An unmanned aerial vehicle (UAV) includes a fuselage, a pair of wings attached to the fuselage, and a propulsion system mounted to the wings to provide propulsion to the UAV. The fuselage has an outer fuselage shell that is a first mechanical support structure for an airframe of the UAV. The pair of wings is attached to the fuselage and shaped to provide aerodynamic lift. The wings have outer wing shells that are second mechanical support structures for the airframe. The outer fuselage shell or the outer wing shells comprise one or more formed-metal sheets.

Implementations of an unmanned aerial vehicle (UAV) fuselage are provided. In some implementations, the fuselage comprises a frame having a shell removably secured thereto. The frame of the fuselage is made of printed circuit board (PCB) material that includes conductive tracks configured to conductively connect electrical components of the UAV. Due to the inherent rigidity of PCB material, the transfer of vibration loads to electrical components secured to the frame of the fuselage is minimized. While the shell is secured to the frame, an enclosure for any electrical components on the topside of the frame is formed. In this way, the encased electrical components may be protected from the environment (e.g., rain) and direct impact during a crash. In some implementations, the frame of the UAV fuselage may include a plurality of stiffening inserts that are positioned and configured to increase the rigidity of the frame.

In some embodiments, a rotor assembly for an aerial vehicle includes a main body; and four or more rotors having blades mounted relative to the main body for rotation about respective axes configured to provide thrust predominantly in a common direction. Respective blade trajectories of rotors of at least one pair of adjacent rotors of the four or more rotors rotate in different planes. The blade trajectories of the at least one pair of adjacent rotors partially overlap when viewed along a line containing the common direction.

Disclosed are devices, systems and methods for mission-adaptable aerial vehicle. In some aspects, a mission-adaptable aerial vehicle includes a configuration having swappable, manipulatable, and interchangeable sections and components connectable by a connection and fastening system able to be modified by an end-user in the field. In some embodiments, a mission-adaptable aerial vehicle can be configured to include a main center body extending along a longitudinal direction, a wing with a lateral cross-sectional airfoil shape, and/or stabilizer and control surface structures with corresponding cross-sectional airfoil shapes.

Disclosed are devices, systems and methods for mission-adaptable aerial vehicle. In some aspects, a mission-adaptable aerial vehicle includes a configuration having swappable, manipulatable, and interchangeable sections and components connectable by a connection and fastening system able to be modified by an end-user in the field. In some embodiments, a mission-adaptable aerial vehicle can be configured to include a main center body extending along a longitudinal direction, a wing with a lateral cross-sectional airfoil shape, and/or stabilizer and control surface structures with corresponding cross-sectional airfoil shapes.

The invention relates inter alia to a drone (10) comprising at least one electromotive drive (24a, 24b) and a controller (33, 33a, 33b), wherein the drone can permanently maintain a set flight position with the aid of the controller, wherein the drone that is in the flight position thereof is connected to a ground station (11) by a cable (13), wherein the cable comprises at least two electrical conductors (27a, 27b, 27c, 27d, 27e, 27f, 27g) for supplying voltage to the drive, wherein the drone comprises lightning-protection means (34a, 34b, 34c) that protects the controller and/or the drive and/or other electronic component parts of the drone from lightning strikes, wherein the overall cross section of the electrical conductors of the cable allows for high electrical currents, caused by lightning strikes, to be conducted away from the drone (10) to the ground station (11), and wherein the cable is connected to a lightning transfer point (16) in the earth (15), in the region of the ground station.

An airframe assembly for an unmanned aerial vehicle (UAV) is provided where the airframe assembly includes a top airframe assembly, a bottom airframe assembly, and a planar support frame disposed between the top and bottom airframe assemblies. The top and bottom airframe assemblies may form one or more rotor ducts disposed about one or more UAV propulsion motor mounts, respectively, where the rotor ducts are configured to protect rotating rotors disposed therein from physical damage caused by impact with environmental flight hazards. The airframe assembly may further include a heat sink thermally coupled to electronics of the UAV and disposed within the airframe assembly such that rotating blades in the rotor ducts cause air to be drawn from outside of inlet orifices of the top airframe assembly, through an airflow channel in which dissipation surfaces of the heat sink are disposed, and into a rotor duct via an airflow outlet.

An unmanned flying device including a body; a first blade and at least a second blade; a coupling assembly for coupling the first blade and the at least second blade to the body, wherein the coupling assembly urges the collapsing of the first blade and the at least second blade towards the body; and wherein both the first blade and the at least second blade are rotateable about the body, and wherein the first blade and the at least second blade are deployable away from the body via rotation of the first and the at least second blades about the body.

The Multi-Rotor Safety Shield (MRSS) provides a complete and substantial encasement system which can be secured about a Drone, protecting a multitude of aircraft components from contact with any outside disturbance and which can protect the sensitive components from dust, water, wind, rain, snow, fingers, toes, appendages of any kind, and atmospheric changes as example, from disabling the Drone and can protect people, places or things from high velocity spinning exposed rotor/propellers. The MRSS provides rigid non-permeable platform for attaching or incorporating additional safety devices as found in the Drone industry (or other industries) resulting in a safety device that completely prevents the loss a Drone due to the catastrophic failure of any Drone system or combination of systems which would typically result in rapid decent, and/or uncontrolled flight. The MRSS makes Drones safe near humans and safe to use around public gatherings, stadium events, accident scenes, disaster search and rescue and disaster relief, and indoors for the security and communications markets among others expanding the availability of Drones to further assist humanity.

A VTOL aircraft having thrust and directional control comprises a fan for providing a centrifugal flow of air. At least one duct allows for and directs air flow. At least one nozzle allows for exhaust release. Each of the at least one nozzle has a first end attached to one of each of the at least one duct. Each of the at least one nozzle has a turn measuring 90? and faces downward from the second end of each of the at least one duct. Each of the at least one nozzle has a second end at which is a vane for redirecting airflow. The VTOL aircraft also has an attachment for landing.