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1. 发明申请

WO2016053825A1 ROTORCRAFT SYSTEMS TO REDUCE PILOT WORKLOAD 审中-公开
标题翻译： ROTORCRAFT系统减少引航工作量
公开(公告)号：WO2016053825A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/052549
申请日：2015-09-28
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： BREDENBECK, Kevin L. , WEINER, Steven D. , WALSH, David M. , COTTON, Bryan S. , ARIFIAN, Kenneth C.
IPC分类号： G06D1/00
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： An aircraft includes an airframe having an extending tail, a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail and providing translational thrust to the airframe. A fly by wire control system for the aircraft includes a flight control system configured to receive a plurality of inputs and a flight control computer to translate the inputs into commands and issue the commands to one or more controlled elements of the aircraft. A fly by wire control system for a dual coaxial rotor rotorcraft with auxiliary propulsor includes a flight control system configured to receive a plurality of inputs and a flight control computer to translate the inputs into commands and issue the commands to one or more controlled elements of the rotorcraft.
摘要翻译：飞机包括具有延伸尾部的机身，设置在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，以及定位在延伸尾部的平移推力系统，并向机身提供平移推力。用于飞行器的线控系统的飞行包括配置成接收多个输入的飞行控制系统和飞行控制计算机，以将输入转换为命令并向飞机的一个或多个受控元件发出命令。用于具有辅助推进器的双同轴转子旋翼飞机的线控制系统的飞行包括配置成接收多个输入的飞行控制系统和飞行控制计算机，以将输入转换为命令并将命令发布到旋翼机。

2. 发明申请

WO2016043943A2 PITCH CONTROL SYSTEM 审中-公开
标题翻译：间距控制系统
公开(公告)号：WO2016043943A2
公开(公告)日：2016-03-24
申请号：PCT/US2015/047156
申请日：2015-08-27
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： BREDENBECK, Kevin L. , COTTON, Bryan S. , WILSON, Mark K.
IPC分类号： B64C27/16 , G06F19/00
CPC分类号： B64C27/57 , B64C11/30 , B64C11/305 , B64C11/34 , B64C11/40 , B64C27/56 , B64C27/82 , B64C2027/8236
摘要： A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.
摘要翻译：提供了一种变桨控制系统，该变桨控制系统构造成改变螺旋桨系统的多个螺旋桨叶片中的至少一个的螺旋角，该变桨控制系统包括能够在空档位置和多个非空档位置之间移动的开关。开关移动到第一非中立位置产生命令以沿第一方向移动螺旋桨叶片。开关移动到第二非中立位置产生命令以沿第二方向移动螺旋桨叶片。开关移动到第三个非中立位置会产生一个指令，将螺旋桨叶片移动到零推力位置。

3. 发明申请

WO2016054220A2 LIFT OFFSET CONTROL OF A ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋翼式飞机的升降失调控制
公开(公告)号：WO2016054220A2
公开(公告)日：2016-04-07
申请号：PCT/US2015/053235
申请日：2015-09-30
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： ELLER, Erez , LUSZCZ, Matthew T. , ARIFIAN, Kenneth C. , BREDENBECK, Kevin L. , COTTON, Bryan S.
IPC分类号： B64C27/04
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, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly composed of a plurality of blades and a lower rotor assembly composed of a plurality of blades. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A flight control system to control the upper rotor assembly and the lower rotor assembly, wherein the flight control system is configured to control lift offset of the upper rotor assembly and the lower rotor assembly.
摘要翻译：提供了一种飞行器，其包括机身，延伸尾部以及反转同轴主转子组件，所述同轴主转子组件包括由多个叶片组成的上转子组件和由多个刀片。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。一种用于控制上转子组件和下转子组件的飞行控制系统，其中飞行控制系统构造成控制上转子组件和下转子组件的升力偏移。

