An aircraft includes a fuselage having a top surface opposite a bottom surface, a front section, a center section, and a rear section. A first mounting rod and a second mounting rod are coupled to the top surface. The first mounting rod and the second mounting rod are single rods. A first and a second wing are coupled to the center section. A plurality of power generator systems are coupled to the first mounting rod or the second mounting rod. Each power generator system includes a power source, a first propeller and a second propeller. The power source is configured to drive the first propeller and the second propeller. The first propeller and the second propeller have an axis of rotation, and are pivotable between a first position and a second position. A shroud encloses the power generator system.

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 wing. 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. In this vertical flight configuration, the UAV may perform vertical flight or hover. During the vertical flight, the UAV may cause the wing to extend outward via the pivots such that the wing segments become positioned substantially parallel to one another and the wing resembles a conventional fixed wing. With the wing extended, the UAV assumes a horizontal flight configuration that provides upward lift generated from the wing.

Launch and land system for a tethered aircraft (in connection with FIG. 1) The invention provides for a launch and land system (1) for a tethered aircraft (90) comprising a runway (12) for the aircraft and a winch (62) for the tether (92), wherein the runway comprises a funnel-shaped target area (14) with a wide end oriented towards one end of the runway and a narrow end opposite of the wide end, wherein said target area is laterally bordered by restriction devices (80) extending from one end of the target area to the other for preventing the aircraft to roll out of the target area.

Provided is an unmanned aerial vehicle capable of carrying an aerosol container, comprising: a discharge unit with a discharge outlet for discharging contents of the aerosol container from the discharge outlet; a camera capable of capturing footage of the discharge range of the contents; an information acquiring unit for acquiring predetermined information; and an estimation unit for estimating an estimated landing position of the contents based on information obtained by the information acquiring unit. The unmanned aerial vehicle may include a camera capable of capturing footage of a discharge range of the contents; and a coupling unit that is couple with the camera and is a posture control mechanism with rotational degrees of freedom to change a posture.

A lifting system includes an unmanned aerial vehicle, a thruster device, a first wire, a first reel, a second thruster device, a second wire, a second reel, and a controller. When the unmanned aerial vehicle is in a position separated from the ground, the controller detaches the first thruster device and the second thruster device from the unmanned aerial vehicle, causes the first reel to reel out the first wire, detaches the second thruster device from the first thruster device, and causes the second reel to reel out the second wire.

A discharge apparatus and a discharge method for a moving vehicle are provided in which a content in an aerosol container can be stirred in a state where the aerosol container is mounted on the moving vehicle, so that the content of a constant quality can be discharged. The discharge apparatus for a moving vehicle, which is provided with an aerosol container mounted on the moving vehicle and discharges the content in the aerosol container, is characterized by including a stirring means that stirs the content by causing the aerosol container to rotate, reciprocate, swing, vibrate, or otherwise move with respect to the moving vehicle.

Techniques for facilitating an autonomous operation, such as an autonomous navigation, of an unmanned vehicle based on one or more fiducials. For example, image data of a fiducial may be generated with an optical sensor of the unmanned vehicle. The image data may be analyzed to determine a location of the fiducial. A location of the unmanned vehicle may be estimated from the location of the fiducial and the image. The autonomous navigation of the unmanned vehicle may be directed based on the estimated location.

A system and a method are provided for feasibility evaluation of UAV Digital Twin based on Vicon motion capture system is disclosed, which establishes a mission feasibility evaluation model according to flight history data of a target UAV acquired by the UAV Digital Twin system. The mission feasibility evaluation model includes a UAV trajectory prediction module and a mission feasibility determination module. The UAV trajectory prediction module acquires real-time position and attitude information of the target UAV according to the Vicon motion capture system, and predicts target flight trajectory of the target UAV according to the real-time position and attitude information. The mission feasibility determination module compares the position difference between an end point of the target flight trajectory and preset designated mission point to evaluate feasibility of target mission of the target UAV.

A method for controlling an aerial vehicle of a specific type, in particular a multirotor VTOL aerial vehicle with preferably electrically driven rotors, in which a) before a flight, a finite number of nominal trajectories (NT) for the aerial vehicle and a finite number of emergency trajectories (CT) arranged around the nominal trajectories (NT) are calculated and stored in a database available on board the aerial vehicle; b) before a flight, a finite number of type-specific admissible flying maneuvers of the aerial vehicle are pre-planned and stored in the database as a maneuver library; c) optionally before a flight, a number of discrete flight levels with different flight altitudes are defined and stored in the database; d) during a flight, the database is accessed by a computer-aided transition planning algorithm, in order, depending on a state of the aerial vehicle recorded by sensors, to change between the nominal trajectories (NT) and the emergency trajectories (CT) and also optionally between the defined flight levels by using the pre-planned flying maneuvers and to correspondingly activate a path-tracking controller and/or a flight control system of the aerial vehicle.

A system including an unmanned aerial vehicle (UAV) or aerial robotic system (ARS) to perform at least one task to an object during flight of the UAV in a movement mode configured for maneuvering near a surface of the object. A task sensor configured to sense at least one parameter of the surface. An adjustable sensor arm attachable to the UAV and supporting the task sensor to facilitate the task performed to the surface of the object by the UAV during flight of the UAV. The sensor arm being resilient to impact forces caused by direct contact of the sensor or sensor arm with the surface to bend, spring or swivel relative to a contour of the surface.