专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

WO2008147462A3 HYBRID ACTUATOR FOR HELICOPTER ROTOR BLADE CONTROL FLAPS 审中-公开
标题翻译：用于直升机转子叶片控制板的混合动作器
公开(公告)号：WO2008147462A3
公开(公告)日：2009-03-26
申请号：PCT/US2007086585
申请日：2007-12-06
申请人： SIKORSKY AIRCRAFT CORP , SUN FANPING , CHAUDHRY ZAFFIR A , YEH JIMMY LIH-MIN , O'CALLAGHAN MICHAEL G , JONSSON ULF J , WAKE BRIAN E , DOLD ROBERT H
发明人： SUN FANPING , CHAUDHRY ZAFFIR A , YEH JIMMY LIH-MIN , O'CALLAGHAN MICHAEL G , JONSSON ULF J , WAKE BRIAN E , DOLD ROBERT H
IPC分类号： B64C27/46
CPC分类号： B64C27/615 , B64C2027/7294 , Y02T50/34
摘要： A helicopter rotor blade that has a blade body and a control flap secured to the blade body. The rotor blade has a first primary mover capable of generating a first linear motion that is sufficient to generate a high amplitude, low frequency motion of the control flap; and a second primary mover capable of generating a second linear motion that is sufficient to generate a small amplitude, high frequency motion of the control flap. Further, the rotor blade has a coupling transmission for combining the first linear motion with the second linear motion that generates a cumulative linear motion; and a small transmission device that causes the cumulative linear motion to rotate the control flap.
摘要翻译：一种直升机转子叶片，其具有固定到叶片本体的叶片体和控制翼。转子叶片具有能够产生足以产生控制翼片的高振幅，低频运动的第一线性运动的第一原动机; 以及能够产生足以产生控制翼片的小振幅，高频运动的第二线性运动的第二原动机。此外，转子叶片具有用于将第一线性运动与产生累积线性运动的第二线性运动相结合的联接传动装置; 以及引起累积线性运动使控制翼片旋转的小传动装置。

2. 发明申请

WO2008147463A3 ON-BLADE ACTUATOR FOR HELICOPTER ROTOR BLADE CONTROL FLAPS 审中-公开
标题翻译：用于直升机转子叶片控制板的叶片执行机构
公开(公告)号：WO2008147463A3
公开(公告)日：2009-03-26
申请号：PCT/US2007086587
申请日：2007-12-06
申请人： SIKORSKY AIRCRAFT CORP , YEH JIMMY LIH-MIN , SUN FANPING , CHAUDHRY ZAFFIR , DOLD ROBERT H , JONSSON ULF J , WAKE BRIAN E , O'CALLAGHAN MICHAEL G
发明人： YEH JIMMY LIH-MIN , SUN FANPING , CHAUDHRY ZAFFIR , DOLD ROBERT H , JONSSON ULF J , WAKE BRIAN E , O'CALLAGHAN MICHAEL G
IPC分类号： B64C27/46
CPC分类号： B64C27/615 , B64C2027/7272 , Y02T50/34
摘要： A helicopter rotor blade having a blade body that defines a confined space and a control flap that is secured to the blade body that moves through a range of motion. An electric machine is secured inside of the rotor blade body that rotates a motor shaft. A transmission device is secured to the motor shaft and the control flap that transfers rotary motion of the motor shaft to the control flap to generate movement of the control flap through its range of motion. The transmission device remains substantially within the confined space throughout the range of motion.
摘要翻译：一种直升机转子叶片，其具有限定狭缝空间的叶片体和固定到叶片本体上的运动通过运动范围的控制翼片。电动机被固定在转子叶片体内部，使马达轴旋转。传动装置被固定到电动机轴和控制挡板，其将电动机轴的旋转运动传递到控制挡板，以通过其运动范围产生控制挡板的运动。传输装置在整个运动范围内基本保持在限制的空间内。

