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31. 发明申请

WO2016054171A1 ROTOR SPEED MANAGEMENT 审中-公开
标题翻译：转子速度管理
公开(公告)号：WO2016054171A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/053163
申请日：2015-09-30
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： LUSZCZ, Matthew, T. , WEINER, Steven, D. , COTTON, Bryan, S.
IPC分类号： B64C27/57
CPC分类号： B64C27/82 , B64C1/0009 , B64C7/00 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/006 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要： A flight control system for a rotorcraft includes a controller configured to receive input indicative of ambient conditions, determine a threshold rotor blade tip speed based on the input, and to output rotor control commands to prevent rotor blade tips from exceeding the threshold speed. An aircraft includes an airframe, a main rotor assembly operatively connected to the airframe, and a flight control system as described above. The flight control system is operatively connected to control the main rotor assembly. It is contemplated that the main rotor assembly can be a counter rotating coaxial main rotor assembly including an upper rotor assembly with a plurality of blades and a lower rotor assembly having a plurality of blades, wherein the flight control system is operatively connected to control both upper and lower rotor assemblies to prevent any blade tips of the upper and lower rotor assemblies from exceeding the threshold speed.
摘要翻译：用于旋翼航空器的飞行控制系统包括控制器，其被配置为接收指示环境条件的输入，基于输入确定阈值转子叶片尖端速度，并输出转子控制命令以防止转子叶片尖端超过阈值速度。飞机包括机身，可操作地连接到机身的主转子组件和如上所述的飞行控制系统。飞行控制系统可操作地连接以控制主转子组件。可以想到，主转子组件可以是包括具有多个叶片的上转子组件和具有多个叶片的下转子组件的反转旋转同轴主转子组件，其中飞行控制系统可操作地连接以控制上部和下转子组件，以防止上下转子组件的任何叶片尖端超过阈值速度。

32. 发明申请

WO2016054018A2 BLADE INDEXING OF A ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋转飞机的叶片指数
公开(公告)号：WO2016054018A2
公开(公告)日：2016-04-07
申请号：PCT/US2015052907
申请日：2015-09-29
申请人： SIKORSKY AIRCRAFT CORP
发明人： HUNTER DAVID H , CHASEN SCOTT A , CERGE BRANDON MICHAEL , KOESSICK MAXIMILIAN AUGUST , KOSTOSS MICHAEL J , NUSSENBLATT ERIC LUCIEN , THOMAS JUSTIN , BUTLER CHRISTOPHER P
IPC分类号： B64C27/04 , G06F19/00
CPC分类号： B64C27/82 , B64C1/0009 , B64C7/00 , B64C11/48 , B64C11/50 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , B64D2045/0085 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要： An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly with a plurality of blades rotating in a first plane and a lower rotor assembly with a plurality of blades rotating in a second plane, each of the blades having a root end, a midpoint, and a tip end. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. The blades of the upper rotor assembly and the blades of the lower rotor assembly are indexed to improve tip end clearance between pairs of tip ends in the crossing plane as the tip ends move in respective first and second sinusoidal paths.
摘要翻译：提供了一种飞机，其包括机身，延伸尾翼和反向旋转的同轴主转子组件，其包括具有在第一平面中旋转的多个叶片的上转子组件和具有在第二平面中旋转的多个叶片的下转子组件每个叶片具有根端，中点和尖端。位于延伸尾部的平移推力系统，平移推力系统为机身提供平移推力。上转子组件的叶片和下转子组件的叶片被分度以改善当尖端在相应的第一和第二正弦路径中移动时在交叉平面中的成对的尖端之间的尖端间隙。

