Inter alia, the invention relates to an aerial device (10), comprising at least one rotor (12, 12a, 12b) that generates lift forces that, using a controller (18), can be addressed by a drive (16, 16a, 16b), wherein the drive (16, 16a, 16b) comprises an electromotively-driven rotor drive shaft (29). The particular feature of the invention is, among other things, that the drive (16, 16a, 16b) comprises a plurality of electric motors (25, 26, 27) that jointly drive the rotor drive shaft (29).

A rotorcraft with counter-rotating rotor blades can hover in place, translate forwards, backwards, or side-to-side irrespective of the airspeed over the rotorcraft. The rotorcraft includes a fuselage, a first axial-flow rotor, a radial-flow rotor, a propulsion funnel, and a plurality of lift funnels. The fuselage is used to house passengers, cargo, flight electronics, and or fuel. The first axial-flow rotor rotates independent of the radial-flow rotor and generates forward thrust for propelling the rotorcraft. The radial-flow rotor in the opposite direction of the first axial-flow rotor and generates upward thrust for lifting the rotorcraft. The airflow generated by the first axial-flow rotor travels through the propulsion funnel and exits out of the back of the rotorcraft. The airflow generated by the radial-flow rotor travels through the plurality of lift funnels which gradually directs the airflow downwards.

An unmanned aerial vehicle is removably connected to a container. The container has a vessel retaining a pressurized gas supply and a manifold having a plurality of ports connected to a plurality of expandable structures. The pressurized gas supply is in communication with a plurality of expandable structures. The container also has least one compartment having a plurality of expandable structures configured to capture a payload. Additional improvements include an improved docking structure for the unmanned aerial vehicle to engage a container and a rotatable weight distribution system for maintaining a center of gravity at the physical center of gravity of the unmanned aerial vehicle.

A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.

A helicopter includes a propulsion system, gimbal assembly, and a controller. The propulsion system includes a first rotor assembly and a second rotor assembly. The first rotor assembly comprises a first motor coupled to a first rotor and the second rotor assembly comprises a second motor coupled to a second rotor. The second rotor is coaxial to the first rotor and is configured to be counter-rotating to the first rotor. The gimbal assembly couples a fuselage of the helicopter to the propulsion system. The controller is communicably coupled to the gimbal assembly and is configured to provide instructions to the gimbal assembly in order to weight-shift the fuselage of the helicopter, thereby controlling movements of the helicopter.

An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.

The invention pertains to a remote-controlled miniature aircraft with at least one lift surface (17), with at least one pair of propeller drives (12, 13) and with a weight element (20), the position of which can be varied in the longitudinal direction of the miniature aircraft (10) in order to change the center of gravity of the miniature aircraft (10). In order to realize a more compact and more robust construction with improved flying characteristics, the lift surface (17) of the miniature aircraft (10) is arranged above a plane defined by the rotational axes of the propeller drives (12, 13) in order to generate a lifting force for taking off and/or landing from a standstill.

The present disclosure relates to an autonomous, electric, vertical takeoff and landing (VTOL) aircraft that is low-noise, safe, and efficient to operate for cargo transportation over relatively long ranges. A VTOL aircraft includes a fuselage, a plurality of arms, a tail, and a plurality of propulsion systems mounted on the arms and the tail. The plurality of arms have parts that are rotatable and the tail has a part that is rotatable for transitioning the VTOL aircraft between a forward-flight configuration and a hover configuration.

The invention relates to a drone, having at least one central body, at least one thrust element, at least one jointed leg, wherein the at least one jointed leg has leg parts which are connected via joints, wherein the at least one jointed leg is connected in an articulated manner via a proximal end to the central body. It is provided according to the invention that a distal end of at least one jointed leg has an exchangeable chuck, via which the distal end of the jointed leg can be connected to a selection of sensor devices and/or gripping devices and/or tools.

The invention relates to a drone, having at least one central body, at least one thrust element, at least one jointed leg, wherein the at least one jointed leg has leg parts which are connected via joints, wherein the at least one jointed leg is connected in an articulated manner via a proximal end to the central body. It is provided according to the invention that a distal end of at least one jointed leg has an exchangeable chuck, via which the distal end of the jointed leg can be connected to a selection of sensor devices and/or gripping devices and/or tools.