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.

A system for landing, comprising a vertical-take-off-and-landing (VTOL) unmanned air vehicle (UAV) having landing gear, wherein the landing gear is telescopic and comprises a sensor, and wherein the landing gear is compressed upon landing on a surface, and the compression causes a signal to be sent to a system that computes the slope of the ground surface using the length of the compressed landing gear and the attitude of the UAV. If the center of gravity falls within the support area, the legs are locked and the UAV power is turned off. If the center of gravity falls outside the support area, the UAV is forced to take off and find a safer landing spot.

An unmanned rotorcraft has a lift module having a propulsion system and coaxial rotors driven in rotation by the propulsion system. The rotorcraft includes a payload support system adapted to couple an external payload directly to the lift module. The rotorcraft is devoid of provisions for human passengers.

A bracket for connecting a traverse of a landing gear to a cabin of a helicopter. A landing gear retainer is fixed around the traverse coaxially to the longitudinal direction of the traverse and at least one cabin clamp mount is fixed to the cabin. The landing gear retainer is in between the cabin and upper and lower pendulum bolts and upper and lower pendulum bearings. A pendulum is in longitudinal direction of the traverse hinged to the landing gear retainer. The invention is further related to an application of such brackets.

A landing gear includes a pair of skids, a cross tube and a stiffening portion. The pair of skids is arranged in parallel with a front-rear axis of an airframe of a rotary wing aircraft. The cross tube is attached to the airframe and coupling the pair of skids to each other. The cross tube includes curved portions located closer to end portions of the cross tube than to portions of the cross tube attached to the airframe. The stiffening portion suppresses flattening of the cross tube and is arranged in at least one of internal spaces of the curved portions or a stiffened portion located between a pair of curved portions. The stiffening portion includes an enlarged diameter portion which increases in diameter by an axial fastening power acting in an axial direction of the cross tube, and a fastening portion configured to generate the axial fastening power.

A rotorcraft together with a heat dissipation structure for a motor are provided. The motor includes a body and a revolving shaft driven by the body, and the heat dissipation structure for the motor includes: a casing being a hollow structure having a top opening and an air inlet in a bottom portion, in which the body is disposed inside of the casing, and an air channel is formed between a circumferential edge of the body and an inner wall of the casing; a head cover connected to the revolving shaft of the motor synchronously and provided with a plurality of air flow picks on the lower surface thereof; and a mounting stand fixed to an upper surface of the head cover.

An aircraft having an airframe that extends longitudinally along an anteroposterior plane. A buoyancy system is provided with at least one pair of two floats arranged transversely on opposite sides of said anteroposterior plane. Each float is movable in elevation from a bottom position to a top position. For each float, the buoyancy system includes a blocking system for blocking each float by default in the bottom position, and for acting under a predetermined condition to block the floats present on one of the sides only of the aircraft in the top position.

A towing system comprises a bar, a first attachment device arranged at a first end of the bar, the first attachment device being able to attach the towing system to a towing vehicle, a second attachment device arranged at a second end of the bar, the second attachment device being able to attach the towing system to a travelling machine to be towed, the second attachment device comprising a fork able to hold at least one wheel of the travelling machine, the fork having two longitudinal members between which at least one wheel of the travelling machine is able to be received, a separation device able to modify the spacing between the two longitudinal members and a holding device able to hold the wheel between the two longitudinal members.

A helicopter includes a gimbal assembly, a first rotor assembly, a second rotor assembly, a fuselage, and a controller. The first rotor assembly, the second rotor assembly, and the fuselage are mechanically coupled to the gimbal assembly. The first rotor assembly includes a first rotor and the second rotor assembly includes a second rotor, the first rotor including a plurality of first fixed-pitch blades and the second rotor including a plurality of second fixed-pitch blades. Each of the plurality of first and the second fixed-pitch blades are coupled to a hub of its respective rotor via a hinge mechanism that is configured to allow each of the fixed-pitch blades to pivot from a first position to a second position, the first position being substantially parallel to the fuselage and the second position being substantially perpendicular to the fuselage.

A system for weight measurement for an aircraft having a weight on wheels threshold between a flight mode and a ground mode includes a weight on wheels sensor arrangeable on a landing gear assembly of the aircraft, and a computing device receiving first detected data from the sensor related to strain on the landing gear assembly. The computing device calculates a rate of change of the strain over time to determine when the landing gear assembly reaches the weight on wheels threshold. The system also measures aircraft gross weight in a static condition.