The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and/or horizontal thrust depending on the configuration. One or more of the propellers may be configured to tilt forward, backward, and/or side-to-side with respect to the airframe.

Systems, devices, and methods for receiving, by a processor having addressable memory, data representing a geographical area for imaging by one or more sensors of an aerial vehicle; determining one or more straight-line segments covering the geographical area; determining one or more waypoints located at an end of each determined straight-line segment, where each waypoint comprises a geographical location, an altitude, and a direction of travel; determining one or more turnarounds connecting each of the straight-line segments, where each turnaround comprises one or more connecting segments; and generating, by the processor, a flight plan for the aerial vehicle comprising: the determined one or more straight-line segments and the determined one or more turnarounds connecting each straight-line segment.

A method and device for controlling a flight of an unmanned aerial vehicle (UAV) is provided. The UAV includes a fuselage, two wings, two supporting arms, two rotor wing structures, two second power modules, two third power modules, two steering modules, a lifting module, an altitude sensor, and a speed sensor. The two wings are fixed to the fuselage, the supporting arms are fixed to the wings, the rotor wing structure includes a first power module and a driving module, the driving module of the rotor wing structure is fixed to the supporting arm, and the driving module is configured to drive the first power module to rotate such that the first power module switches between the level flight mode and the lifting mode.

A method and device for controlling a flight of an unmanned aerial vehicle (UAV) is provided. The UAV includes a fuselage, two wings, two supporting arms, two rotor wing structures, two second power modules, two third power modules, two steering modules, a lifting module, an altitude sensor, and a speed sensor. The two wings are fixed to the fuselage, the supporting arms are fixed to the wings, the rotor wing structure includes a first power module and a driving module, the driving module of the rotor wing structure is fixed to the supporting arm, and the driving module is configured to drive the first power module to rotate such that the first power module switches between the level flight mode and the lifting mode.

Embodiments of the present disclosure relate to the technical field of unmanned aerial vehicles, in particular to a tiltable wing and an unmanned aerial vehicle. The tiltable wing includes a wing body, a wingtip, a power device, a cable, a rotating shaft and a driving mechanism. The power device is mounted on the wingtip; one end of the cable is connected to the power device, the rotating shaft is rotatably connected to the wing body and the wingtip, respectively, a through hole is disposed in an axial direction of the rotating shaft, and the other end of the cable passes through the through hole and extends to the inside of the wing body; the driving mechanism is used for driving the wingtip to rotate with the rotating shaft as an axis; and the power device is switchable between a first preset position and a second preset position relative to the wing body, so that the power device is switched between a horizontal state and a vertical state.

An aircraft for vertical take-off and landing includes an aircraft frame having an open frame portion, at least one vertical thruster, a pod, separable from the aircraft and including a cabin to contain at least one of cargo and passengers, where the pod, when mounted to the aircraft, defines at least a portion of the aircraft frame, and a mounting system including at least one attachment member configured to attach the pod to the open frame portion. Such aircraft is capable of flight with and without the pod.

An aircraft includes a fuselage coupled to a wing having a root section and first and second outboard sections each having first and second wing layers pivotably coupled to respective outboard ends of the root section. A thrust array is coupled to the wing. A power system is operably associated with the thrust array to provide power to each of a plurality of propulsion assemblies. A flight control system is operably associated with the thrust array and the wing. The flight control system is operable to control the thrust output from the propulsion assemblies and the configuration of the wing. In a thrust-borne vertical lift mode, the wing has a split wing configuration such that the thrust array forms a two dimensional thrust array. In the wing-borne forward flight mode, the wing has a monoplane configuration such that the thrust array forms a one dimensional thrust array.

A vertical take-off aircraft with a propulsion drive for generating a driving force being effective in a horizontal direction and with a lift drive for generating a lifting force being effective in a vertical direction includes a motor for providing mechanical energy for the propulsion drive and a first generator for providing electrical energy for the lift drive. Moreover, the aircraft includes an exhaust gas turbocharger for the motor with a first turbine being driven by an exhaust gas flow of the motor, wherein the first turbine is configured to provide mechanical energy for the propulsion drive.

A modular payload airframe section for an aircraft airframe is disclosed. The modular payload airframe section comprises: a storage volume for receiving a payload; a releasable fixation means for releasably affixing the modular payload airframe section to an airframe of the aircraft; and wherein the modular payload airframe section forms at least part of a nose-cone of the aircraft airframe when affixed thereto.

This disclosure is directed to an unmanned aerial vehicle (UAV) that transitions in-flight between vertical flight configuration and horizontal flight configuration by changing an orientation of the UAV by approximately ninety degrees. The UAV may include propulsion units that are coupled to a fuselage or wing. The UAV may include a tail and/or a swing arm that is rotatably coupled to the fuselage and that rotate between different positions. The swing arm may be selectively coupled to cargo. The wing may include wing segments rotatably coupled together by pivots that rotate to position the propulsion units around a center of mass of the UAV when the fuselage is oriented perpendicular with the horizon.