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180 条记录 (耗时 0.019 秒)

    System for heat dissipation from an internal actuator in a rotor blade
    12.
    发明公开
    System for heat dissipation from an internal actuator in a rotor blade 有权
    系统用于在转子叶片从内部致动器散热

    公开(公告)号：EP2567894A1

    公开(公告)日：2013-03-13

    申请号：EP11185125.9

    申请日：2011-10-13

    申请人： Bell Helicopter Textron Inc.

    发明人： Schank, Troy C ,  McGlaun, Monte A

    IPC分类号： B64C27/615 ,  B64C27/72

    CPC分类号： B64C27/615 ,  B64C27/72 ,  B64C2027/7266 ,  Y02T50/34

    摘要： A rotor blade (109) for an aircraft (101) includes an airfoil skin, an active element (125), and an actuator (129) configured to operate the active element. A heat pipe (131) is configured to promote heat transfer from the actuator to the airfoil skin. The heat pipe has a slope gradient such that a centrifugal force generated during rotation of the rotor blade promotes travel of a condensed working fluid within the heat pipe (131) to move from a condenser end (145) of the heat pipe toward an evaporator end (147) of the heat pipe.

    摘要翻译： 在飞行器（101）的转子叶片（109）包括在翼面蒙皮到activeElement（125），并且配置成操作所述有源元件到致动器（129）。 一种热管（131）被配置为促进从所述致动器的热传递到翼面蒙皮。 该热管具有倾斜梯度搜索做了转子叶片的旋转期间产生的离心力促进热管（131）内的冷凝的工作流体的行程从所述热管朝向蒸发器端的冷凝器端（145）移动 热管（147）。

    Steuerungseinrichtung eines Hubschrauber-Hauptrotors
    13.
    发明公开
    Steuerungseinrichtung eines Hubschrauber-Hauptrotors 有权
    直升飞机主旋翼的控制器

    公开(公告)号：EP1985536A3

    公开(公告)日：2011-01-05

    申请号：EP08154292.0

    申请日：2008-04-10

    申请人： ZF Friedrichshafen AG

    发明人： Wintjen, Carsten ,  Hausberg, André ,  Fürst, Daniel

    IPC分类号： B64C27/605 ,  B64C27/615 ,  B64C27/72

    CPC分类号： B64C27/605 ,  B64C27/615 ,  B64C27/72 ,  B64C2027/7266 ,  Y02T50/34

    摘要： Die Erfindung betrifft zwei Steuerungseinrichtungen eines Hubschrauber-Hauptrotors, bei dem eine erste Steuerungseinrichtung mehrere Rotorblätter (3) an einem Rotorkopf (4) einer Rotorwelle (2) umfangsseitig verteilt angeordnet und um eine Blattlängsachse (5) drehbar oder verwindbar gelagert sind, wobei zur kollektiven Blattwinkelverstellung der Rotorblätter (3) ein im ruhenden System angeordneter und über Stellmittel (9-14) mit den Blattwurzeln (16) der Rotorblätter (3) in Wirkverbindung stehender Kollektivaktuator (7) vorgesehen ist, und zur zyklischen sowie individuellen Blattwinkelverstellung jedem Rotorblatt (3) mindestens ein im rotierenden System angeordneter Individualaktuator (8) zugeordnet ist. Zur Erzielung einer erhöhten Betriebssicherheit und einer verbesserten Steuerbarkeit weist jedes Rotorblatt (3) mindestens eine um eine zur Blattlängsachse (5) parallele oder koaxiale Drehachse (18) schwenkbar gelagerte Rotorblattklappe (19, 22) auf, die mittels eines innerhalb des betreffenden Rotorblattes (3) angeordneten Klappenaktuators (20, 23) auslenkbar ist, wobei die Klappenaktuatoren (20, 23) für die Funktionen des Individualaktuators (8) vorgesehen und entsprechend ausgebildet sind. Die zweite Steuerungseinrichtung weist keinen Kollektivaktuator (7) auf, dafür aber an jedem Rotorblatt (3) einen Blattwurzelaktuator (24) und zumindest einen Klappenaktuator (20, 23).