3. 发明申请

WO2008048279A3 BRUSHLESS DIRECT CURRENT MOTOR (BLDC) BASED ACTUATOR FOR HELICOPTER ROTOR CONTROL 审中-公开
标题翻译：无刷直流电动机（BLDC）基于执行器的直升机转子控制
公开(公告)号：WO2008048279A3
公开(公告)日：2008-09-25
申请号：PCT/US2006042628
申请日：2006-10-31
申请人： SIKORSKY AIRCRAFT CORP , CHAUDHRY ZAFFIR , WAKE BRIAN E , FANPING SUN , BEDWELL RICHARD J , HOFFMAN LEE A , YEH JIMMY LIH-MIN
发明人： CHAUDHRY ZAFFIR , WAKE BRIAN E , FANPING SUN , BEDWELL RICHARD J , HOFFMAN LEE A , YEH JIMMY LIH-MIN
IPC分类号： B64C9/00 , B64C9/32
CPC分类号： B64C27/615 , B64C27/72 , B64C2027/7266 , Y02T50/34
摘要： A device for controlling the pitch of a helicopter's rotor blade, the device having a BLDC motor based actuator; and at least one control surface operatively connected to the BLDC motor based actuator. The actuator and the control surface are preferably fully integrated into the interior profile of the rotor blade and are capable of controlling the PFC of the helicopter and improving HHC during operation by reducing noise and vibration. The motor is preferably a high power density motor incorporating rare earth permanent magnets connected to a roller/ball screw or planetary gear set to provide the right combination of force/torque, stroke and frequency.
摘要翻译：一种用于控制直升机转子叶片间距的装置，该装置具有基于无刷直流电动机的致动器; 以及可操作地连接到基于无刷直流电动机的致动器的至少一个控制表面。致动器和控制表面优选完全集成到转子叶片的内部轮廓中，并且能够通过降低噪音和振动来控制直升机的PFC并改善操作中的HHC。电动机优选地是结合稀土永磁体的高功率密度电动机，其连接到滚子/滚珠丝杠或行星齿轮组，以提供力/转矩，行程和频率的正确组合。

4. 发明申请

WO2008048278A3 ROTORCRAFT CONTROL SYSTEM AND METHOD OF USING 审中-公开
标题翻译：旋转手柄控制系统和使用方法
公开(公告)号：WO2008048278A3
公开(公告)日：2008-11-13
申请号：PCT/US2006042627
申请日：2006-10-31
申请人： SIKORSKY AIRCRAFT CORP , CHAUDHRY ZAFFIR , WAKE BRIAN E , MING CAO
发明人： CHAUDHRY ZAFFIR , WAKE BRIAN E , MING CAO
IPC分类号： B64C27/52
CPC分类号： B64C27/615 , B64C27/001 , B64C2027/7266 , Y02T50/34
摘要： A rotorcraft control system for effectuating primary flight control and high harmonic control. The control system preferably including at least one primary flap, at least one primary actuator used principally for primary flight control, at least one secondary flap, and at least one secondary actuator used principally for high harmonic control. The at least one secondary flap and the at least one secondary actuator preferably may also be used to enhance primary flight control under some flight conditions.
摘要翻译：用于实现主飞行控制和高次谐波控制的旋翼飞行器控制系统。控制系统优选地包括至少一个主翼片，主要用于主飞行控制的至少一个主致动器，至少一个副翼片以及主要用于高次谐波控制的至少一个副致动器。所述至少一个副翼和所述至少一个副致动器优选地还可以用于增强在一些飞行条件下的主飞行控制。

5. 发明申请

WO2016126301A2 ACTIVE FLOW CONTROL SYSTEM 审中-公开
标题翻译：主动流量控制系统
公开(公告)号：WO2016126301A2
公开(公告)日：2016-08-11
申请号：PCT/US2015061600
申请日：2015-11-19
申请人： SIKORSKY AIRCRAFT CORP
发明人： WAKE BRIAN E , MATALANIS CLAUDE G , BOWLES PATRICK
IPC分类号： B64C27/08
CPC分类号： B64C27/10 , B64C7/00 , B64C23/005 , B64C2027/8236 , Y02T50/166
摘要： An aircraft is provided and includes a fuselage including a top and a tail, a main rotor apparatus disposed at the top of the fuselage, which rotates one or more rotors to generate lift, and an active flow control (AFC) system. The AFC system includes plasma actuators configured to generate plasma at a location adjacent to the main rotor apparatus and/or at the tail of the fuselage.
摘要翻译：提供了一种飞机，其包括具有顶部和尾部的机身，设置在机身顶部的主旋翼装置以及主动流动控制（AFC）系统，所述主旋翼装置旋转一个或多个旋翼以产生升力。 AFC系统包括等离子体致动器，等离子体致动器被配置为在与主旋翼装置相邻的位置和/或机身的尾部产生等离子体。

