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1. 发明公开

EP2719619A3 Rotary wing aircraft having collocated exhaust duct and propeller shaft 有权
标题翻译：配有排气管和螺旋桨轴的旋翼飞机
公开(公告)号：EP2719619A3
公开(公告)日：2017-09-27
申请号：EP13187930.6
申请日：2013-10-09
申请人： Sikorsky Aircraft Corporation
发明人： Pantalone III, Joseph , Chapkovich III, John S. , DeVito, Ashley , Eller, Erez
IPC分类号： B64C27/08 , B64C27/12 , B64D33/04 , B64C27/10 , B64C27/14 , B64D35/00 , B64C27/82
摘要： An exhaust system for reducing infrared emissions of a rotary wing aircraft includes an exhaust duct (106) having a fore end for connection with an aft turbine section of an engine of the rotary wing aircraft, the exhaust duct having an aft end having an exhaust opening (108) to expel engine exhaust proximate to a tail fairing (33) of the rotary wing aircraft; and a drive shaft (104) collocated with the exhaust duct, the drive shaft configured to provide rotational force to an aft propeller of the rotary wing aircraft.
摘要翻译：一种用于降低旋翼飞机的红外发射的排气系统包括排气管（106），该排气管具有用于与旋翼飞机的发动机的后涡轮部分连接的前端，排气管的后端具有排气口（108）在靠近所述旋翼飞行器的尾翼（33）的地方排出发动机排气; 和与所述排气管道配置的驱动轴（104），所述驱动轴构造成向所述旋翼飞行器的后螺旋桨提供旋转力。

2. 发明公开

EP2476614A3 Moment limiting control laws for dual rigid rotor helicopters 有权
标题翻译：双刚性旋翼直升机的力矩限制控制法则
公开(公告)号：EP2476614A3
公开(公告)日：2017-07-26
申请号：EP12151142.2
申请日：2012-01-13
申请人： Sikorsky Aircraft Corporation
发明人： Eller, Erez , Knag, John
IPC分类号： B64C27/10 , B64C27/04
CPC分类号： B64C27/10 , B64C27/04
摘要： A method of counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter (10) includes sensing angular velocity and angular acceleration of a helicopter during a flight maneuver. The angular velocity and angular acceleration are compared to a set of control parameters and one or more control servos change the cyclic pitch of the one or more rotors (12a,12b) to counteract the rotor moment. A control system for counteracting a rotor moment of one or more rotors (12a,12b) of a concentric dual-rotor helicopter (10) includes one or more sensors configured to sense angular velocity and angular acceleration of a helicopter during a flight maneuver. A computer (42) is operably connected to the one or more sensors (44) and configured to compare sensor data to a set of control parameters. A plurality of control servos change the cyclic pitch of the one or more rotors (12a,12b) to counteract the rotor moment.
摘要翻译：一种抵消同心双转子直升机（10）的一个或多个转子的转子力矩的方法包括在飞行机动过程中感测直升机的角速度和角加速度。将角速度和角加速度与一组控制参数进行比较，并且一个或多个控制伺服系统改变一个或多个转子（12a，12b）的循环间距以抵消转子力矩。用于抵消同心双旋翼直升机（10）的一个或多个转子（12a，12b）的转子力矩的控制系统包括一个或多个传感器，其配置为感测飞行机动期间直升机的角速度和角加速度。计算机（42）可操作地连接到一个或多个传感器（44）并且被配置为将传感器数据与一组控制参数进行比较。多个控制伺服机构改变一个或多个转子（12a，12b）的周期性间距以抵消转子力矩。

3. 发明公开

EP2829471A1 Swashplateless coaxial rotary wing aircraft 有权
标题翻译： TaumelscheibenfreiesKoaxialdrehflügelflugzeug
公开(公告)号：EP2829471A1
公开(公告)日：2015-01-28
申请号：EP14177865.4
申请日：2014-07-21
申请人： Sikorsky Aircraft Corporation
发明人： Eller, Erez , Weiner, Steven D. , Bourne, Frederick L.
IPC分类号： B64C27/10 , B64C27/72 , B64C27/32 , B64C27/12 , B64C27/82
CPC分类号： B64C27/80 , B64C27/10 , B64C27/12 , B64C27/32 , B64C27/72 , B64C2027/7216 , B64C2027/8236 , H02K99/10 , Y02T50/34
摘要： A main rotor system 12 of an aircraft 10 is provided including a first rotor 16 coupled to a transmission 25 and configured to rotate about an axis R in a first direction. A second rotor 18 is similarly coupled to the transmission 25 and is configured to rotate about the axis R in a second direction. At least the first rotor 16 includes an individual blade control system (IBCS) 50 configured to adjust a pitch of each of a plurality of blade 54 of the first rotor 16 independently. At least one slip ring 60 is configured to transmit electrical power and/or a control signal to the at least one IBCS 50.
摘要翻译：提供飞行器10的主转子系统12，其包括联接到变速器25的第一转子16并且构造成围绕第一方向的轴线R旋转。类似地，第二转子18耦合到变速器25，并被构造成在第二方向围绕轴线R旋转。至少第一转子16包括单独的叶片控制系统（IBCS）50，其被配置成独立地调节第一转子16的多个叶片54中的每一个的间距。至少一个滑环60被配置为将电功率和/或控制信号传送到至少一个IBCS 50。

