Abstract: A method for landing an aircraft, which takes off and lands vertically, at a predetermined landing site defined by a circular marking that can be captured optically and has a circular outer contour utilizes a landing system. A camera arranged on the aircraft and directed to the landing site is used to capture images electronically, each of which represents a reproduction of the marking detected at least in sections. Each camera image is evaluated in a control device. The control device is used to fit a geometric object with at least one straight line, which has a predetermined line slope in relation to the camera image, into the reproduction in such a way that the line constitutes a tangent through a contact point to the marking detected at least in sections. The control device steers the aircraft in the direction of the contact point determined in this way.

Abstract: An aircraft has a battery block for supplying the aircraft with energy. The battery block is arrangeable within a battery compartment of the aircraft. The battery compartment is arranged within a volume formed by a fuselage of the aircraft and is accessible from the outside through a receiving opening in the fuselage. The battery block is introducible into the battery compartment through the receiving opening. When the aircraft is used as intended, the receiving opening is arranged on an upwardly facing top side of the fuselage. The battery block is insertable into the battery compartment by the battery block being moved along an introduction axis oriented substantially parallel to the direction of gravitational force. The battery block comprises a handle, which, when the battery block has been inserted properly into the battery compartment, is accessible from outside the aircraft.

Abstract: A main aircraft body is made of fiber-reinforced composite material. The main aircraft body includes a load-bearing structure configured in the form of an elongate fuselage. Two wings are arranged laterally on the elongate fuselage. The wings are configured such that a lifting force is generated for the aircraft. A plurality of receiving devices for receiving drive means are formed on the wings. The main aircraft body is formed from an upper shell and a lower shell. The upper shell and the lower shell are connected to one another along a common connecting surface. An empennage is arranged at a tail of the fuselage. The empennage is formed by a pair of empennage surfaces. Guide surfaces of the pair of empennage surfaces are oriented in a V-shaped manner in relation to one another in a horizontal direction of flight. The upper shell is produced in one piece.

Abstract: An aircraft (1) includes a transporting device (2) for receiving and transporting a plurality of articles. The transporting device (2) includes a plurality of receiving devices (4). A respective article (3) can be releasably arranged on a receiving device (4). The receiving device (4) can be moved into a transporting position and into a release position. In a transporting position of the receiving device (4), the article (3) has been secured on the receiving device (4) and, in a release position, the article (3) has been separated from the receiving device (4). In the transporting position of the receiving device (4), the articles (3) are arranged on an underside (5) of the aircraft (1) and one behind the other in a horizontal direction of flight (6) of the aircraft (1).

Abstract: A vertical take-off aircraft (1) has two wings arranged on an aircraft fuselage (2) of the aircraft (1). Along each wing (3), in each case at least one pivoting drive unit (5) is arranged pivotably on the wings. The at least one pivoting drive unit (5) can be brought into a vertical flying position and into a horizontal flying position. In the vertical flying position, the pivoting drive units (5) generate an uplift necessary for a vertical flying movement of the aircraft (1) and, in the horizontal flying position, a propulsion necessary for a horizontal flying movement of the aircraft (1). On each wing (3), at least one vertical drive unit (6) is arranged rigidly in a vertical flying 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: 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.