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1. 发明申请

WO2016054215A1 SINGLE COLLECTIVE STICK FOR A ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋转式飞机的单集合
公开(公告)号：WO2016054215A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/053229
申请日：2015-09-30
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： BREDENBECK, Kevin L. , FELL, William , ELLER, Erez
IPC分类号： B64C13/50
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 and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A cockpit in the airframe, the cockpit including two seats and a single collective control input positioned between the two seats.
摘要翻译：提供一种飞机，其包括机身，延伸尾翼以及包括上转子组件和下转子组件的反向旋转的同轴主转子组件。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。在机身的驾驶舱，驾驶舱包括两个座位和位于两个座位之间的单个集体控制输入。

2. 发明申请

WO2016054137A1 ELEVATOR AND RUDDER CONTROL OF A ROTORCRAFT 审中-公开
标题翻译：电梯和电梯的控制
公开(公告)号：WO2016054137A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/053091
申请日：2015-09-30
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： ELLER, Erez , LUSZCZ, Matthew T. , EADIE, William J.
IPC分类号： B64C9/06
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 empennage, a counter rotating, coaxial main rotor assembly located at the airframe including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the empennage and providing translational thrust to the airframe. At least two control surfaces located at the empennage are independently operable via commands from one or more flight control computers. A method of operating an aircraft includes transmitting a first signal from one or more flight control computers to a first control surface located at a first lateral side of a translational thrust system, and actuating the first control surface to a first position via the first signal. A second signal is transmitted to a second control surface located at a second lateral side opposite the first lateral side, and the second control surface is actuated to a second position via the second signal
摘要翻译：飞机包括具有尾翼的机身，位于机身处的反转旋转同轴主转子组件，包括上转子组件和下转子组件，以及定位在尾翼处的平移推力系统，并向机身提供平移推力。位于尾翼处的至少两个控制面可以通过来自一个或多个飞行控制计算机的命令独立地操作。一种操作飞行器的方法包括将第一信号从一个或多个飞行控制计算机发送到位于平移推力系统的第一侧面的第一控制表面，以及经由第一信号将第一控制表面驱动到第一位置。第二信号被发送到位于与第一侧面相对的第二横向侧的第二控制表面，并且第二控制表面经由第二信号被致动到第二位置

3. 发明申请

WO2015152910A1 ELEVATOR LOAD ALLEVIATING CONTROL FOR A ROTARY WING AIRCRAFT 审中-公开
标题翻译：电动机负载控制旋转式飞机
公开(公告)号：WO2015152910A1
公开(公告)日：2015-10-08
申请号：PCT/US2014/032638
申请日：2014-04-02
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： ELLER, Erez , GREENFIELD, Aaron L. , WULFF, Ole , WHITE, Matthew A. , LUSZCZ, Matthew T.
IPC分类号： B64C27/00
CPC分类号： B64C13/503 , B64C13/18 , B64C27/08 , B64C27/10 , B64C27/57 , B64C27/82 , B64C2027/8236 , B64C2027/8272 , B64C2027/8281 , Y02T50/44
摘要： One aspect is a flight control system for a rotary wing aircraft including a main rotor system and an elevator control system. A flight control computer of the flight control system includes processing circuitry configured to execute control logic. The control logic includes an inverse plant model that produces a main rotor feed forward command based on a pitch rate command, and a load alleviation control filter configured to reduce loads on a main rotor system and produce an elevator command for an elevator control system. A transformed elevator command filter produces a main rotor pitch adjustment command based on the elevator command, and a main rotor command generator generates an augmented main rotor feed forward command for the main rotor system based on the main rotor feed forward command and the main rotor pitch adjustment command.
摘要翻译：一个方面是用于包括主转子系统和电梯控制系统的旋翼飞机的飞行控制系统。飞行控制系统的飞行控制计算机包括配置成执行控制逻辑的处理电路。控制逻辑包括基于俯仰速率指令产生主转子前馈命令的逆电厂模型，以及负载减轻控制滤波器，其被配置为减少主转子系统上的负载并产生用于电梯控制系统的电梯命令。转换后的升降机指令滤波器基于电梯指令产生主转子桨距调整指令，主转子指令发生器基于主转子前进指令和主转子间距产生主转子系统的增大主转子前馈指令调整指令。

4. 发明申请

WO2015050614A1 HELICOPTER ROTOR LOAD REDUCTION AND TIP CLEARANCE CONTROL 审中-公开
标题翻译：直升机转子负载减少和提升间隙控制
公开(公告)号：WO2015050614A1
公开(公告)日：2015-04-09
申请号：PCT/US2014/046155
申请日：2014-07-10
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： ELLER, Erez , KNAG, John
IPC分类号： B64C27/54 , B64C27/605 , B64C27/72
CPC分类号： B64C27/001 , B64C27/008 , B64C27/10 , B64C2027/002 , B64C2027/7238 , Y02T50/34
摘要： A method of controlling a helicopter having a rotor with blades is provided. The method includes receiving, by a computing device comprising a processor, at least one input associated with the helicopter; generating, by the computing device, control signals configured to counteract blade bending associated with the rotors based on the received at least one input; measuring, by the computing device, blade signals using sensors for the blades; extracting, by the computing device, harmonic loads from the measured blade signals; adapting, by the computing device, the control signals based on the harmonic loads; and controlling, by the computing device, servos connected to the blades to adjust the blades according to the adapted control signals to reduce vibratory loads on the blades.
摘要翻译：提供一种控制具有带叶片的转子的直升机的方法。该方法包括由包括处理器的计算设备接收与直升机相关联的至少一个输入; 由所述计算设备产生控制信号，所述控制信号被配置为基于所接收的至少一个输入来抵消与所述转子相关联的叶片弯曲; 通过计算设备测量使用用于叶片的传感器的叶片信号; 由计算设备从所测量的叶片信号中提取谐波负载; 通过计算装置调整基于谐波负载的控制信号; 以及由所述计算设备控制连接到所述叶片的伺服器，以根据所适配的控制信号调整所述叶片以减少所述叶片上的振动载荷。