4. 发明公开

EP2476614A2 Moment limiting control laws for dual rigid rotor helicopters 有权
标题翻译： MomentenbegrenzungssteuerungsgesetzefürHubschrauber mit zwei starren Rotoren
公开(公告)号：EP2476614A2
公开(公告)日：2012-07-18
申请号：EP12151142.2
申请日：2012-01-13
申请人： Sikorsky Aircraft Corporation
发明人： Eller, Erez , Knag, John
IPC分类号： B64C27/10 , B64C27/04
CPC分类号： B64C27/10 , B64C27/04
摘要： A method of counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter (10) includes sensing angular velocity and angular acceleration of a helicopter during a flight maneuver. The angular velocity and angular acceleration are compared to a set of control parameters and one or more control servos change the cyclic pitch of the one or more rotors (12a,12b) to counteract the rotor moment. A control system for counteracting a rotor moment of one or more rotors (12a,12b) of a concentric dual-rotor helicopter (10) includes one or more sensors configured to sense angular velocity and angular acceleration of a helicopter during a flight maneuver. A computer (42) is operably connected to the one or more sensors (44) and configured to compare sensor data to a set of control parameters. A plurality of control servos change the cyclic pitch of the one or more rotors (12a,12b) to counteract the rotor moment.
摘要翻译：一种抵消同心双转子直升机（10）的一个或多个转子的转子力矩的方法包括在飞行操纵期间感测直升机的角速度和角加速度。将角速度和角加速度与一组控制参数进行比较，并且一个或多个控制伺服器改变一个或多个转子（12a，12b）的循环间距以抵消转子力矩。用于抵消同心双转子直升机（10）的一个或多个转子（12a，12b）的转子力矩的控制系统包括一个或多个传感器，其构造成在飞行操纵期间感测直升机的角速度和角加速度。计算机（42）可操作地连接到一个或多个传感器（44）并且被配置为将传感器数据与一组控制参数进行比较。多个控制伺服机构改变一个或多个转子（12a，12b）的循环间距以抵消转子力矩。

5. 发明授权

EP2476614B1 Moment limiting control laws for dual rigid rotor helicopters 有权
公开(公告)号：EP2476614B1
公开(公告)日：2018-08-22
申请号：EP12151142.2
申请日：2012-01-13
申请人： Sikorsky Aircraft Corporation
发明人： Eller, Erez , Knag, John
IPC分类号： B64C27/10 , B64C27/04
CPC分类号： B64C27/10 , B64C27/04
摘要： A method of counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter (10) includes sensing angular velocity and angular acceleration of a helicopter during a flight maneuver. The angular velocity and angular acceleration are compared to a set of control parameters and one or more control servos change the cyclic pitch of the one or more rotors (12a,12b) to counteract the rotor moment. A control system for counteracting a rotor moment of one or more rotors (12a,12b) of a concentric dual-rotor helicopter (10) includes one or more sensors configured to sense angular velocity and angular acceleration of a helicopter during a flight maneuver. A computer (42) is operably connected to the one or more sensors (44) and configured to compare sensor data to a set of control parameters. A plurality of control servos change the cyclic pitch of the one or more rotors (12a,12b) to counteract the rotor moment.