    ROTORBLATT FÜR EIN DREHFLÜGELFLUGZEUG
    14.
    发明授权
    ROTORBLATT FÜR EIN DREHFLÜGELFLUGZEUG 有权
    ROTORBLATTFÜREINDREHFLÜGELFLUGZEUG

    公开(公告)号：EP1966045B1

    公开(公告)日：2010-08-25

    申请号：EP06829420.6

    申请日：2006-12-08

    申请人： EUROCOPTER DEUTSCHLAND GmbH

    发明人： GROHMANN, Boris ,  MAUCHER, Christoph ,  ALTMIKUS, Andree ,  MANGELSDORF, Stephan

    IPC分类号： B64C27/615 ,  B64C13/50

    CPC分类号： B64C27/615 ,  B64C2027/7283 ,  B64C2027/7288 ,  Y02T50/34

    摘要： A rotor blade (20), especially for a rotary wing aircraft, has an aerodynamically effective rotor blade profile which comprises a profile tip section (21), a profile base (20a) with a profile core (22) and an upper and lower covering skin (30) enclosing the profile core (22), and a profile trailing edge section (23) with a trailing edge (40). A reversibly flexible flection actuator (26) is fastened with a first end to an end section of the profile base (20a) pointing towards the trailing edge (40) and projects with a second end from the profile base (20a) and the end section thereof towards the trailing edge (40). The flection actuator, with the projecting second end, forms a part of the profile trailing edge section (23) of the rotor blade profile and a mobile rotor blade flap (24) which can be deformed to an arched rotor blade flap deflection when the flection actuator (26) is bent.

    摘要翻译： 特别是用于旋翼飞行器的转子叶片（20）具有空气动力学有效的转子叶片轮廓，其包括轮廓末端部分（21），具有轮廓芯部（22）的轮廓基部（20a）以及上部和下部覆盖物 包围型材型芯（22）的蒙皮（30）和具有后缘（40）的型材后缘部分（23）。 可逆地挠曲的挠曲致动器（26）以第一端紧固到型材基部（20a）的指向后缘（40）的端部区段并且与第二端部一起从型材基部（20a）和端部区段 朝向后缘（40）。 具有突出的第二端的挠曲致动器形成转子叶片轮廓的型材后缘部分（23）的一部分和活动转子叶片襟翼（24），当挠曲时该挠性致动器可以变形成拱形转子叶片襟翼 致动器（26）弯曲。

    SELF-LUBRICATED ACTUATOR FOR ON-BLADE ROTOR CONTROL
    16.
    发明公开
    SELF-LUBRICATED ACTUATOR FOR ON-BLADE ROTOR CONTROL 审中-公开
    SELBSTSCHMIERENDER AKTUATORFÜRROTORSTEUERUNG AUF DER LAUFSCHAUFEL

    公开(公告)号：EP2094562A1

    公开(公告)日：2009-09-02

    申请号：EP07875042.9

    申请日：2007-11-12

    申请人： Sikorsky Aircraft Corporation

    发明人： COLLINS, Andrew John ,  CHAUDHRY, Zaffir ,  JONSSON, Ulf J. ,  SUN, Fanping ,  WAKE, Brian E. ,  O'CALLAGHAN, Michael G. ,  YEH, Jimmy Lin-min

    IPC分类号： B64C9/00

    CPC分类号： B64C27/615 ,  B64C2027/7266 ,  Y02T50/34

    摘要： A self-lubricated actuator for a rotor blade flap of a helicopter having a housing; a motor having a shaft disposed in a bearing is provided. The actuator further has an output rod and a mechanism operatively associated with the motor and the output rod to transmit movement from the motor to the output rod. The housing includes a lubrication medium capable of substantially immersing the bearing, the motor shaft and the mechanism during operation.

