Abstract: A device for the automated vertical take-off, vertical landing, and/or handling of an aerial vehicle with the aid of a robot, the device including a first connection module and a second connection module, each including a capture and/or release section that is active in a capture and/or release phase and a guide section that is active in a guide phase, and the first connection module and the second connection module being lockable in a holding position. An aerial vehicle capable of automatedly vertically taking off, vertically landing, or being handled with the aid of a robot, the aerial vehicle including a first connection module or a second connection module of such a device. An end effector for a robot for the automated vertical take-off, vertical landing, and/or handling of an aerial vehicle, the end effector including a second connection module or a first connection module of such a device.

Abstract: An aircraft system includes an aircraft fuselage having at least one coupling point that is configured to connect various mutually exchangeable drive module units detachably and load-transmittingly to the aircraft fuselage. The aircraft system further includes at least one first drive module unit that is detachably, load-transmittingly and with another drive module unit exchangeably attachable to the at least one coupling point to form a first aircraft comprising the aircraft fuselage and the first drive module unit and at least one second drive module unit that is detachably, load-transmittingly and with another drive module unit exchangeably attachable to the at least one coupling point to form a second aircraft comprising the aircraft fuselage and the second drive module unit. In some embodiments, the first aircraft is a rotary wing aircraft and the second aircraft is a fixed-wing aircraft or a convertiplane.

Abstract: The invention relates to an aircraft (1), preferably an unmanned aircraft (UAV), drone, or Unmanned Aerial System (UAS), comprising a rigid wing (2) which enables aerodynamic horizontal flight, and at least four rotors (4, 4?) which are driven by means of controllable electric motors (5) and which can be pivoted between a vertical starting position and a horizontal flight position by means of a pivoting mechanism (7), wherein all electric motors (5) and rotors (4) are arranged on the wing (2).