprising the step of:
capturing environmental data with at least one of an optical and a sensor element attached to the at least one mounting.
9. A rotary-wing aircraft ( 100 ), comprising at least four rotors ( 110 ), which are disposed on girder elements ( 120 a , 120 b ),
wherein said rotors ( 110 ) and girder elements ( 120 a , 120 b ) are disposed such that a free field of vision (S) is defined along a longitudinal axis (L) of said rotary-wing aircraft ( 100 ) at least between two terminal rotors;
wherein the girder elements ( 120 a , 120 b ) provide a straight-line connection between the rotors on each side of the longitudinal axis (L);
wherein the girder elements ( 120 a , 120 b ), when viewed from a top view of the aircraft, are disposed in an open V-shape arrangement symmetrically with respect to the longitudinal axis (L); and
wherein the girder elements are connected to each other via at least one strut element.
10. The rotary-wing aircraft according to claim 9 ,
wherein the free field of vision (S), originating from a point near the center of gravity of the aircraft, has an extension with respect to the longitudinal axis of more than ±15° in both the horizontal and the vertical planes.
11. The rotary-wing aircraft according to claim 9 ,
wherein connections between said at least one strut element and said girder elements ( 120 a , 120 b ) are releasably and/or rotatably configured.
12. The rotary-wing aircraft according to claim 9 , further comprising:
a body element ( 140 ) with at least one mounting for accommodation of at least one optical and/or sensor element.
13. The rotary-wing aircraft according to claim 12 ,
wherein said at least one mounting is adjustably disposed in proximity to the center of gravity of said rotary-wing aircraft.
14. Use of the rotary-wing aircraft according to claim 12 for environment capture, the use comprising the step of:
capturing environmental data with at least one of an optical and a sensor element attached to the at least one mounting.
15. The rotary-wing aircraft according to claim 9 ,
wherein said at least one strut element is configured in the shape of an X.