A rotary-wing aircraft (100), comprising at least four rotors (110), which are disposed on girder elements (120a, 120b), wherein said rotors (110) and girder elements (120a, 120b) are disposed such that a free field of vision (S) is defined along a longitudinal axis (L) of said rotary-wing aircraft
A rotary-wing aircraft (100), comprising at least four rotors (110), which are disposed on girder elements (120a, 120b), wherein said rotors (110) and girder elements (120a, 120b) 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.
대표청구항▼
1. A rotary-wing aircraft (100), comprising: at least four rotors (110), which are disposed on girder elements (120a, 120b),wherein said rotors (110) and girder elements (120a, 120b) are disposed such that a free field of vision (S) is defined along a longitudinal axis (L) of said rotary-wing aircra
1. A rotary-wing aircraft (100), comprising: at least four rotors (110), which are disposed on girder elements (120a, 120b),wherein said rotors (110) and girder elements (120a, 120b) 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 (120a, 120b) provide a straight-line connection between the rotors on each side of the longitudinal axis (L);wherein the girder elements (120a, 120b), 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); andwherein 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 (120a, 120b). 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 (120a, 120b) 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 (120a, 120b), wherein said rotors (110) and girder elements (120a, 120b) 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 (120a, 120b) provide a straight-line connection between the rotors on each side of the longitudinal axis (L);wherein the girder elements (120a, 120b), 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); andwherein 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 (120a, 120b) 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.
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Kuntz, Julian, Flying device with improved movement on the ground.
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