Abstract: An alignment device aligns a piece good part, which is received by a cable winch, relative to a yaw axis of an aircraft. An alignment member is fastened on an underside of the aircraft, and an alignment mating part fixed to the piece good part. In use, the alignment mating part has an alignment lug pointing towards the aircraft. The alignment member has a guide track having a sliding surface facing the alignment mating part. When the alignment mating part is displaced towards the aircraft, the alignment lug of the alignment mating part abuts the sliding surface through retraction of the cable winch. During further axial displacement of the alignment mating part towards the aircraft, through further retraction of the cable winch, the alignment lug slides along the sliding surface. This causes the alignment mating part to rotate and align the piece good part with the aircraft.

Abstract: A control method for controlling a yaw angle ?z and a roll angle ?x of a vertical take-off aircraft comprising at least two drive groups arranged in opposite side regions of the aircraft so as to be spaced apart from a fuselage of the aircraft is presented. Each drive group comprises at least one first drive unit. The first drive unit is arranged so as to be spaced apart from the fuselage to pivot about a pivot angle ? into a horizontal flight position and a vertical flight position.

Abstract: A control method for controlling a yaw angle ?z and a roll angle ?x of a vertical take-off aircraft comprising at least two drive groups arranged in opposite side regions of the aircraft so as to be spaced apart from a fuselage of the aircraft is presented. Each drive group comprises at least one first drive unit. The first drive unit is arranged so as to be spaced apart from the fuselage to pivot about a pivot angle ? into a horizontal flight position and a vertical flight position.

Abstract: A control method for controlling a yaw angle ?z and a roll angle ?x of a vertical take-off aircraft comprising at least two drive groups arranged in opposite side regions of the aircraft so as to be spaced apart from a fuselage of the aircraft is presented. Each drive group comprises at least one first drive unit. The first drive unit is arranged so as to be spaced apart from the fuselage to pivot about a pivot angle ? into a horizontal flight position and a vertical flight position.

Abstract: A control method for controlling a yaw angle ?z and a roll angle ?x of a vertical take-off aircraft comprising at least two drive groups arranged in opposite side regions of the aircraft so as to be spaced apart from a fuselage of the aircraft is presented. Each drive group comprises at least one first drive unit. The first drive unit is arranged so as to be spaced apart from the fuselage to pivot about a pivot angle ? into a horizontal flight position and a vertical flight position.

Abstract: The invention relates to a wingless aircraft (1) having a plurality of lifting rotors (3) which are driven by electric motor and rotate about various rotor axes (2). The aircraft (1) has at least one energy store (21) for making available the electrical energy necessary to operate the lifting rotors (3), at least one control device (22) for actuating the lifting rotors (3) and for communication with a ground station and at least two camera devices (4) for detecting a panorama image. An extremely small, spherical rotor envelope (5) which encloses all the lifting rotors (3) has a larger volume than an extremely small spherical camera envelope (6) which encloses camera lenses (7) of all the camera devices (4). The camera devices (4) extend over a field of vision, wherein the field of vision surrounds the entire aircraft (1), and wherein the lifting rotors (3) lie outside the field of vision.

Abstract: The invention relates to a wingless aircraft (1) having a plurality of lifting rotors (3) which are driven by electric motor and rotate about various rotor axes (2). The aircraft (1) has at least one energy store (21) for making available the electrical energy necessary to operate the lifting rotors (3), at least one control device (22) for actuating the lifting rotors (3) and for communication with a ground station and at least two camera devices (4) for detecting a panorama image. An extremely small, spherical rotor envelope (5) which encloses all the lifting rotors (3) has a larger volume than an extremely small spherical camera envelope (6) which encloses camera lenses (7) of all the camera devices (4). The camera devices (4) extend over a field of vision, wherein the field of vision surrounds the entire aircraft (1), and wherein the lifting rotors (3) lie outside the field of vision.

Abstract: A vertical-takeoff aircraft with a wing. A first drive unit and a second drive unit are swivellably mounted on the wing. The first drive unit and the second drive unit are arranged on the wing at a distance from a wing-end of the wing. A first distance between the first drive unit and a longitudinal axis of the aircraft is approximately equal to a second distance between the second drive unit and the longitudinal axis of the aircraft. The first drive unit and the second drive unit are swivellable into a horizontal flying position and a vertical flying position. In the horizontal flying position the first drive unit is arranged above a wing surface and the second drive unit below the wing surface on the wing. In the vertical flying position the first drive unit and the second drive unit are arranged in an approximately horizontal plane. The first drive unit and the second drive unit each have a swivel arm, wherein the swivel arms are swivellably mounted on the wing.

Abstract: A vertical-takeoff aircraft with a wing. A first drive unit and a second drive unit are swivellably mounted on the wing. The first drive unit and the second drive unit are arranged on the wing at a distance from a wing-end of the wing. A first distance between the first drive unit and a longitudinal axis of the aircraft is approximately equal to a second distance between the second drive unit and the longitudinal axis of the aircraft. The first drive unit and the second drive unit are swivellable into a horizontal flying position and a vertical flying position. In the horizontal flying position the first drive unit is arranged above a wing surface and the second drive unit below the wing surface on the wing. In the vertical flying position the first drive unit and the second drive unit are arranged in an approximately horizontal plane. The first drive unit and the second drive unit each have a swivel arm, wherein the swivel arms are swivellably mounted on the wing.