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    Buoyancy system for an aircraft
    1.
    发明授权
    Buoyancy system for an aircraft 有权
    飞机浮力系统

    公开(公告)号：US09533757B2

    公开(公告)日：2017-01-03

    申请号：US14513508

    申请日：2014-10-14

    Applicant: AIRBUS HELICOPTERS

    Inventor： Louis Delorme ,  Nicolas Lamarche ,  David Ayache ,  Bernard Certain

    IPC: B64C25/56 ,  B64D25/00 ,  B64C25/32

    CPC classification number: B64C25/56 ,  B64C2025/325 ,  B64D25/00 ,  B64D2201/00

    Abstract: A buoyancy system (10) for an aircraft (1), the buoyancy system (10) being provided with at least one inflatable float (15). The buoyancy system (10) has at least one inflator (25) and at least one actuator (30) interposed between the inflator (25) and a float (15), the actuator (30) having a cylinder (35) and a rod (40) partially received in the cylinder (35). The rod (40) is secured to a piston (50) defining a first chamber (61) within the cylinder (35) and in fluid flow communication with the inflator (25), and a second chamber (62) within the rod (40) and in fluid flow communication with the float (15), and the piston (50) has a channel (63) to put the first chamber (61) into fluid flow communication with the second chamber (62), the deployment device (20) having a shutter (70) for shutting the channel (63).

    Abstract translation: 一种用于飞机（1）的浮力系统（10），所述浮力系统（10）设置有至少一个可充气浮子（15）。 浮力系统（10）具有至少一个充气机（25）和置于充气机（25）和浮子（15）之间的至少一个致动器（30），所述致动器（30）具有气缸（35）和杆 （40）部分地容纳在气缸（35）中。 所述杆（40）固定到限定所述气缸（35）内并与所述充气机（25）流体连通的第一室（61）的活塞（50），并且所述杆（40）内的第二室（62） ）并且与所述浮子（15）流体连通，并且所述活塞（50）具有通道（63）以使所述第一室（61）与所述第二室（62）流体连通，所述展开装置（20） ）具有用于关闭通道（63）的快门（70）。

    Automatic flight control method for a rotorcraft enabling the rotorcraft to maintain a path by tracking manual flight controls
    2.
    发明授权
    Automatic flight control method for a rotorcraft enabling the rotorcraft to maintain a path by tracking manual flight controls 有权
    用于旋翼航空器的自动飞行控制方法，使得旋翼航空器能够通过跟踪手动飞行控制来维持航路

    公开(公告)号：US08977412B2

    公开(公告)日：2015-03-10

    申请号：US13908364

    申请日：2013-06-03

    Applicant: Airbus Helicopters

    Inventor： Bernard Certain

    IPC: B64C27/56 ,  B64C27/78

    CPC classification number: G05D1/0808 ,  B64C13/18 ,  B64C27/57 ,  G05D1/0858 ,  G05D1/102

    Abstract: A method of enabling an autopilot (9) to cause a rotorcraft (1) to follow a path. At least one guide mode (G) relative to at least one progression axis (P, R, V, Y) of the rotorcraft (1) is selected by the rotorcraft pilot. Said selection causes the selected guide mode (G) to be inhibited (19) and causes a path setpoint (C) to be acquired (20) from the pilot of the rotorcraft (1) operating a manual control member (4) for controlling the progression of the rotorcraft (1). The path setpoints (C) relating to other guide modes (G) of the rotorcraft (1) that continue to be engaged are conserved in their initial states and the autopilot (9) adapts the commands relating to the progression axes (P, R, V, Y) relating to these other guide modes (G).

    Abstract translation: 一种使自动驾驶仪（9）能够使旋翼航空器（1）沿着路径行进的方法。 相对于旋翼航空器（1）的至少一个前进轴（P，R，V，Y）的至少一个引导模式（G）由旋翼飞行员选择。 所述选择使得所选择的引导模式（G）被禁止（19），并且导致从操作手动控制构件（4）的旋翼航空器（1）的导频获取路径设定点（20），以控制 旋翼航空器（1）的进展。 与其继续接合的旋翼航空器（1）的其他导向模式（G）相关的路径设定点（C）在其初始状态下是保守的，并且自动驾驶仪（9）适应与进度轴（P，R， V，Y）与这些其他指导模式（G）有关。

