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1. 发明授权

US10562641B2 AFT exhaust system for rotary wing aircraft 有权
公开(公告)号：US10562641B2
公开(公告)日：2020-02-18
申请号：US14049735
申请日：2013-10-09
申请人： Sikorsky Aircraft Corporation
发明人： Joseph Pantalone, III , Ashley DeVito , John S. Chapkovich, III , Steven D. Weiner
IPC分类号： F02K1/82 , B64D33/04 , F02K1/40 , B64C27/04 , F02C7/00 , F02K3/072 , B64C27/10 , B64C27/82
摘要： An exhaust system for reducing infrared emissions of a rotary wing aircraft includes a duct assembly having an inlet portion and an outlet portion; the inlet portion configured to receive exhaust from an engine of the aircraft; and the outlet portion coupled to the inlet portion, the outlet portion having an outlet duct with an outlet opening, the outlet duct configured expel an emission containing engine exhaust proximate to a tail fairing of the rotary wing aircraft.

2. 发明申请

US20170297694A1 ROTOR SPEED MANAGEMENT 审中-公开
公开(公告)号：US20170297694A1
公开(公告)日：2017-10-19
申请号：US15516271
申请日：2015-09-30
申请人： Sikorsky Aircraft Corporation
发明人： Matthew T. Luszcz , Steven D. Weiner , Bryan S. Cotton
IPC分类号： B64C27/57 , B64C27/10 , F02C9/28 , G05D1/02
CPC分类号： F16F15/02 , B64C13/04 , B64C13/50 , B64C27/001 , B64C27/006 , B64C27/10 , B64C27/14 , B64C27/467 , B64C27/57 , B64C2027/004 , B64C2027/8236 , B64D35/06 , G05D1/0816 , G05D1/0858
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.

3. 发明申请

US20170297690A1 HUB SEPARATION IN DUAL ROTOR ROTARY WING AIRCRAFT 审中-公开
公开(公告)号：US20170297690A1
公开(公告)日：2017-10-19
申请号：US15509741
申请日：2015-09-28
申请人： Sikorsky Aircraft Corporation
发明人： Steven D. Weiner , Mikel Brigley , David H. Hunter
IPC分类号： B64C27/32 , B64C27/82 , B64C27/10
摘要： An aircraft includes 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 providing translational thrust to the airframe; wherein a ratio of (i) the hub separation between the hub of the upper rotor assembly and the hub of the lower rotor assembly to (ii) a radius of the upper rotor assembly is between about 0.1 and about 0.135.

4. 发明申请

US20170217575A1 ACTIVE VIBRATION CONTROL OF A ROTORCRAFT 审中-公开
公开(公告)号：US20170217575A1
公开(公告)日：2017-08-03
申请号：US15515040
申请日：2015-08-06
申请人： Sikorsky Aircraft Corporation
发明人： William A. Welsh , Steven D. Weiner , Robert H. Blackwell, JR.
IPC分类号： B64C27/10 , B64C27/32
CPC分类号： F16F15/02 , B64C13/04 , B64C13/50 , B64C27/001 , B64C27/006 , B64C27/10 , B64C27/14 , B64C27/467 , B64C27/57 , B64C2027/004 , B64C2027/8236 , B64D35/06 , G05D1/0816 , G05D1/0858
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.

5. 发明授权

US10167079B2 Main rotor rotational speed control for rotorcraft 有权
公开(公告)号：US10167079B2
公开(公告)日：2019-01-01
申请号：US15508346
申请日：2015-09-29
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： Steven D. Weiner , William J. Eadie
IPC分类号： G05D1/00 , B64C27/82 , B64C27/10 , B64C27/12 , B64C27/14 , B64C13/04 , B64C13/18 , G05D1/08 , B64C13/50 , B64C27/57 , G05D1/02 , B64C27/00 , B64D39/00 , B64D39/06 , B64C27/80 , B64D35/06 , F16H37/02 , B64C27/51 , B64C27/52 , B64C27/32 , B64C27/33 , B64C27/473 , B64C27/48 , B64C27/16 , B64C1/00 , B64C19/00 , B64C27/54 , B64C27/78 , B64C27/467 , B64C7/00 , B64D45/02 , F16D13/52 , F16D13/72 , F16D13/74 , B64C27/08 , G06F19/00 , F02C9/28
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 flight control computer is configured to control a main rotor rotational speed of the upper and the lower rotor assemblies of the main rotor assembly as a function of airspeed of the aircraft. A method of operating an aircraft includes retrieving a threshold main rotor rotational speed of the dual coaxial main rotor assembly and calculating an actual main rotor rotational speed according to an environment of the aircraft. The actual main rotor rotational speed is maintained to remain at or below the threshold main rotor speed according to an airspeed of the aircraft.

6. 发明申请

US20170283047A1 MAIN ROTOR ROTATIONAL SPEED CONTROL FOR ROTORCRAFT 审中-公开
公开(公告)号：US20170283047A1
公开(公告)日：2017-10-05
申请号：US15508346
申请日：2015-09-29
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： Steven D. Weiner , William J. Eadie
IPC分类号： B64C27/14 , B64C27/10
CPC分类号： F16F15/02 , 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 , B64C27/82 , 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 flight control computer is configured to control a main rotor rotational speed of the upper and the lower rotor assemblies of the main rotor assembly as a function of airspeed of the aircraft. A method of operating an aircraft includes retrieving a threshold main rotor rotational speed of the dual coaxial main rotor assembly and calculating an actual main rotor rotational speed according to an environment of the aircraft. The actual main rotor rotational speed is maintained to remain at or below the threshold main rotor speed according to an airspeed of the aircraft.