6. 发明公开

EP2333726A1 Virtual monitoring of aircraft fleet loads 失效
标题翻译： VirtuelleÜberwachungfürLuftfahrzeugbelastungen
公开(公告)号：EP2333726A1
公开(公告)日：2011-06-15
申请号：EP10251921.2
申请日：2010-11-12
申请人： Sikorsky Aircraft Corporation
发明人： Isom, Joshua D. , Cycon, James P. , Eller, Erez , Davis, Mark W.
IPC分类号： G07C5/00 , G07C5/08
CPC分类号： G07C5/006 , G05B23/024 , G05B23/0283 , G06Q10/06311 , G07C5/008 , G07C5/0841
摘要： A computer-implemented method, system, and computer program product for virtual monitoring of aircraft fleet loads are provided. The method includes calculating virtual load data associated with an aircraft from a set of orthogonal waveforms. The method also includes calculating a set of coefficients as a function of parametric data and high frequency data associated with an aircraft. The method further includes storing the set of coefficients on the aircraft and transmitting the set of coefficients to a ground-based system configured to reproduce the virtual load data based on a copy of the set of orthogonal waveforms and the received set of coefficients in order to perform aircraft fleet management.
摘要翻译：提供了一种用于虚拟监控飞机机队负载的计算机实现的方法，系统和计算机程序产品。该方法包括从一组正交波形计算与飞机相关联的虚拟载荷数据。该方法还包括根据与飞机相关联的参数数据和高频数据来计算一组系数。该方法还包括将该系数集合存储在飞行器上并且将该系数集合发射到基于地面的系统，该地面系统被配置为基于该组正交波形和所接收的一组系数的副本再现虚拟负载数据，以便执行飞机机队管理。

7. 发明授权

EP2719619B1 Rotary wing aircraft having collocated exhaust duct and propeller shaft 有权
公开(公告)号：EP2719619B1
公开(公告)日：2020-01-01
申请号：EP13187930.6
申请日：2013-10-09
申请人： Sikorsky Aircraft Corporation
发明人： Pantalone III, Joseph , Chapkovich III, John S. , DeVito, Ashley , Eller, Erez
IPC分类号： B64C27/08 , B64C27/12 , B64D33/04 , B64C27/10 , B64C27/14 , B64D35/00 , B64C27/82

8. 发明授权

EP2333726B1 Virtual monitoring of aircraft fleet loads 失效
标题翻译：飞机机队负载的虚拟监控
公开(公告)号：EP2333726B1
公开(公告)日：2017-05-10
申请号：EP10251921.2
申请日：2010-11-12
申请人： Sikorsky Aircraft Corporation
发明人： Isom, Joshua D. , Cycon, James P. , Eller, Erez , Davis, Mark W.
IPC分类号： G05B23/02 , G06Q10/06 , G07C5/00 , G07C5/08
CPC分类号： G07C5/006 , G05B23/024 , G05B23/0283 , G06Q10/06311 , G07C5/008 , G07C5/0841

9. 发明授权

EP2829471B1 Swashplateless coaxial rotary wing aircraft 有权
标题翻译：无斜盘同轴旋翼飞机
公开(公告)号：EP2829471B1
公开(公告)日：2017-02-15
申请号：EP14177865.4
申请日：2014-07-21
申请人： Sikorsky Aircraft Corporation
发明人： Eller, Erez , Weiner, Steven D. , Bourne, Frederick L.
IPC分类号： B64C27/10 , B64C27/72 , B64C27/32 , B64C27/12 , B64C27/82
CPC分类号： B64C27/80 , B64C27/10 , B64C27/12 , B64C27/32 , B64C27/72 , B64C2027/7216 , B64C2027/8236 , H02K99/10 , Y02T50/34

10. 发明公开

EP2719619A2 Rotary wing aircraft having collocated exhaust duct and propeller shaft 有权
标题翻译： Drehflügelflugzeugmit ineinanderangeordnetem Abgaskanal und Propellerwelle
公开(公告)号：EP2719619A2
公开(公告)日：2014-04-16
申请号：EP13187930.6
申请日：2013-10-09
申请人： Sikorsky Aircraft Corporation
发明人： Pantalone III, Joseph , Chapkovich III, John S. , DeVito, Ashley , Eller, Erez
IPC分类号： B64C27/08 , B64C27/12 , B64D33/04 , B64C27/82
摘要： An exhaust system for reducing infrared emissions of a rotary wing aircraft includes an exhaust duct (106) having a fore end for connection with an aft turbine section of an engine of the rotary wing aircraft, the exhaust duct having an aft end having an exhaust opening (108) to expel engine exhaust proximate to a tail fairing (33) of the rotary wing aircraft; and a drive shaft (104) collocated with the exhaust duct, the drive shaft configured to provide rotational force to an aft propeller of the rotary wing aircraft.
摘要翻译：用于减少旋转翼飞行器的红外发射的排气系统包括排气管道（106），其具有用于与旋转翼飞行器的发动机的后涡轮部分连接的前端，排气管道具有尾端，其具有排气口（108）以排出靠近所述旋翼飞机的尾翼整流罩（33）的发动机排气; 以及与所述排气管道配置的驱动轴（104），所述驱动轴构造成向所述旋转翼飞行器的后部螺旋桨提供旋转力。

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