4. 发明申请

WO2016053991A1 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：WO2016053991A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/052864
申请日：2015-09-29
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： BREDENBECK, Kevin L. , COTTON, Bryan S. , ARIFIAN, Kenneth C. , ELLER, Erez , LUSZCZ, Matthew T.
IPC分类号： B64C27/82
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 and includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions.
摘要翻译：提供了一种飞机，包括一个机身，一个延伸的尾巴，一个反向旋转的，同轴的主转子组件，它包括一个上部转子组件和一个下部转子组件，平移推力系统位于延伸尾部，平移推力系统提供平移推力机身，至少一个传感器和至少一个惯性测量单元（IMU），用于感测飞行器的当前飞行状况，根据控制命令执行主转子组件的控制的接口和至少一个飞行控制计算机（FCC ）发出控制命令。所述至少一个FCC包括中央处理单元（CPU）和存储有其上的逻辑和可执行指令的存储器，其在执行时使CPU根据当前飞行条件和执行结果发出控制命令当前航班条件的逻辑。

5. 发明申请

WO2015108954A1 TIP CLEARANCE MEASUREMENT 审中-公开
标题翻译：提示间隙测量
公开(公告)号：WO2015108954A1
公开(公告)日：2015-07-23
申请号：PCT/US2015/011376
申请日：2015-01-14
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： COTTON, Bryan S.
IPC分类号： B64C27/08
CPC分类号： G01B11/14 , B64C27/008 , B64C27/10
摘要： An aircraft is provided and includes an airframe, first and second main rotors rotatably supported on the airframe to rotate about a rotational axis in opposite directions, first and second emitters disposed on an emitter blade of the second main rotor, each of the first and second emitters being configured to emit an emission toward a detector blade of the first main rotor, a detector disposed on the detector blade of the first main rotor, the detector being configured to detect the emissions of the first and second emitters and a flight computer which determines a clearance between the first and second main rotors in accordance with detections of the emissions by the detector.
摘要翻译：提供飞机并且包括机身，可旋转地支撑在机身上以相反方向围绕旋转轴线旋转的第一和第二主转子，设置在第二主转子的发射器叶片上的第一和第二发射器，第一和第二发射器被配置为朝向第一主转子的检测器叶片发射发射，设置在第一主转子的检测器叶片上的检测器，检测器被配置为检测第一和第二发射器的发射，以及飞行计算机，其确定根据检测器的发射的检测，第一和第二主转子之间的间隙。

6. 发明申请

WO2008147451A2 TRANSLATIONAL THRUST SYSTEM FOR A ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋转式飞机翻转系统
公开(公告)号：WO2008147451A2
公开(公告)日：2008-12-04
申请号：PCT/US2007/084397
申请日：2007-11-12
申请人： SIKORSKY AIRCRAFT CORPORATION , COTTON, Bryan S. , ARIFIAN, Kenneth C. , SCHWEIZER, Leslie , CEVETTE, Jeffrey L.
发明人： COTTON, Bryan S. , ARIFIAN, Kenneth C. , SCHWEIZER, Leslie , CEVETTE, Jeffrey L.
IPC分类号： B64C27/22 , B64C27/12 , B64C11/38
CPC分类号： B64C27/10 , B64C11/38 , B64C27/14 , B64C2027/8236 , B64C2027/8254
摘要： A translational thrust system for a high speed rotary-wing aircraft includes a propeller system driven by a propeller gearbox, a hydraulic system, and a mechanical-hydraulic control system. The mechanical-hydraulic control system utilizes a hydraulic fluid which travels to and from a propeller dome via an oil transfer/position feedback tube which translates with a propeller pitch change piston. Translation of the oil transfer/position feedback tube and the propeller pitch change piston pitches the blades between high (coarse) and low (fine) pitch positions.
摘要翻译：用于高速旋翼飞机的平移推力系统包括由螺旋桨变速箱，液压系统和机械液压控制系统驱动的螺旋桨系统。机械液压控制系统利用一个液压流体，该液压流体经由与螺旋桨变桨活塞平移的油传递/位置反馈管行进和往返于螺旋桨穹顶。油传递/位置反馈管和螺旋桨螺距改变活塞的转换在高（粗）和低（精细）间距位置之间调节叶片。

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