    摘要翻译： 一种用于具有壳体的直升机的转子叶片瓣的自润滑致动器; 设置有设置在轴承中的轴的电动机。 致动器还具有输出杆和与马达和输出杆可操作地相关联的机构，以将运动从马达传递到输出杆。 壳体包括能够在操作期间基本上浸入轴承，马达轴和机构的润滑介质。

    ROTOR SYSTEM WITH PITCH FLAP COUPLING
    17.
    发明公开
    ROTOR SYSTEM WITH PITCH FLAP COUPLING 有权
    皮瓣及电站转子系统

    公开(公告)号：EP2084055A1

    公开(公告)日：2009-08-05

    申请号：EP07875057.7

    申请日：2007-11-12

    申请人： Sikorsky Aircraft Corporation

    发明人： SCHMALING, David N. ,  CABRERA, Pedro L.

    IPC分类号： B63H1/06

    CPC分类号： B64C27/10 ,  B64C27/32 ,  B64C27/35 ,  B64C27/615 ,  B64C2027/7294 ,  Y02T50/34

    摘要： An articulated rotor system with a servo-flap rotor control system locates the focal point of a blade retention spherical elastomeric bearing inboard of a joint in the servo-flap pitch control tube which separates the flap hinge and supports the servo-flap pitch control tube on a single pivot bearing within a blade retention spindle. Rotor blade flapping produces relative movements between the servo-flap pitch control tube and the blade retention spindle which is converted through a servo-flap drive linkage into servo-flap pitch motions to provide flap/pitch coupling which reduces steady and transient blade flapping.

    FLAP ACTUATOR SYSTEM
    18.
    发明授权
    FLAP ACTUATOR SYSTEM 有权
    襟翼致动器系统

    公开(公告)号：EP1224116B1

    公开(公告)日：2007-09-19

    申请号：EP01934925.7

    申请日：2001-04-27

    申请人： Diversified Technologies, Inc.

    发明人： FINK, David, Allan ,  GAUDREAU, Marcel, Pierre, Joseph ,  CARSON, Stephen, Mark

    IPC分类号： B64C27/615 ,  B64C3/50

    CPC分类号： B64C3/50 ,  B64C27/615 ,  B64C2027/7266 ,  Y02T50/34

    摘要： A flap actuator system for an airfoil structure (10) including a flap member (14a) for controlling the airfoil structure; a bearing member interconnected with the flap member and airfoil structure for rotating the flap member about the axis of the bearing member relative to the airfoil structure and including a field circuit (40) integral with one of the flap member and airfoil structure and an armature circuit (46) integral with the other, the bearing member may be a tension member (26a) which is attached to the airfoil structure at a first point (36) and to the flap member at a second point (32) spaced from the first point.

    FLAP ACTUATOR SYSTEM
    19.
    发明授权
    FLAP ACTUATOR SYSTEM 有权
    襟翼致动器系统

    公开(公告)号：EP1339601B1

    公开(公告)日：2007-01-03

    申请号：EP01999510.9

    申请日：2001-10-15

    申请人： Diversified Technologies, Inc.

    发明人： FINK, David, Allan ,  GAUDREAU, Marcel, Pierre, Joseph

    IPC分类号： B64C3/50 ,  B64C27/615

    CPC分类号： B64C3/50 ,  B64C27/615 ,  B64C2027/7266 ,  Y02T50/34

    摘要： A flap actuator system for an airfoil structure (10) including: a flap member (14a) for controlling the airfoil structure; a bearing member (26a) interconnected with the flap member and the airfoil structure; and an actuator device for rotating the flap member about the bearing member relative to the airfoil structure; the actuator device including an electromagnetic motor segment and a drive mechanism driven by the electromagnetic motor to rotate the flap member about the axis of the bearing member relative to the airfoil structure; the electromagnetic motor being integral with the airfoil structure and the drive mechanism; the electromagnetic motor including a field circuit (40) integral with the drive mechanism and an armature circuit (46) integral with the airfoil structure; the field circuit located within the armature circuit.