5. 发明申请

WO2016060827A3 TRANSLATION THRUST SYSTEM ENGAGEMENT AND DISENGAGMENT FOR ROTARY WING AIRCRAFT 审中-公开
公开(公告)号：WO2016060827A3
公开(公告)日：2016-04-21
申请号：PCT/US2015/052547
申请日：2015-09-28
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： GARCIA, Todd A. , ELLER, Erez , EADIE, William J. , HUNTER, David H.
IPC分类号： B64C27/22
摘要： An aircraft is provided including an airframe, an extending tail, one or more engines supported by the airframe, and 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. A gearbox configured to transfer power from the engine to the main rotor assembly. A flight control computer to independently control one or more of the engine, the upper rotor assembly, the lower rotor assembly, and the translational thrust system. The flight control computer, in response to at least one control command, engages or disengages the translational thrust system, while maintaining controlled powered flight.

6. 发明申请

WO2015156879A2 ROTOR MOMENT FEEDBACK FOR STABILITY AUGMENTATION 审中-公开
标题翻译：转子动力反馈用于稳定性补偿
公开(公告)号：WO2015156879A2
公开(公告)日：2015-10-15
申请号：PCT/US2015/011906
申请日：2015-01-19
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： ELLER, Erez , WULFF, Ole
IPC分类号： B64C19/00 , B64C27/00
CPC分类号： G05D1/0816 , B64C27/32 , B64C27/57 , G05D1/0858
摘要： Embodiments are directed to obtaining at least one measurement of blade bending associated with at least one blade of at least one rotor of an aircraft, processing, by a device comprising a processor, the at least one measurement to obtain moment data, obtaining data from an inertial measurement unit (IMU), and processing, by the device, the moment data and the data from the IMU to generate a command configured to stabilize the aircraft.
摘要翻译：实施例旨在获得与飞机的至少一个转子的至少一个叶片相关联的叶片弯曲的至少一个测量，由包括处理器的装置处理，所述至少一个测量以获得力矩数据，从惯性测量单元（IMU），以及由设备处理来自IMU的力矩数据和数据以产生用于使飞机稳定的命令。

7. 发明申请

WO2005087583A1 GEARBOX MOUNTED FORCE GENERATOR 审中-公开
标题翻译：齿轮安装力发电机
公开(公告)号：WO2005087583A1
公开(公告)日：2005-09-22
申请号：PCT/US2005/008130
申请日：2005-03-10
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： WELSH, William, A. , ELLER, Erez , GOODMAN, Robert, K.
IPC分类号： B63H1/00
CPC分类号： B64C27/14 , B64C27/001
摘要： An active vibration control (AVC) system includes a shaft-driven gearbox mounted force generator (GMFG) mounted to a main rotor transmission. The GMFGs receive shaft power from an output shaft driven by the main rotor transmission and/or engine-to-transmission gearbox to avoid separate drive motors.
摘要翻译：主动振动控制（AVC）系统包括安装在主转子传动装置上的轴驱动变速箱安装力发生器（GMFG）。 GMFG从主转子传动和/或发动机传动齿轮箱驱动的输出轴接收轴功率，以避免单独的驱动电机。

8. 发明申请

WO2016060816A1 STEADY STATE DIFFERENTIAL ROLL MOMENT CONTROL WITH AUTOMATED DIFFERENTIAL LATERAL CONTROL 审中-公开
标题翻译：具有自动差分横向控制的稳态差分滚动控制
公开(公告)号：WO2016060816A1
公开(公告)日：2016-04-21
申请号：PCT/US2015/051914
申请日：2015-09-24
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： FEGELY, Cody , ELLER, Erez , WITTMER, Kenneth S. , GREENFIELD, Aaron L. , KNAG, John
IPC分类号： B64C27/80
CPC分类号： B64C27/80 , B64C27/10 , G05D1/0808 , G05D1/0858
摘要： A method for controlling a differential rotor roll moment for a coaxial helicopter with rigid rotors, the method including receiving, with a processor, a signal indicative of a displacement command from a controller; receiving, with the processor via a sensor, one or more signals indicative of a longitudinal velocity, an angular velocity of one or more rotors and an air density ratio for the helicopter; determining, with the processor, a ganged collective mixing command in response to the receiving of the displacement command; determining, with the processor, a rotor advance ratio as a function of the longitudinal velocity and the angular velocity; and determining, with the processor, a corrective differential lateral cyclic command for the rigid rotors that controls the differential rotor roll moment to a desired value.
摘要翻译：一种用于控制具有刚性转子的同轴直升机的差动转子转矩的方法，所述方法包括：用处理器接收指示来自控制器的位移指令的信号; 通过传感器与处理器接收一个或多个指示纵向速度，一个或多个转子的角速度和直升机的空气密度比的信号; 响应于所述位移命令的接收，与所述处理器确定联合的混合命令; 用处理器确定作为纵向速度和角速度的函数的转子提前比; 以及用所述处理器确定所述刚性转子的校正差分横向循环命令，所述刚性转子将所述差速转子卷轴力矩控制到期望值。

9. 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。

10. 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。

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