Rotary-Wing Aircraft

• US 20110017865A1
• Filed: 03/17/2009
• Published: 01/27/2011
• Est. Priority Date: 03/18/2008
• Status: Active Grant

• Current Assignee: Intel Corporation
• Original Assignee: Ascending Technologies GmbH (Intel Corporation)
• Inventors: Doth, Klaus-Michael, Gurdan, Daniel, Stumpf, Jan, Achtelik, Michael
• Granted Patent: US 9,051,050 B2
• Time in Patent Office: Days
• US Class Current: 244/17.23
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 47/08 Arrangements of cameras
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/16 with five or more distinct rotor axes, e.g. octocopters
• CPC Class Codes: B64U 20/50 Foldable or collapsible UAVs with frangible components B64U20/30
• CPC Class Codes: B64U 20/87 Mounting of imaging devices, e.g. mounting of gimbals
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/19 using electrically powered motors

Abstract

The invention relates to 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.

Claims

1. 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.

2. Rotary-wing aircraft according to claim 1,

wherein said girder elements (120a, 120b) extend substantially in a straight line on both sides of the longitudinal axis (L).

3. Rotary-wing aircraft according to claim 1,

wherein said girder elements (120a, 120b) are disposed in a V shape symmetrically with respect to the longitudinal axis.

4. Rotary-wing aircraft according to claim 1,

wherein the free field of vision (S), originating from 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.

5. 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).

6. Rotary-wing aircraft according to claim 5,

wherein said at least one strut element (130) is configured in the shape of an X.

7. Rotary-wing aircraft according to claim 5,

wherein the connections between said at least one strut element (130) and said girder elements (120a, 120b) are releasably and/or rotatably configured.

8. 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.

9. Rotary-wing aircraft according to claim 8,

wherein said at least one mounting is adjustably disposed in proximity to the center of gravity of said rotary-wing aircraft.

10. Use of a rotary-wing aircraft according to claim 8 for environment capture by optical and/or sensor elements disposed upon it.