中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

54 records (took 0.011 seconds)

    WING ASSEMBLY FOR AN AIRCRAFT
    1.
    发明申请
    WING ASSEMBLY FOR AN AIRCRAFT 审中-公开

    公开(公告)号：WO2022175071A1

    公开(公告)日：2022-08-25

    申请号：PCT/EP2022/052300

    申请日：2022-02-01

    Applicant: LILIUM EAIRCRAFT GMBH

    Inventor： BANSAL, Amar ,  WIEGAND, Daniel ,  MÖBIUS, Andreas ,  VERMEIREN, Sébastien

    IPC: B64C3/48 ,  B64C9/16 ,  B64C29/00 ,  B64D27/02 ,  B64D27/12 ,  B64C39/12 ,  B64C11/00 ,  B64D27/24 ,  B64C9/38

    Abstract: The present invention relates to a wing assembly (10) for an aircraft with a fuselage and at least one pair of wings, the wing assembly (10) defining a direction of flow (F) with respect to which the wing assembly (10) is configured to create lift for the aircraft, comprising a main section (12), which is configured to be mounted to the fuselage in a fixed manner so as to extend from the fuselage in an extension direction of the wing; and a plurality of flap sections (14) each with a body part (16), which are mounted to the main section (12) in a pivotable manner so as to be individually pivotable around a pivot axis (A) by means of a pivoting means (18) over a range of angular orientations including a horizontal orientation in which the body part (16) of the flap section (14) is substantially aligned with the main section (12) to form an elongate and substantially continuous cross-section; and a vertical orientation in which the flap section (14) is angled downwards with respect to the main section (12). The invention further relates to an aircraft equipped with at least one pair of such wing assemblies.

    VTOL AIRCRAFT
    2.
    发明申请
    VTOL AIRCRAFT 审中-公开

    公开(公告)号：WO2021069157A1

    公开(公告)日：2021-04-15

    申请号：PCT/EP2020/074778

    申请日：2020-09-04

    Applicant: VOLARE GMBH

    Inventor： FÜRLINGER, Andreas

    IPC: B64C29/00 ,  B64C39/12

    Abstract: The invention relates to a vertical take-off and landing (VTOL), aircraft (1) comprising a fuselage (2) supporting two main wings (6), a first group of propulsion units (11) mounted fixedly on the aircraft (1) in a vertical thrust generating configuration, and a second group of propulsion units (12) each of which is mounted on the aircraft (1) configurable between a vertical thrust generating configuration and a horizontal thrust generating configuration, wherein the first group is subdivided into two front sets (13) and a rear set (14), wherein the two front sets (13) are mounted at opposite sides of the fuselage (2) ahead of the main wings (6) and the rear set (14) is mounted in the fuselage (2), passing therethrough, and wherein the second group is subdivided into a wing set (15) and a tail set (16), wherein the propulsion units (12) of the wing set (15) are mounted at opposite tips (27) of the main 20 wings (6) and the propulsion units (12) of the tail set (16) are mounted at opposite sides of the fuselage (2).

    AN OBLIQUE ROTOR-WING AIRCRAFT
    5.
    发明申请
    AN OBLIQUE ROTOR-WING AIRCRAFT 审中-公开

    公开(公告)号：WO2018060970A3

    公开(公告)日：2018-04-05

    申请号：PCT/IB2017/056043

    申请日：2017-09-29

    Applicant: AMPAIRE, INC.

    Inventor： COMBS, Cory Michael

    IPC: B64C27/22 ,  B64C27/24 ,  B64C27/26 ,  B64C27/30 ,  B64C27/32 ,  B64C29/00 ,  B64C29/02 ,  B64C39/12

    Abstract: An oblique rotor-wing aircraft may be capable of vertical take-off and landing, subsonic cruise, transonic cruise, and/or supersonic cruise. The oblique rotor-wing aircraft may comprise one or more of a fuselage, a rotor-wing, a thrust-vectored propulsion system, a locking mechanism, and/or other components. The rotor-wing may be rotatably coupled to the fuselage. The rotor-wing may rotate about an axis in a first flight mode for vertical takeoff and landing. The oblique rotor-wing aircraft may include a thrust-vectored propulsion system that drives the rotation of the rotor-wing about the axis. The thrust-vectored propulsion system may include multiple, separately operable propulsion systems coupled to the rotor-wing and/or the fuselage. The oblique rotor-wing aircraft may comprise a locking mechanism that locks the rotor-wing at an angle oblique to the fuselage responsive to initiation of a second flight mode. The rotor-wing may be fixed at an angle oblique to the fuselage during the second flight mode.

    "> ЛЕТАТЕЛЬНЫЙ АППАРАТ
    6.
    发明申请
    ЛЕТАТЕЛЬНЫЙ АППАРАТ "ВАРИАНТЫ" 审中-公开
    飞机（变种）

    公开(公告)号：WO2015016731A1

    公开(公告)日：2015-02-05

    申请号：PCT/RU2013/000650

    申请日：2013-07-30

    Applicant: ПЧЕНТЛЕШЕВ, Валерий Туркубеевич

    Inventor： ПЧЕНТЛЕШЕВ, Валерий Туркубеевич

    IPC: B64C39/10 ,  B64C39/08 ,  B64C39/12

    CPC classification number: B64C39/08 ,  B64C39/10 ,  B64C39/12 ,  B64D27/16

    Abstract: Заявляемое изобретение имеет отношение к авиации и касается в частности самолетов. В одном из возможных вариантов своего исполнения заявляемое изобретение имеет две тандемно расположенные несущие поверхности. Передняя несущая поверхность состоит из двух консолей. Консоли передней несущей поверхности примыкают к концевым частям задней несущей поверхности, при этом, ближе к передней кромке задней несущей поверхности. Корневая хорда консолей передней несущей поверхности имеет меньшую величину, чем концевая хорда задней несущей поверхности. Консоли передней несущей поверхности выполнены с возможностью их установки на большие углы атаки, по отношению к задней несущей поверхностью.