6. 发明专利

DE69624679T2 未知
公开(公告)号：DE69624679T2
公开(公告)日：2003-07-17
申请号：DE69624679
申请日：1996-08-16
申请人： SIKORSKY AIRCRAFT CORP
发明人： WAKE BRIAN E , EGOLF ALAN T , LORBER PETER F , LANDGREBE ANTON J
IPC分类号： B64C27/46 , B64C23/06
摘要： In one embodiment for a helicopter main rotor assembly, a half-plow vortex generator is mounted in combination with the upper aerodynamic surface of each main rotor blade and is operative to generate a primary corotating vortex of sufficient strength to interact with and dissipate the tip vortex generated by the same main rotor blade, thereby reducing blade-vortex interaction noise radiating from the helicopter main rotor assembly. The half-plow vortex generator has a right triangular planform configuration defined by a length, a width, and an apex angle. The three-dimensional configuration of the vortex generator is further defined by an apex height. The apex height is the primary determinant of the strength of the generated primary corotating vortex and is defined in terms of the magnitude of the local chord where the vortex generator is mounted. The apex height preferably has a magnitude within the range of about 0.01 to about 0.08 of the magnitude of the local chord. The length, width, and apex angle are secondary determinants of the strength of the primary corotating vortex generated by the half-plow vortex generator. The length and width of the vortex generator are also defined in terms of the magnitude of the local chord, the length preferably having a magnitude within the range of about one-fourth to about one-half of the magnitude of the local chord and the width preferably having a value of about one-third of the length of the vortex generator. The apex angle preferably has a value within the range of about twenty to about thirty degrees. The mounting site for the half-plow vortex generator is defined in terms of the length of the local and tip chords. The vortex generator is mounted inboardly from the tip of the main rotor blade a spanwise distance having a magnitude preferably within the range of about one-half to about equal to the tip chord length and is mounted with the length thereof in substantial alignment with the local chord. The apex of the vortex generator is mounted inwardly from the leading edge of the main rotor blade by a chordal distance having a magnitude of about one-quarter of the magnitude of the local chord.

7. 发明专利

CA2609917C ROTOR HUB FAIRING SYSTEM FOR A COUNTER-ROTATING, COAXIAL ROTOR SYSTEM 未知
公开(公告)号：CA2609917C
公开(公告)日：2011-01-25
申请号：CA2609917
申请日：2006-04-28
申请人： SIKORSKY AIRCRAFT CORP
发明人： BERTOLOTTI FABIO P , SCOTT MARK W , WAKE BRIAN E , EGOLF T ALAN , MCCORMICK DUANE C
IPC分类号： B64C27/50 , B63H7/02 , B64C7/00 , B64C11/48 , F01D5/06
摘要： A rotor hub fairing system includes an upper hub fairing, a lower hub fairing and a shaft fairing therebetween. The rotor hub fairing system is sized and configured to reduce the overall drag on a dual, counter-rotating, coaxial rotor system. Preferably, the rotor hub fairing is fully integrated. The shaft fairing preferably includes a minimal thickness at the midsection to reduce drag with an increasing thickness adjacent the upper and lower hub fairings to reduce the flow separation on the hub fairing surfaces without overly excessive drag. Other aerodynamic structures, such as a horizontal splitter and/or a plurality of turning vanes may be mounted to the shaft fairing to facilitate flow around the upper and lower hub fairings to reduce flow separation and drag.

8. 发明专利

DE69624679D1 未知
公开(公告)号：DE69624679D1
公开(公告)日：2002-12-12
申请号：DE69624679
申请日：1996-08-16
申请人： SIKORSKY AIRCRAFT CORP
发明人： WAKE BRIAN E , EGOLF ALAN T , LORBER PETER F , LANDGREBE ANTON J
IPC分类号： B64C27/46 , B64C23/06
摘要： In one embodiment for a helicopter main rotor assembly, a half-plow vortex generator is mounted in combination with the upper aerodynamic surface of each main rotor blade and is operative to generate a primary corotating vortex of sufficient strength to interact with and dissipate the tip vortex generated by the same main rotor blade, thereby reducing blade-vortex interaction noise radiating from the helicopter main rotor assembly. The half-plow vortex generator has a right triangular planform configuration defined by a length, a width, and an apex angle. The three-dimensional configuration of the vortex generator is further defined by an apex height. The apex height is the primary determinant of the strength of the generated primary corotating vortex and is defined in terms of the magnitude of the local chord where the vortex generator is mounted. The apex height preferably has a magnitude within the range of about 0.01 to about 0.08 of the magnitude of the local chord. The length, width, and apex angle are secondary determinants of the strength of the primary corotating vortex generated by the half-plow vortex generator. The length and width of the vortex generator are also defined in terms of the magnitude of the local chord, the length preferably having a magnitude within the range of about one-fourth to about one-half of the magnitude of the local chord and the width preferably having a value of about one-third of the length of the vortex generator. The apex angle preferably has a value within the range of about twenty to about thirty degrees. The mounting site for the half-plow vortex generator is defined in terms of the length of the local and tip chords. The vortex generator is mounted inboardly from the tip of the main rotor blade a spanwise distance having a magnitude preferably within the range of about one-half to about equal to the tip chord length and is mounted with the length thereof in substantial alignment with the local chord. The apex of the vortex generator is mounted inwardly from the leading edge of the main rotor blade by a chordal distance having a magnitude of about one-quarter of the magnitude of the local chord.

