Rotary-wing aircraft, comprising: a drive motor (12) with a motor output shaft (12-3), a transfer gearbox (14) having the motor output shaft (12-3) as an input and having a first output (14-1) and a second output (14-2), a cockpit with associated cockpit electronics, a rotary wing with rotor and blades, a tail and tail rotor (20) with a drive shaft (20-1) for driving the tail rotor, and a skids unit with equipment suited to the intended application, characterized in that the motor shaft (12-3) of the motor (12), the transfer gearbox (14) with its second output (14-2) and the drive shaft (20-1) that drives the tail rotor (20) are aligned.

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 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.

Various embodiments of a novel monocoque aerostructure quadcopter implemented as a vertical take-off and landing vehicle are described. In one example, a vertical take-off and landing vehicle includes a fuselage having a leading end positioned in a first horizontal plane and a trailing end positioned in a second horizontal plane that is vertically below the first horizontal plane. The vertical take-off and landing vehicle further includes a first arm assembly extending from the leading end of the fuselage in the first horizontal plane. The vertical take-off and landing vehicle further includes a second arm assembly extending from the trailing end of the fuselage in the second horizontal plane. The vertical take-off and landing vehicle further includes a first rotor assembly coupled to the first arm assembly and a second rotor assembly coupled to the second arm assembly.

Various embodiments of a novel monocoque aerostructure quadcopter implemented as a vertical take-off and landing vehicle are described. In one example, a vertical take-off and landing vehicle includes a fuselage having a leading end positioned in a first horizontal plane and a trailing end positioned in a second horizontal plane that is vertically below the first horizontal plane. The vertical take-off and landing vehicle further includes a first arm assembly extending from the leading end of the fuselage in the first horizontal plane. The vertical take-off and landing vehicle further includes a second arm assembly extending from the trailing end of the fuselage in the second horizontal plane. The vertical take-off and landing vehicle further includes a first rotor assembly coupled to the first arm assembly and a second rotor assembly coupled to the second arm assembly.

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.

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.

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.

A circuit-based vehicle archway assembly having an arched casing with a cylinder ramp at one end and an opposing semi-oval end. It includes a plurality of rotational cylinders within the casing and has respective airfoil bridges between the rotational cylinders. The airfoil bridges and cylinder ramps may be structured to create a cambered hybrid magnus lift airfoil assembly generating directional force to a circuit-based vehicle.