    Method of stopping a rotorcraft engine in overspeed, and a system and a rotorcraft associated therewith
    4.
    发明授权
    Method of stopping a rotorcraft engine in overspeed, and a system and a rotorcraft associated therewith 有权

    公开(公告)号：US10150569B2

    公开(公告)日：2018-12-11

    申请号：US14867464

    申请日：2015-09-28

    Applicant: AIRBUS HELICOPTERS

    Inventor： Bernard Certain

    IPC: F02C9/28 ,  B64D31/06 ,  B64D27/10 ,  F02C9/26 ,  F02C9/46 ,  F02C3/10

    Abstract: A method of stopping an engine of a rotorcraft in overspeed, the engine comprising a gas generator and a power assembly. When the engine is in operation, a relationship is established giving a limit derivative that varies as a function of the speed of rotation of the power assembly. The speed of rotation, referred to as the “current speed”, reached by the power assembly is measured and the time derivative of the speed of rotation is determined and referred to as the “current derivative”. The engine is stopped automatically when the limit derivative corresponding to the current speed as determined by the relationship is less than or equal to the current derivative.

    Rotary wing aircraft having a non-ducted tail rotor with at least five blades
    6.
    发明授权
    Rotary wing aircraft having a non-ducted tail rotor with at least five blades 有权

    公开(公告)号：US10131425B2

    公开(公告)日：2018-11-20

    申请号：US14946862

    申请日：2015-11-20

    Applicant: AIRBUS HELICOPTERS

    Inventor： Bernard Certain

    IPC: B64C11/06 ,  B64C11/30 ,  B64C27/82

    Abstract: A non-ducted tail rotor comprising a hub and at least five blades, each of the blades extending to a free end that, in rotation, describes a circle presenting a given “maximum” radius. The hub is rigidly secured to a drive shaft, the hub comprising a hollow circular body centered on an axis of rotation, the body presenting an “internal” radius between the axis of rotation and an outer periphery of the body, the internal radius lying in the range 0.2 times to 0.4 times the maximum radius, each blade presenting a root extended by an airfoil element projecting from the body, extending from the root to the free end, the root being swivel-hinged to the outer periphery about a pitch axis.

    Rotary wing aircraft having two main engines together with a less powerful secondary engine, and a corresponding method
    8.
    发明授权
    Rotary wing aircraft having two main engines together with a less powerful secondary engine, and a corresponding method 有权
    具有两个主发动机和较不强力的二次发动机的旋翼机，以及相应的方法

    公开(公告)号：US09353642B2

    公开(公告)日：2016-05-31

    申请号：US14085034

    申请日：2013-11-20

    Applicant: AIRBUS HELICOPTERS

    Inventor： Bernard Certain

    IPC: B64D35/00 ,  F01D13/00 ,  B64C27/12 ,  F01D15/12 ,  B64D35/08

    CPC classification number: F01D13/003 ,  B64C27/12 ,  B64D35/08 ,  F01D15/12

    Abstract: An aircraft (1) having a rotary wing (2) and turboshaft engines (11, 12, 13) for driving said rotary wing (2). The aircraft then includes two main engines (11, 12) that are identical, each capable of operating at at least one specific rating associated with a main power (maxTOP, OEIcont), and a secondary engine (13) capable of operating at at least one specific rating by delivering secondary power (maxTOP′, OEIcont′) proportional to the corresponding main power (maxTOP, OEIcont) in application of a coefficient of proportionality (k) less than or equal to 0.5, said aircraft having a control system (20) for driving the rotary wing by causing each main engine (11, 12) to operate continuously throughout a flight, and by using the secondary engine (13) as a supplement during at least one predetermined specific stage of flight.

    Abstract translation: 具有用于驱动所述旋转翼（2）的旋翼（2）和涡轮轴发动机（11,12,13）的飞机（1）。 飞机然后包括两个相同的主发动机（11,12），每个主发动机能够以至少一个与主功率（maxTOP，OEIcont）相关联的特定额定值和至少能够至少操作的次级发动机（13） 所述飞机具有控制系统（20（20）），通过在比例系数（k）小于或等于0.5的情况下提供与相应的主功率（maxTOP，OEIcont）成比例的次级功率（maxTOP'，OEIcont' ），用于通过使每个主发动机（11,12）在整个飞行中连续地操作并且在至少一个预定的特定飞行阶段期间通过使用二次发动机（13）作为补充来驱动旋转翼。

