Abstract: An electrically or hybrid powered multirotor aircraft with complete redundancy on all of its functions of lift, of propulsion, and of control, the aircraft having optimized energy consumption and comprising: a longitudinal structure having two longitudinal beams; a fuselage fastened to the longitudinal structure; two fixed wings serving essentially to provide the aircraft with lift in cruising flight and arranged at respective ends of the longitudinal structure and in a common first plane; at least six rotors serving essentially to provide the aircraft with lift during stages of takeoff and landing, the rotors being arranged in a common second plane distinct from the first plane and parallel to the first plane in such a manner as not to be situated vertically above or below a fixed wing; and two propulsion propellers. An electrical or hybrid power plant serves to drive the rotors and the propulsion propellers in rotation.

Abstract: An electrically or hybrid powered multirotor aircraft with complete redundancy on all of its functions of lift, of propulsion, and of control, the aircraft having optimized energy consumption and comprising: a longitudinal structure having two longitudinal beams; a fuselage fastened to the longitudinal structure; two fixed wings serving essentially to provide the aircraft with lift in cruising flight and arranged at respective ends of the longitudinal structure and in a common first plane; at least six rotors serving essentially to provide the aircraft with lift during stages of takeoff and landing, the rotors being arranged in a common second plane distinct from the first plane and parallel to the first plane in such a manner as not to be situated vertically above or below a fixed wing; and two propulsion propellers. An electrical or hybrid power plant serves to drive the rotors and the propulsion propellers in rotation.

Abstract: The convertible aircraft with tilting rotors comprises two fixed wings with zero sweep on which an inter-connecting shaft is substantially rectilinear and parallel with the pivot axis but offset from this axis, substantially perpendicular to a longitudinal axis of symmetry of the aircraft, the center of gravity of which, in helicopter mode, is substantially in a vertical plane passing through the pivot axis and, in aeroplane mode, is substantially contained in or is in proximity to another vertical plane passing through the straight line of the aerodynamic centers of the wings.

Abstract: To provide aerodynamic continuity between the front part, pivoting with the rotor, and the stationary rear part of a pod housing an engine for driving the rotor, a curved cowl curved about the pivot axis extends the rear edge of the bottom cowling of the front part to join this rear edge to the front edge of a bottom cowling of the stationary rear part, in helicopter mode, and a flap swivel-mounted on the top cowling of the front part joins this latter to the top cowling of the stationary rear part, onto which this flap is folded, in helicopter mode.

Abstract: Landing gear for aerodynes and especially helicopters comprising two lateral members (2) for contact with the ground being linked to the fuselage of the aerodyne by at least two crosspieces (3, 4). These crosspieces (3, 4) are produced as a bundle (7) of unidirectional synthetic fibers sheathed by a skin (8) of tissues of fibers which are crossed with respect to the unidirectional fibers of the bundle (7). The extremities (9) of the crosspieces are embedded in the lateral members (2) for contact with the ground. The structural links between the crosspieces (3, 4) and the fuselage of the aerodyne (H) allow the pivoting of the crosspieces (3, 4) about transverse axes of the aerodyne (H).