An impact absorber device (10) of a fixed landing skid of an aircraft (1) is described. The device comprises a female element (20), a male element (30) and a core (40) arranged between said female element and said male element, wherein said female element comprises a cavity and said male element comprises a support and pressure surface for supporting said core, wherein said core comprises a body with controlled plastic deformation of a metallic material. In embodiments of the invention, the core comprises an extruded body having a honeycomb structure or a body comprising a spirally wound metallic substrate.

A rotorcraft (1) having: a lift rotor (5); a wing (10) extending from a first end (11) carrying a first propulsive propeller (21) to a second end (12) carrying a second propeller (22); landing gear (30); and a tail (40). The rotorcraft (1) is provided with two fuselages (51, 52) secured to said wing (10) between said first and second propulsive propellers (21, 22) in such a manner as to present an inter-fuselage space (60) having no propeller between said fuselages (51, 52), each fuselage (51, 52) including at least one undercarriage of said landing gear (30).

Disclosed is a drone. The present invention includes a plurality of propellers creating a lift to prevent inclination and overturn of the drone due to a lift difference generated from uneven ground, a power driving unit providing a rotation power to each of a plurality of the propellers, a ground sensing unit measuring a distance to a first region of the ground and a shape of the first region, and a controller controlling the power driving unit to differentiate rotation ratios of a plurality of the propellers based on the measured distance and shape if receiving an input signal for landing at the first region.

A drone aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades. The main rotor blades are connected to a first annular gear that rotates in a first direction and the counter-rotation blades rotate are connected to a second annular gear that rotates in a second direction that is opposite the first direction for anti-torque. Planetary gears simultaneously drive the first and second annular gear at about the same speed.

A VTOL aircraft system includes a first unit having a cockpit, at least one propeller, at least two landing legs and at least two locking mechanisms. A second unit has a housing with a base portion, a first unit engaging portion, and at least two lock mechanism-engaging structure, each corresponding to one of the at least two locking mechanisms of the first unit. The housing of the second unit defines at least one interior cavity with at least one cargo area, a central passage providing access between the first and second unit, and a fuel cell configured around the central passage.

A multicopter (100) having a plurality of propellers (1) is configured to be electrically operated. The multicopter (100) is provided with electric motors (2), at least one main battery (3), a generator (4), an engine (5), and a battery condition detecting section (71). The electric motors (2) drive the propellers (1). The main battery (3) is a first electric power source that supplies the electric power to the electric motors (2). The generator (4) is a second electric power source that supplies the electric power to the electric motors (2). The engine (5) drives the generator (4). The battery condition detecting section (71) detects abnormality of the main battery (3). When the battery condition detecting section (71) detects the abnormality of the main battery (3), the generator (4) supplies the electric power that has been converted from motive power from the engine (5) directly to the electric motors (2).

A drone comprising a carrier structure, at least three lift propulsion rotors and a control system delivering at least one electrical power supply to at least three electric motors driving said at least three rotors, said at least three rotors being spaced apart longitudinally and transversely beside one another, wherein said drone includes a wing carrying two half-wings symmetrically about an anteroposterior plane of symmetry P of said drone, serving at least to increase the lift of said drone, each of said two half-wings including at least one movable portion suitable for moving relative to said carrier structure of said drone with at least a first degree of freedom to move in rotation about a first pivot axis parallel to a longitudinal direction X of said drone; and two first electric actuators respectively enabling each of said movable portions of one of said two half-wings.

A flying machine includes a flying machine body including a rotor blade; a frame including a frame body supporting the flying machine body, and a pressing section that is pressed against a target object at least at two locations separated along a direction orthogonal to a width direction of the frame body; and a detector fixed to the frame, and having a detection direction that is a direction orthogonal to a direction joining the two locations together and facing toward the target object.

A rotor with an elongated nosecone structure to provide stability when boarding or deplaning and to prevent damage to rotor blades is disclosed. A rotor as disclosed herein may include a plurality of rotor blades affixed to the hub structure; and an elongated nose structure extending away from the hub in a direction substantially orthogonal to a deployed direction of said rotor blades, the elongated nose structure having a length greater than a diameter of the elongated nose structure.