An aircraft that can improve cruising speed by making the body shape of the airframe (especially, multicopter) into a shape that has less unnecessary positive lift force by the main body and less drag in the cruising posture of the airframe. An aircraft equipped with a plurality of rotary blades including a propeller and a motor, wherein the aircraft comprises a main body with an inverted airfoil shape. The main body has an attack angle that does not generate a lift force or produces a negative lift force during cruising. The main body has a positive attack angle of 12 degrees or less. Further, it is provided with a mounting unit on which a mounted object can be mounted. The mounting unit is connected to the main body via the connection unit.

A first embodiment includes a circuit based aerial vehicle including an enclosed air duct circuit with a plurality of fans within respective fan tunnels and a plurality of rotating archway assemblies. The rotating archway assemblies may include respective cylinder casings with medial archways, actuating collars at opposing ends of the cylinder casing, and a rotational cylinder rotatable along its longitudinal axis. The actuating collars may be structured to spin their respective cylinder casings along the cylinder casing longitudinal axes thereby orienting the rotational cylinders in different positions along their medial axes.

A second embodiment includes rounded cylinder assemblies with respective bulbous cylinder casings including medial actuating collars that rotate rather than the entire cylinder casing. The actuating collars themselves are structured to spin their respective rotational cylinders along the rotational cylinder longitudinal axes to orient the rotational cylinders in different positions along their medial axes.

A drone chassis including an external structure that deforms elastically in bending, and a set of cables connecting at least one support, intended to support a functional element of the drone, to the external structure. The set of cables includes elastic cables deforming elastically in traction under a tensile stress above a natural deformation threshold, the set of cables being attached at several points on the external structure, referred to as attachment points, to hold the at least one support in a stable position with respect to the external structure. The elastic cables are attached under stress by applying an initial tensile stress and maintains the initial tensile stress by attaching to the external structure. An additional tensile stress applied to the cables attached under stress causes a deformation under traction of the cables only as from a threshold that is above the natural deformation threshold of the cables.

A drone chassis including an external structure that deforms elastically in bending, and a set of cables connecting at least one support, intended to support a functional element of the drone, to the external structure. The set of cables includes elastic cables deforming elastically in traction under a tensile stress above a natural deformation threshold, the set of cables being attached at several points on the external structure, referred to as attachment points, to hold the at least one support in a stable position with respect to the external structure. The elastic cables are attached under stress by applying an initial tensile stress and maintains the initial tensile stress by attaching to the external structure. An additional tensile stress applied to the cables attached under stress causes a deformation under traction of the cables only as from a threshold that is above the natural deformation threshold of the cables.

Methods, apparatus, systems and a vertical take-off and landing (VTOL) vehicle are provided. The VTOL vehicle includes: a fuselage having longitudinally a front section, a central section and a rear section; a first lifting surface comprising two wings respectively secured to opposite sides of the rear section of the fuselage; a second lifting surface comprising two wings respectively secured to opposite sides of the front section of the fuselage; where each wing comprises at least one engine module, each of the engine modules being pivotally coupled to the wing and each engine module being independently controlled for transitioning between a vertical mode of flight and a horizontal mode of flight.

A vehicle can be configured to include a body having a body bottom conjoined with a body sidewall and a body top forming a body cavity. The body top includes a body top opening and the body sidewall includes a body sidewall opening. The vehicle can include a payload housing having a payload bottom conjoined with a payload housing sidewall and a payload housing top forming a payload housing cavity, wherein the payload housing cavity is configured to hold at least one operating module for the vehicle. The vehicle can include at least one arm. The vehicle can include at least one interlocking arrangement of the body top opening or body side wall configured to removably secure the payload housing and the at least one arm to the body. Each of the body, the payload housing, and the at least one arm can be structured with additive manufactured material.

A system and method for pilot assistance in an electric vertical takeoff and landing (eVTOL) aircraft. The system generally includes a pilot control and a flight controller. The pilot control is attached to the eVTOL aircraft. The pilot control is configured to transmit an input relating to the flight path of the aircraft. The flight controller is communicatively connected to the pilot control. The flight controller is configured to receive the input relating to the flight path, generate an output of a recommended flight maneuver as a function of the input, and display the recommended flight maneuver.

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.

An airframe or a part thereof 3, for example a skin assembly or a profile such as a structural profile, comprises: a wall W having an aperture A therethrough, wherein the wall W provides a frame F surrounding, at least in part, the aperture A; a panel P conforming with the aperture A; and wherein the airframe or the part 3 thereof is configurable in: a first configuration, wherein the panel P and the frame F are mutually spaced apart; and a second configuration, wherein the panel P is received in the frame F and wherein the frame F resists movement of the panel P in two or three mutually orthogonal directions.

An unmanned aerial vehicle (UAV) device and the manufacturing process to make the UAV. The UAV device comprises a monocoque shell with a single-piece molded construction that includes a central body and arms that extend outward from the central body. Each of the arms includes a terminal end that is spaced away from the central body. The monocoque shell has a cupped shape with a closed first side and an open second side that includes sidewalls that extend around an interior space. The UAV device comprises a plurality of motors and rotors attached to the first side of the monocoque shell with one of said plurality of motors and rotors positioned at the terminal end of each of the arms.