33. 发明申请

WO2016053774A1 DUAL ROTOR, ROTARY WING AIRCRAFT 审中-公开
标题翻译：双转子，旋转翼飞机
公开(公告)号：WO2016053774A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/052123
申请日：2015-09-25
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： ELLER, Erez , LUSZCZ, Matthew T. , EADIE, William J. , WEINER, Steven D.
IPC分类号： B64C27/22
CPC分类号： B64C27/82 , B64C1/0009 , B64C7/00 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/006 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要： An aircraft is provided including an airframe, an extending tail, a counter-rotating, coaxial main rotor assembly having an upper rotor assembly and a lower rotor assembly, and a translational thrust system including a propeller positioned at the extending tail. The translational thrust system is configured to provide translational thrust to the airframe when the aircraft is in a non-autorotation state and to generate power when in an autorotation state. A gearbox interconnects the propeller and the main rotor assembly to drive the main rotor assembly and the translational thrust system in the non-autorotation state. When the aircraft is in autorotation, the power generated by the propeller drives rotation of the main rotor assembly via the gearbox.
摘要翻译：提供一种飞机，其包括机身，延伸尾翼，具有上转子组件和下转子组件的反向旋转同轴主转子组件，以及包括位于延伸尾部的螺旋桨的平移推力系统。平移推力系统构造成当飞行器处于非自动状态时向机身提供平移推力，并且在处于自动状态时产生动力。齿轮箱将螺旋桨和主转子组件相互连接，以在非自转状态下驱动主转子组件和平移推力系统。当飞机处于自动运转状态时，螺旋桨产生的动力通过变速箱驱动主转子总成的转动。

34. 发明申请

WO2016053740A1 ROTOR HOVER FIGURE OF MERIT FOR ROTARY WING AIRCRAFT 审中-公开
标题翻译：转子盖旋转飞机的梅尔图
公开(公告)号：WO2016053740A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/051901
申请日：2015-09-24
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： EADIE, William J. , EGOLF, Thomas Alan , MOFFITT, Robert C.
IPC分类号： B64C27/10
CPC分类号： B64C27/82 , B64C1/0009 , B64C7/00 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/006 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要： An aircraft composed of an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail. The translational thrust system provides translational thrust to the airframe. The aircraft also includes a rotor hover figure of merit greater than about 0.79 for a C T/σ between about 0.085 and about 0.125.
摘要翻译：由机身，延伸尾翼，反转旋转，同轴主转子组件组成的飞机，其包括上转子组件和下转子组件，以及定位在延伸尾部的平移推力系统。平移推力系统为机身提供平移推力。该飞机还包括转子悬停数值大于约0.79，CT /σ在约0.085至约0.125之间。

35. 发明申请

WO2016053473A1 ACTIVE VIBRATION CONTROL OF A ROTORCRAFT 审中-公开
标题翻译：转子的主动振动控制
公开(公告)号：WO2016053473A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/044005
申请日：2015-08-06
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： WELSH, William, A. , WEINER, Steven, D. , BLACKWELL, Robert, H., Jr.
IPC分类号： B64C27/00 , B64C27/08 , B64C27/10
CPC分类号： B64C27/82 , B64C1/0009 , B64C7/00 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/006 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要： An aircraft includes an airframe having an extending tail, and a counter rotating, coaxial main rotor assembly located at the airframe including an upper rotor assembly and a lower rotor assembly. A translational thrust system is positioned at the extending tail and providing translational thrust to the airframe. An active vibration control (AVC) system is located and the airframe and includes a plurality of AVC actuators configured to generate forces to dampen aircraft component vibration, and an AVC controller configured to transmit control signals to the plurality of AVC actuators thereby triggering force generation by the plurality of AVC actuators. A method of damping vibration of an aircraft includes receiving a vibration signal at an AVC controller, communicating a control signal from the AVC controller to a plurality of AVC actuators, generating a force at the AVC actuators, and damping vibration of the aircraft via the generated force.
摘要翻译：飞机包括具有延伸尾部的机身和位于机身处的反转旋转的同轴主转子组件，包括上转子组件和下转子组件。平移推力系统位于延伸尾部，为机身提供平移推力。主动振动控制（AVC）系统位于机身上并且包括多个AVC致动器，其构造成产生阻尼飞行器部件振动的力，AVC控制器被配置为向多个AVC致动器发送控制信号，从而通过多个AVC致动器。一种阻尼飞行器的振动的方法包括在AVC控制器处接收振动信号，将来自AVC控制器的控制信号传送到多个AVC致动器，在AVC致动器处产生一个力，并通过产生的力。