7. 发明申请

US20170225797A1 AIRCRAFT DESIGN FOR AIR TO AIR REFUELING 审中-公开
公开(公告)号：US20170225797A1
公开(公告)日：2017-08-10
申请号：US15503599
申请日：2015-07-01
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： Kevin L. Bredenbeck , William Fell , Steven D. Weiner
IPC分类号： B64D39/06 , B64C27/82 , B64C27/10
CPC分类号： F16F15/02 , B64C13/04 , B64C13/50 , B64C27/001 , B64C27/006 , B64C27/10 , B64C27/14 , B64C27/467 , B64C27/57 , B64C2027/004 , B64C2027/8236 , B64D35/06 , G05D1/0816 , G05D1/0858
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. The upper rotor assembly and the lower rotor assembly each include a plurality of blades. A translational thrust system is positioned at the extending tail and provides translational thrust to the airframe. The plurality of blades of the main rotor assembly extend beyond a nose of the aircraft by about 13 inches.

8. 发明申请

US20140314563A1 VIBRATION CONTROL OF A SWASHPLATELESS COAXIAL ROTOR 审中-公开
标题翻译：无刷同轴转子的振动控制
公开(公告)号：US20140314563A1
公开(公告)日：2014-10-23
申请号：US13867402
申请日：2013-04-22
申请人： Sikorsky Aircraft Corporation
发明人： Bryan D. Mayrides , William A. Welsh , Steven D. Weiner
IPC分类号： B64C27/12
CPC分类号： B64C27/72 , B64C27/001 , B64C27/10 , B64C2027/004 , B64C2027/7216 , B64C2027/7244 , Y02T50/34
摘要： A rotary wing aircraft is provided including a dual counter-rotating, coaxial rotor system having an upper rotor system and a lower rotor system rotatable about a common axis. A plurality of blade assemblies is mounted to a portion of either the upper rotor system or the lower rotor system. A plurality of individually controllable actuators is coupled to each of the plurality of blade assemblies. Each of the plurality of actuators is configured to control movement of the coupled blade assembly about a pitch axis. The rotary-wing aircraft additionally includes a sensor system within an airframe. A higher harmonic control (HHC) controller is arranged in communication with the sensor system and the plurality of actuators to individually control the upper rotor system and the lower rotor system to reduce vibration.
摘要翻译：提供了一种旋转翼飞行器，其包括具有上转子系统和可围绕公共轴线旋转的下转子系统的双反向旋转同轴转子系统。多个叶片组件安装到上转子系统或下转子系统的一部分。多个可独立控制的致动器联接到多个叶片组件中的每一个。多个致动器中的每一个构造成控制联接的叶片组件围绕俯仰轴线的运动。旋转翼飞机另外包括机身内的传感器系统。高次谐波控制器（HHC）控制器被布置成与传感器系统和多个致动器连通，以分别控制上转子系统和下转子系统以减少振动。

9. 发明授权

US10717521B2 Hub separation in dual rotor rotary wing aircraft 有权
公开(公告)号：US10717521B2
公开(公告)日：2020-07-21
申请号：US15509741
申请日：2015-09-28
申请人： Sikorsky Aircraft Corporation
发明人： Steven D. Weiner , Mikel Brigley , David H. Hunter
IPC分类号： B64C27/10 , F16F15/02 , B64C27/00 , B64C27/14 , B64C1/00 , B64C7/00 , B64C13/18 , B64C13/50 , B64C19/00 , B64C27/12 , B64C27/16 , B64C27/32 , B64C27/33 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/78 , B64C27/80 , B64C27/82 , B64D39/00 , B64D39/06 , B64D45/02 , F16H37/02 , G05D1/00 , G05D1/02 , B64C13/04 , G05D1/08 , B64C27/57 , B64D35/06 , B64C27/467 , B64C27/08 , F02C9/28 , F16D13/52 , F16D13/72 , F16D13/74
摘要： An aircraft includes 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 providing translational thrust to the airframe; wherein a ratio of (i) the hub separation between the hub of the upper rotor assembly and the hub of the lower rotor assembly to (ii) a radius of the upper rotor assembly is between about 0.1 and about 0.135.

10. 发明授权

US10086935B2 Guide vanes for a pusher propeller for rotary wing aircraft 有权
公开(公告)号：US10086935B2
公开(公告)日：2018-10-02
申请号：US14963859
申请日：2015-12-09
申请人： Sikorsky Aircraft Corporation
发明人： Colman D. Shattuck , Peter F. Lorber , Blake Almy Moffitt , Peter J. Germanowski , Brian E. Wake , Steven D. Weiner
IPC分类号： B64C27/82 , B64C23/06 , B64C27/473
摘要： A propulsor system for a rotary winged aircraft includes a propeller including having a propeller hub rotatable about a propeller axis and a plurality of propeller blades secured to and extending radially outwardly from the propeller hub. The propeller is oriented on the rotary winged aircraft to provide forward thrust for the rotary winged aircraft when the propeller is rotated about the propeller hub. A plurality of guide vanes non rotatable about the propeller axis are positioned upstream of the plurality of propeller blades. The plurality of guide vanes are positioned to turn an airflow flowing into the plurality or propeller blades, thereby reducing an angle of attack of the plurality of propeller blades relative to the airflow.

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