    Ducted rotor for an aircraft and a rotorcraft
    9.
    发明授权
    Ducted rotor for an aircraft and a rotorcraft 有权
    用于飞机和旋翼航空器的导管转子

    公开(公告)号：US09302769B2

    公开(公告)日：2016-04-05

    申请号：US14267264

    申请日：2014-05-01

    Applicant: AIRBUS HELICOPTERS

    Inventor： Bernard Certain

    IPC: B64C27/82 ,  B64C27/467

    CPC classification number: B64C27/82 ,  B64C27/467 ,  B64C2027/8254

    Abstract: A rotorcraft ducted rotor comprising a rotary assembly arranged in a passage to rotate about an axis of symmetry (AX1). The rotary assembly (15) has a plurality of blades (20), each fastened to a hub (16), each blade (20) complies with a twisting relationship defining an angle of twist lying in the range zero degrees inclusive to 5 degrees inclusive. Spanwise, each blade (20) comprises a first zone (21) followed by a second zone (22), which second zone presents rearward sweep, being provided with a second trailing edge (30″) situated downstream from a first trailing edge (30′) of the first zone (21). Each first zone (21) includes a root (24) connected to the hub (16) by a fastener device (40) having a rolling bearing (45) without clearance and a conical laminated abutment (50).

    Abstract translation: 一种旋翼航空器导管转子，其包括设置在围绕对称轴线（AX1）旋转的通道中的旋转组件。 旋转组件（15）具有多个叶片（20），每个叶片（20）均紧固到轮毂（16），每个叶片（20）符合扭转关系，该扭转关系限定了在0度至5度范围内的扭转角度 。 每个叶片（20）包括第一区域（21），随后是第二区域（22），该第二区域呈向后扫掠，设置有位于第一后缘（30“）下游的第二后缘（30”） '）的第一区（21）。 每个第一区域（21）包括通过具有无空隙的滚动轴承（45）和锥形层压邻接（50）的紧固装置（40）连接到轮毂（16）的根部（24）。

    AUTOMATIC FLIGHT CONTROL METHOD FOR A ROTORCRAFT ENABLING THE ROTORCRAFT TO MAINTAIN A PATH BY TRACKING MANUAL FLIGHT CONTROLS
    10.
    发明申请
    AUTOMATIC FLIGHT CONTROL METHOD FOR A ROTORCRAFT ENABLING THE ROTORCRAFT TO MAINTAIN A PATH BY TRACKING MANUAL FLIGHT CONTROLS 有权
    自动飞行控制方法，用于通过跟踪手动飞行控制使转子维持航向的转轮

    公开(公告)号：US20150309513A1

    公开(公告)日：2015-10-29

    申请号：US14616195

    申请日：2015-02-06

    Applicant: AIRBUS HELICOPTERS

    Inventor： Bernard Certain

    IPC: G05D1/08

    CPC classification number: G05D1/0808 ,  B64C13/18 ,  B64C27/57 ,  G05D1/0858 ,  G05D1/102

    Abstract: A method of enabling an autopilot (9) to cause a rotorcraft (1) to follow a path. At least one guide mode (G) relative to at least one progression axis (P, R, V, Y) of the rotorcraft (1) is selected by the rotorcraft pilot. Said selection causes the selected guide mode (G) to be inhibited (19) and causes a path setpoint (C) to be acquired (20) from the pilot of the rotorcraft (1) operating a manual control member (4) for controlling the progression of the rotorcraft (1). The path setpoints (C) relating to other guide modes (G) of the rotorcraft (1) that continue to be engaged are conserved in their initial states and the autopilot (9) adapts the commands relating to the progression axes (P, R, V, Y) relating to these other guide modes (G).

    Abstract translation: 一种使自动驾驶仪（9）能够使旋翼航空器（1）沿着路径行进的方法。 相对于旋翼航空器（1）的至少一个前进轴（P，R，V，Y）的至少一个引导模式（G）由旋翼飞行员选择。 所述选择使得所选择的引导模式（G）被禁止（19），并且导致从操作手动控制构件（4）的旋翼航空器（1）的导频获取路径设定点（20），以控制 旋翼航空器（1）的进展。 与其继续接合的旋翼航空器（1）的其他导向模式（G）相关的路径设定点（C）在其初始状态下是保守的，并且自动驾驶仪（9）适应与进度轴（P，R， V，Y）与这些其他指导模式（G）有关。

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