Airbus Helicopters

Aerospatiale Societe Nationale Industrielle

Frederic Balayn

Claude Bietenhader

Xavier Maraninchi

Emmanuel Mermoz

Alande D Rene

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.

Electrically or hybrid powered multirotor aircraft with optimized energy consumption

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).

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Vitrolles, France

Frederic Balayn