36. 发明申请

WO2016053452A1 NOISE MODES FOR ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋转式飞机的噪音模式
公开(公告)号：WO2016053452A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/042219
申请日：2015-07-27
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： ELLER, Erez , EADIE, William J. , BREDENBECK, Kevin L. , WEINER, Steven D.
IPC分类号： B64C27/467 , B64D43/00
CPC分类号： B64C27/82 , B64C1/0009 , B64C7/00 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/006 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要： A method of controlling noise of an aircraft includes storing a plurality of predefined noise modes; receiving a selection of a selected noise mode from the plurality of predefined noise modes, the selected noise mode identifying at least one operational parameter; and controlling the aircraft in response to the at least one operational parameter.
摘要翻译：一种控制飞行器噪声的方法包括存储多个预定义的噪声模式; 从所述多个预定噪声模式接收所选择的噪声模式的选择，所选择的噪声模式识别至少一个操作参数; 以及响应于所述至少一个操作参数来控制飞行器。

37. 发明申请

WO2014100655A1 SYSTEM AND METHOD FOR LINKAGE LENGTH ADJUSTMENT 审中-公开
标题翻译：用于连接长度调整的系统和方法
公开(公告)号：WO2014100655A1
公开(公告)日：2014-06-26
申请号：PCT/US2013/077071
申请日：2013-12-20
申请人： BELL HELICOPTER TEXTRON, INC.
发明人： WIINIKKA, Mark A.
IPC分类号： B64C27/51 , F16C7/06
CPC分类号： B64C27/51 , B64C27/008 , B64C27/32 , F16C11/0614
摘要： A rotor system has a rotor (302), an axis of rotation about which the rotor (302) may be rotated, a linkage system (310) having a first adjustable length portion (210) and a second adjustable length portion (212), wherein the second adjustable length portion (212) is configured to provide a relatively finer adjustment of an overall effective length of the linkage system (310) as compared to the first adjustable length portion (210) and wherein the rotor (302) is configured to rotate about the axis in response to changing the overall effective length of the linkage system (310).
摘要翻译：转子系统具有转子（302），转子（302）可以旋转的旋转轴线，具有第一可调节长度部分（210）和第二可调长度部分（212）的连杆系统（310）其中所述第二可调节长度部分（212）被配置为与所述第一可调整长度部分（210）相比提供所述连杆系统（310）的总有效长度的相对更精细的调整，并且其中所述转子（302）被配置为响应于改变连杆系统（310）的总有效长度，围绕轴旋转。

38. 发明申请

WO2013152300A3 MOTION CONTROLLED HELICOPTER AND ROTATION RATE SWITCHED FLUID LEAD LAG DAMPER 审中-公开
标题翻译：运动控制直升机和旋转速率切换流体导管拉杆阻尼器
公开(公告)号：WO2013152300A3
公开(公告)日：2013-12-27
申请号：PCT/US2013035468
申请日：2013-04-05
申请人： LORD CORP , FUHRER ZACHARY , JOLLY MARK , MARR CONOR
发明人： FUHRER ZACHARY , JOLLY MARK , MARR CONOR
IPC分类号： B64C27/51 , F16F9/504
CPC分类号： B64C27/51 , B64C27/32 , F16F9/064 , F16F9/20 , F16F9/504 , F16F13/08 , F16F2230/16
摘要： A method for controlling helicopter ground resonance and air resonance motions as well as centrifugal force switching dampers are disclosed. A helicopter lead-lag damper (30) has a first ground resonance motion damping rate stage (FDR) and a second air resonance motion damping rate stage (SDR). The damper (30) includes a centrifugal force switch (52). The damper (30) is oriented relative to the rotary wing rotation axis (26) and helicopter blade (24). An in-flight rotation rate of the centrifugal force switching damper (30) actuates the centrifugal force switch (52) with the damper switching from the first ground resonance motion damping rate stage (FDR) to the second air resonance motion damping rate stage (SDR).
摘要翻译：公开了一种用于控制直升机地面共振和空气共振运动的方法以及离心力开关阻尼器。直升机牵引滞后阻尼器（30）具有第一接地共振运动阻尼速率级（FDR）和第二空气谐振运动阻尼速率级（SDR）。阻尼器（30）包括离心力开关（52）。阻尼器（30）相对于旋转翼旋转轴线（26）和直升机叶片（24）定向。离心力切换阻尼器30的飞行中旋转速度致动离心力开关52，其中阻尼器从第一接地共振运动阻尼率阶段（FDR）切换到第二空气共振运动阻尼速率级（SDR ）。