9. 发明申请

WO2006022777A3 MINIMIZING THE STACK EFFECT IN TALL BUILDINGS HAVING VERTICAL SHAFTS 审中-公开
标题翻译：尽量减少竖直高层建筑的堆砌效应
公开(公告)号：WO2006022777A3
公开(公告)日：2006-04-27
申请号：PCT/US2004035496
申请日：2004-10-26
申请人： OTIS ELEVATOR CO , NARAYANAN SATISH , SUNDEL TIMOTHY N , WAKE BRIAN E , ZEIDNER LAWRENCE E , DOBBS GREGORY M , PENG PEI-YUAN
发明人： NARAYANAN SATISH , SUNDEL TIMOTHY N , WAKE BRIAN E , ZEIDNER LAWRENCE E , DOBBS GREGORY M , PENG PEI-YUAN
IPC分类号： B66B9/00 , B66B11/02 , B66B13/02 , B66B13/24 , E04H6/06 , E06B7/00
CPC分类号： B66B11/0005
摘要： An elevator system (20) includes at least one vertical shaft (32) extending between at least two levels (24, 36) of a building (22). One of the levels (24) includes at least one passageway (28) between an interior of the building and the outside environment. At least one second shaft (40) extends between the other building level (36) and at least one other level within the building. The interior of the second shaft (40) is isolated from airflow on the building level (24) that includes the passageway (28) to the outside environment. Disclosed examples include enclosures (52) for isolating the first shaft (32) from airflow on at least one of the levels to which the first shaft provides access.
摘要翻译：电梯系统（20）包括在建筑物（22）的至少两个层（24,36）之间延伸的至少一个竖直轴（32）。其中一个水平面（24）包括建筑物内部和外部环境之间的至少一个通道（28）。至少一个第二轴（40）在建筑物内的另一建筑物楼层（36）和至少一个其他楼层之间延伸。第二轴（40）的内部与包括通道（28）的建筑物楼层（24）上的气流隔离到外部环境。所公开的示例包括用于将第一轴（32）与第一轴提供进入的至少一个水平面上的气流隔离的外壳（52）。

10. 发明公开

EP2094562A4 SELF-LUBRICATED ACTUATOR FOR ON-BLADE ROTOR CONTROL 失效
标题翻译： SELBSTSMIMIERENDER AKTUATORFÜRROTORSTEUERUNG AUF DER LAUFSCHAUFEL
公开(公告)号：EP2094562A4
公开(公告)日：2017-05-17
申请号：EP07875042
申请日：2007-11-12
申请人： SIKORSKY AIRCRAFT CORP
发明人： COLLINS ANDREW JOHN , CHAUDHRY ZAFFIR , JONSSON ULF J , SUN FANPING , WAKE BRIAN E , O'CALLAGHAN MICHAEL G , YEH JIMMY LIN-MIN
IPC分类号： B64C9/00 , B64C27/615 , B64C27/72
CPC分类号： B64C27/615 , B64C2027/7266 , Y02T50/34
摘要： A self-lubricated actuator for a rotor blade flap of a helicopter having a housing; a motor having a shaft disposed in a bearing is provided. The actuator further has an output rod and a mechanism operatively associated with the motor and the output rod to transmit movement from the motor to the output rod. The housing includes a lubrication medium capable of substantially immersing the bearing, the motor shaft and the mechanism during operation.
摘要翻译：一种用于具有壳体的直升机的转子叶片襟翼的自润滑致动器; 提供具有设置在轴承中的轴的电动机。致动器还具有输出杆和与马达和输出杆操作地相关联的机构，以将运动从马达传递到输出杆。壳体包括润滑介质，其能够在操作期间基本浸入轴承，马达轴和机构。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式