    Abstract translation: 所要求保护的发明涉及航空，尤其涉及飞机。 在其可能的变型实施例之一中，要求保护的发明具有串联布置的两个翼型。 领先的机翼由两个面板组成。 引导机翼的面板抵靠后翼面的尖端，靠近尾翼的前缘。 前导机翼的面板的根弦比尾翼的尖端弦具有更小的值。 先导机翼的面板可以设置成相对于尾翼的更高的迎角。

    AIRCRAFT
    7.
    发明申请
    AIRCRAFT 审中-公开
    飞机

    公开(公告)号：WO2011056082A3

    公开(公告)日：2011-08-25

    申请号：PCT/PL2010000110

    申请日：2010-11-05

    Applicant: MARGANSKI EDWARD

    Inventor： MARGANSKI EDWARD

    IPC: B64C39/12

    CPC classification number: B64C5/04 ,  B64C9/10 ,  B64C39/12

    Abstract: The object of the invention is an aircraft provided with a device for creating a constant moment in relation to the axis of rotation of an additional control surface placed at the front of the aircraft at an as large as possible distance from the centre of gravity of the aircraft. The aircraft is characterised in that the control of the aerodynamic vertical force (7) is effected by deflecting control elements (3) pivotably mounted on the rotation axis (4), the deflection of said control elements causing rotation of a balance and control surface (1) mounted rotatably on axis (2), wherein the axis (2) is mounted perpendicularly to the plane of symmetry (5) of aircraft (6) forward of the resultant aerodynamic vertical force (7) generated by the balance and control surface (1).

    Abstract translation: 本发明的目的是提供一种飞行器，该飞行器用于相对于放置在飞机前部的附加控制表面的旋转轴线产生恒定的力矩，该力矩与飞行器的重心距离尽可能大 飞机。 该飞行器的特征在于，通过偏转枢转地安装在旋转轴线（4）上的控制元件（3）来实现气动垂直力（7）的控制，所述控制元件的偏转导致平衡和控制表面（ 其中轴（2）垂直于飞机（6）的对称面（5）安装在由平衡和控制表面（7）产生的合成气动垂直力（7） 1）。

    SERIES OF CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING AND METHOD FOR CONFIGURING A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING
    8.
    发明申请
    SERIES OF CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING AND METHOD FOR CONFIGURING A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING 审中-公开

    公开(公告)号：WO2022263949A1

    公开(公告)日：2022-12-22

    申请号：PCT/IB2022/054836

    申请日：2022-05-24

    Applicant: LEONARDO S.P.A

    Inventor： BIANCO MENGOTTI, Riccardo

    IPC: B64C29/00 ,  B64C3/56 ,  B64C39/12

    Abstract: A series of convertible aircraft (1, 1') with a core (100) with an airframe (2) defining a first axis (Y) is described; a first, a second, a third, a fourth, a fifth and a sixth rotor (20a, 20b, 21a, 21b, 22a, 22b) which are rotatable about respective first, second, third, fourth, fifth and sixth axis (B, C, D, E, F, G), and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value (Tl, T2, T3, T4, T5, T6) independent of each other; the core (100) comprises first and second portions (11, 17) of respective half-wings (3) and aerodynamic surfaces (9) and each module (110, 120, 130, 140) comprises third and fourth portions (12, 18) of respective half-wings (3) and aerodynamic surfaces (9).

    SERIES OF CONVERTIBLE AIRCRAFTS CAPABLE OF HOVERING AND METHOD FOR CONFIGURING A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING
    9.
    发明申请
    SERIES OF CONVERTIBLE AIRCRAFTS CAPABLE OF HOVERING AND METHOD FOR CONFIGURING A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING 审中-公开

    公开(公告)号：WO2022263948A1

    公开(公告)日：2022-12-22

    申请号：PCT/IB2022/054832

    申请日：2022-05-24

    Applicant: LEONARDO S.P.A

    Inventor： BIANCO MENGOTTI, Riccardo

    IPC: B64C29/00 ,  B64C39/02 ,  B64C39/08 ,  B64C39/12

    Abstract: A series of convertible aircrafts (1, 1') with a core (100) with an airframe (2) defining a first axis (Y) is described; a first, a second, a third, a fourth, a fifth and a sixth rotor (20a, 20b, 21a, 21b, 22a, 22b) which are rotatable about respective first, second, third, fourth, fifth and sixth axis (B, C, D, E, F, G), and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value (T1, T2, T3, T4, T5, T6) independent of each other; the core (100) comprises an electric power source (81) and electric motors (72a, 72b, 73a, 73b, 74a, 74b) which are connected to said first, second, third, fourth, fifth and sixth rotor (20a, 20b, 21a, 21b, 22a, 22b); each aircraft (1, 1') of the series comprises a module (110, 120, 130, 140) associated with a respective architecture and interfaced with said core (100).

Patent Agency Ranking