39. 发明申请

WO2012075236A1 FREQUENCY-DEPENDENT DAMPER AND ROTARY WING SYSTEM 审中-公开
标题翻译：频率依赖阻尼器和旋转摆动系统
公开(公告)号：WO2012075236A1
公开(公告)日：2012-06-07
申请号：PCT/US2011/062806
申请日：2011-12-01
申请人： LORD CORPORATION , FUHRER, Zachary , JOLLY, Mark
发明人： FUHRER, Zachary , JOLLY, Mark
IPC分类号： B64C27/51 , F16F9/20
CPC分类号： B64C27/51 , F16F1/3814 , F16F1/3835 , F16F1/50 , F16F9/0209 , F16F9/064 , F16F9/20 , F16F9/3415 , F16F9/43 , F16F9/5126 , F16F9/54 , F16F13/16 , F16F2228/04 , Y10T29/494 , Y10T29/49615
摘要： A frequency- dependent damper (10) for creating a damping force in response to a variable - frequency disturbance includes an outer damper body (12) having an internal cavity (16), an inner damper body (14) for receiving the variable - frequency disturbance extending into the internal cavity, a first fluid chamber (46) and a second fluid chamber (48) defined inside the internal cavity, a piston (44) separating the first and second fluid chambers, a selected orifice ( 39 ) for transferring fluid between the first and second fluid chambers, and a selected spring element (54) arranged serially between the piston and the inner damper body such that the piston can move relative to the inner damper body through deformation of the spring element.
摘要翻译：用于响应于可变频率干扰产生阻尼力的频率相关阻尼器（10）包括具有内部空腔（16）的外部阻尼器体（12），用于接收可变频率的内部阻尼器本体（14）干扰延伸到内腔中，限定在内腔内部的第一流体室（46）和第二流体室（48），分隔第一和第二流体室的活塞（44），用于输送流体的选定孔在第一和第二流体室之间，以及选定的弹簧元件（54），其串联地布置在活塞和内部阻尼器主体之间，使得活塞可以通过弹簧元件的变形相对于内部阻尼器主体移动。

40. 发明申请

WO2012019117A2 FLUID ELASTOMERIC DAMPER ASSEMBLY INCLUDING INTERNAL PUMPING MECHANISM AND CONTROL VALVE 审中-公开
标题翻译：流体弹性阻尼器组件，包括内部泵送机构和控制阀
公开(公告)号：WO2012019117A2
公开(公告)日：2012-02-09
申请号：PCT/US2011/046782
申请日：2011-08-05
申请人： LORD CORPORATION , RUSSELL, Donald, D.
发明人： RUSSELL, Donald, D.
IPC分类号： B64C27/51
CPC分类号： B64C27/51 , F16F9/50 , F16F13/28 , F16K15/00 , Y10T137/7837
摘要： A rotary wing system with a rotating blade and a fluid damper with a damper fluid in a first variable volume chamber and a second variable volume chamber, with a fluid damping flow valve controlled conduit and a fluid flow pressure sensing control valve assembly between the first variable volume chamber and the second variable volume chamber. The fluid flow pressure sensing control valve assembly has a fluid flow pressure sensing control valve assembly control valve for obstructing a damper fluid flow through the fluid damping flow valve controlled conduit. A working of the first variable volume chamber and the second variable volume chamber by rotary wing motions actuates the opening of the fluid flow pressure sensing control valve assembly control valve that obstructs the damper fluid flow through the fluid damping flow valve controlled conduit.
摘要翻译：在第一可变容积腔室和第二可变容积腔室中具有旋转叶片和流体阻尼器的旋转翼片系统具有阻尼流体，流体阻尼流量阀控制导管和流体流动压力感测第一可变容积室和第二可变容积室之间的控制阀组件。流体流动压力感测控制阀组件具有流体流动压力感测控制阀组件控制阀，用于阻挡通过流体阻尼流动阀控制导管的阻尼流体流动。第一可变容积腔室和第二可变容积腔室通过旋翼运动的工作致动流体流量压力感测控制阀组件控制阀的打开，该流体流量压力感测控制阀组件控制阀阻碍阻尼器流体流过流体阻尼流量阀控制管道。

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