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    PROPULSION UNIT FOR A VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    1.
    发明公开
    PROPULSION UNIT FOR A VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-公开

    公开(公告)号：EP4434880A1

    公开(公告)日：2024-09-25

    申请号：EP23163557.4

    申请日：2023-03-22

    申请人： Lilium GmbH

    发明人： Sorbilli Cardoso de Sousa, Rodrigo ,  Bittel, Nele

    IPC分类号： B64C29/00 ,  B64C21/00 ,  B64C3/38 ,  B64D29/02

    CPC分类号： B64C29/0033 ,  B64C21/00 ,  B64D29/02 ,  B64C11/001

    摘要： The invention related to a propulsion unit (10) for a vertical take-off and landing aircraft (100), comprising a fan engine housing (20) with a fan engine (24), further comprising a mounting interface (30) for mounting at a wing (110) of the aircraft (100) moveable between at least one hovering position (HP) and at least one cruising position (CP), wherein the fan engine housing (20) comprises at least one aerodynamic stall element (40) at an upper leading edge (23) and wherein the aerodynamic stall element (40) extends transverse to an engine axis (EA) of the fan engine housing (20) to generate a controlled stall at the upper surface (25) at least in one position between the at least one hovering position (HP) and the at least one cruising position (CP) during flight conditions.

    A HYBRID AIR VEHICLE
    2.
    发明公开
    A HYBRID AIR VEHICLE 审中-公开

    公开(公告)号：EP4420978A1

    公开(公告)日：2024-08-28

    申请号：EP23275033.1

    申请日：2023-02-24

    申请人： BAE SYSTEMS plc

    发明人： The designation of the inventor has not yet been filed

    IPC分类号： B64C27/24 ,  B64U10/10 ,  B64U30/21 ,  B64U50/13 ,  B64C3/38 ,  B64C3/44

    CPC分类号： B64C27/24 ,  B64U30/21 ,  B64U50/13 ,  B64U10/10 ,  B64C3/38 ,  B64C2003/44520130101

    摘要： The present invention provides an air vehicle. The air vehicle comprises: a fuselage; a wing body and a pair of opposing wing members extending substantially laterally from the wing body; a stabiliser for generating force that, in use, counteracts torque exerted on the fuselage by the rotating wing body; a rotor mast for coupling the wing body to an upper side of the fuselage, wherein in a first configuration of the air vehicle the rotor mast is locked such that the wing body does not rotate relative to the fuselage and in a second configuration of the air vehicle the rotor mast is unlocked such that the wing body rotates relative to the fuselage; and propulsion means for providing linear thrust in the first configuration and for providing rotary thrust in the second configuration. The present invention also provides a method of controlling an air vehicle.

    AIRCRAFT FLIGHT CONTROL METHOD
    7.
    发明公开
    AIRCRAFT FLIGHT CONTROL METHOD 审中-公开

    公开(公告)号：EP3778380A1

    公开(公告)日：2021-02-17

    申请号：EP18911427.5

    申请日：2018-03-29

    申请人： Narahara, Yutaka

    发明人： Narahara, Yutaka

    IPC分类号： B64C3/38 ,  B64C27/08

    摘要： The present invention is a method for realizing a vertical take-off and landing aircraft that does not use a mechanism dedicated for take-off and landing, which cannot be achieved on the basis of an existing concept of aircraft flight control, by introducing a new concept of a shoulder rotational axis and an arm rotational axis into aircraft flight control and controlling vertical take-off and landing and ordinary flight with the same mechanism. This instruction eliminates a necessity of a tail and ailerons from an airframe of the aircraft, enables reduction of manufacturing, maintenance, and running costs thereof, and makes it possible to avoid problems of maneuverability and cruising distance performance of airframes of vertical take-off and landing aircrafts.

    HYBRID UNMANNED AERIAL VEHICLE
    8.
    发明公开
    HYBRID UNMANNED AERIAL VEHICLE 审中-公开

    公开(公告)号：EP3736213A1

    公开(公告)日：2020-11-11

    申请号：EP19425034.6

    申请日：2019-05-07

    申请人： International Aviation Supply I.A.S. S.R.L.

    发明人： DE Otto, Gian Livio ,  GRASSO, Teodoro ,  LACAITA, Cosimo ,  MAIORANO, Alessandro ,  MARTORANA, Vincenzo ,  RUGGIERO, Andrea

    IPC分类号： B64C29/00 ,  B64C25/10 ,  B64C3/38

    摘要： A convertible aircraft (100) comprising a fuselage body (10) extending according to a main longitudinal direction (L) of development and including a receiving housing (50a, 50b, 50c, 50d); a propulsion unit, connected to the fuselage body (10) and comprising first motor means (20) configured to supply a thrust parallel (H) to said longitudinal direction (L), second motor means (30a, 30b, 30c, 30d) configured to supply a thrust orthogonal (V) to said longitudinal direction (L), which second motor means (30a, 30b, 30c, 30d) are movable between an extracted configuration and a retracted configuration, the aircraft further comprising a wing folding system comprising opposed wings (41, 42) projecting from the fuselage body (10), which opposed wings (41, 42) being configured to be folded so as to define opposite terminal portions (41a, 42a) each intended to support the aircraft (100) on a landing and/or taking-off region, wherein the receiving housing (50a, 50b, 50c, 50d) of the fuselage body (10) and the second motor means (30a, 30b, 30c, 30d) are configured so that the receiving housing entirely encloses the second motor means (30a, 30b, 30c, 30d) inside it in said retracted configuration.