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    MULTI-FUNCTION STRUT
    1.
    发明公开
    MULTI-FUNCTION STRUT 审中-公开

    公开(公告)号：EP3546349A1

    公开(公告)日：2019-10-02

    申请号：EP19161475.9

    申请日：2019-03-08

    申请人： Rolls-Royce plc

    发明人： Moxon, Matthew

    IPC分类号： B64C25/12 ,  B64C1/26 ,  B64C3/16

    摘要： A strut (30) for an aeroplane wing (82) comprises a first part (32) adapted to be connected at one end portion (36) to a fuselage (81) of the aeroplane (80); a second part (34) connected at a first end portion (40) to a second end portion (38) of the first part (32) and adapted to be connected at a second end portion (42) to either a wing (82), a pylon or a nacelle of the aeroplane, the second part (34) being angled to the first part (32) to define an inverted gull-strut arrangement. Either the first part (32) or the second part (34) comprises a compartment (44) to house a landing gear (31) in a folded configuration (Cl).

    An aircraft
    3.
    发明公开
    An aircraft 有权
    一架飞机

    公开(公告)号：EP2878538A1

    公开(公告)日：2015-06-03

    申请号：EP14192431.6

    申请日：2014-11-10

    申请人： Rolls-Royce plc

    发明人： Moxon, Matthew

    IPC分类号： B64D27/12 ,  B64D27/24

    CPC分类号： B64C23/005 ,  B64C3/00 ,  B64C3/28 ,  B64C9/18 ,  B64C11/00 ,  B64C39/00 ,  B64D27/10 ,  B64D27/12 ,  B64D27/24 ,  Y02T50/44 ,  Y02T50/64

    摘要： An aircraft (40). The aircraft (40) comprises a propulsion system comprising a pair of internal combustion engines (10) each driving an electrical power generator (56), each electrical power generator (56) being electrically coupled to a plurality of electrically driven propulsors (46). The propulsors (46) are located forward of a leading edge (45) of the wings (44) such that an airstream generated by the propulsors flows over the wings (44) in use. Each internal combustion engine (10) and electrical generator (56) is mounted on a respective wing (44) outboard of a centre of thrust (70) of the propulsors (46) on that wing (44).

    摘要翻译： 一架飞机（40）。 飞机（40）包括推进系统，该推进系统包括一对内燃机（10），每个内燃机驱动电力发电机（56），每个电力发电机（56）电耦合到多个电力驱动的推进器（46）。 推进器（46）位于机翼（44）的前缘（45）的前方，使得由推进器产生的气流在使用中流过机翼（44）。 每个内燃机（10）和发电机（56）安装在翼（44）上的推进器（46）的推力（70）的中心外侧的相应翼（44）上。

    AIRCRAFT
    4.
    发明公开
    AIRCRAFT 审中-公开

    公开(公告)号：EP3922549A1

    公开(公告)日：2021-12-15

    申请号：EP21173725.9

    申请日：2021-05-13

    申请人： Rolls-Royce plc

    发明人： Moxon, Matthew

    IPC分类号： B64C3/00 ,  B64C11/46 ,  B64C3/32 ,  B64D27/02 ,  B64C3/56

    摘要： An aircraft (1) comprising a wing (3) having a spanwise lift distribution extending from a root (10) to a tip (12), the lift distribution defining an inboard region (14) defining a positive lift contribution, an outboard region (16) defining a negative lift contribution, and an intermediate region (18) defining a neutral lift contribution, the neutral region (18) being spaced from the tip (12) and from the root (10). A propulsion system is provided, comprising a wing mounted propulsor (5). The wing mounted propulsor (5) has a rotational axis (x) positioned substantially at a span of the wing (3) where a value of δLift / δSpan is at a maximum for the span of the wing, and may be located at the intermediate region (18) along the span of the wing (3).

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

    公开(公告)号：EP2963514A1

    公开(公告)日：2016-01-06

    申请号：EP15170958.1

    申请日：2015-06-08

    申请人： Rolls-Royce plc

    发明人： Moxon, Matthew

    IPC分类号： G05D1/00

    CPC分类号： G05D1/042 ,  B64D43/02 ,  G01C23/005 ,  G05D1/0005 ,  G05D1/0055 ,  G05D1/0607

    摘要： A computer implemented method of controlling an aircraft (10). The method comprises the steps of:
    determining whether a change in altitude at a predetermined thrust setting can be performed, the determination comprising:
    determining a climb requirement comprising initial and final altitudes and a required range of airspeeds at the final altitude;
    determining aircraft performance data comprising a thrust at the final altitude at the predetermined thrust setting, an initial airspeed at the initial altitude and an aircraft total mass at the initial altitude;
    using the aircraft performance data to determine a final airspeed and a final drag at the final altitude if a change in altitude at the predetermined setting were performed;
    determining whether thrust at the final altitude at the predetermined thrust settings and
    airspeed is greater than drag; and
    providing a signal indicating whether the calculated final airspeed falls within the required range of airspeeds, and whether the thrust at the final altitude and airspeed at the cruise predetermined thrust setting is greater than drag.

    摘要翻译： 一种控制飞机（10）的计算机实现方法。 该方法包括以下步骤：确定是否可以执行预定推力设定处的高度变化，所述确定包括：确定包括初始和最终高度的爬升要求以及最终高度所需的空速范围; 确定飞机性能数据，其包括在预定推力设置处的最终高度处的推力，初始高度处的初始空速和初始高度处的飞行器总质量; 如果执行了预定设置的高度变化，则使用飞机性能数据来确定最终空速和最终高度的最终阻力; 确定在预定推力设定和空速下的最终高度的推力是否大于阻力; 并且提供指示所计算的最终空速是否落在空速的所需范围内的信号，以及在巡航预定推力设定处的最终高度和空速的推力是否大于阻力。

    AN AIRCRAFT
    9.
    发明授权
    AN AIRCRAFT 有权

    公开(公告)号：EP3048048B1

    公开(公告)日：2018-10-31

    申请号：EP15201624.2

    申请日：2015-12-21

    申请人： Rolls-Royce plc

    发明人： Moxon, Matthew

    IPC分类号： B64D27/02 ,  B64D27/14

    CPC分类号： B64D27/10 ,  B64C39/10 ,  B64C2039/105 ,  B64D27/02 ,  B64D27/14

    摘要： An aircraft (2) comprises at least first and second gas turbine engines (10a, 10b) arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine (10a, 10b) comprising at least one compressor or turbine rotor disc (32 - 42) defining a respective rotational plane (D 32 - D 42 ). The rotational plane (D 32 - D 42 ) of at least one of the rotors (32 - 42) of at least one of the engines (10a, 10b) is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine (10a, 10b) is nonintersecting with another engine (10a, 10b).