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. 发明授权

CN103702902B 方向舵偏置增益变换器失效
公开(公告)号：CN103702902B
公开(公告)日：2015-12-02
申请号：CN201180072544.3
申请日：2011-07-26
申请人：里尔喷射机公司
发明人：哈里斯·巴特勒 , 米哈利斯·韦莱塔斯
IPC分类号： B64C13/24
CPC分类号： B64C13/28 , B64C13/24 , B64C13/26 , B64C13/40
摘要：一种用于飞机方向舵的偏置增益系统（10）包括一对从偏置致动器（12）接收致动力的接头端（21）。舵杆接口位于所述接头端之间。作为源自所述偏置致动器的所述致动力的函数，所述接口绕所述舵杆（11）旋转。包括位于所述接头端和所述舵杆之间的连杆和接头的机构可在其中在所述接头端和所述舵杆接口之间限定出第一力矩臂的收缩配置和其中的第二力矩臂具有大于所述第一力矩臂的尺寸的膨胀增益配置之间进行致动。致动器被连接至所述机构以根据源自所述偏置致动器的所述致动力而单独地致动所述机构，从而在配置之间移动所述机构。本发明也提供了一种用于控制在飞机舵杆上的扭矩的飞机和方法。

2. 发明公开

CN103702902A 方向舵偏置增益变换器失效
公开(公告)号：CN103702902A
公开(公告)日：2014-04-02
申请号：CN201180072544.3
申请日：2011-07-26
申请人：里尔喷射机公司
发明人：哈里斯·巴特勒 , 米哈利斯·韦莱塔斯
IPC分类号： B64C13/24
CPC分类号： B64C13/28 , B64C13/24 , B64C13/26 , B64C13/40
摘要：一种用于飞机方向舵的偏置增益系统（10）包括一对从偏置致动器（12）接收致动力的接头端（21）。舵杆接口位于所述接头端之间。作为源自所述偏置致动器的所述致动力的函数，所述接口绕所述舵杆（11）旋转。包括位于所述接头端和所述舵杆之间的连杆和接头的机构可在其中在所述接头端和所述舵杆接口之间限定出第一力矩臂的收缩配置和其中的第二力矩臂具有大于所述第一力矩臂的尺寸的膨胀增益配置之间进行致动。致动器被连接至所述机构以根据源自所述偏置致动器的所述致动力而单独地致动所述机构，从而在配置之间移动所述机构。本发明也提供了一种用于控制在飞机舵杆上的扭矩的飞机和方法。

3. 发明申请

WO2012060806A1 METHOD AND APPARATUS FOR ACTIVELY MANIPULATING AERODYNAMIC SURFACES 审中-公开
标题翻译：用于动态操纵气动表面的方法和装置
公开(公告)号：WO2012060806A1
公开(公告)日：2012-05-10
申请号：PCT/US2010/054910
申请日：2010-11-01
申请人： BELL HELICOPTER TEXTRON INC. , SCHANK, Troy, C. , KINTZINGER, Peter, H. , SHERRILL, Paul, B. , PARHAM, Thomas
发明人： SCHANK, Troy, C. , KINTZINGER, Peter, H. , SHERRILL, Paul, B. , PARHAM, Thomas
IPC分类号： B64C27/615
CPC分类号： B64C13/26 , B64C13/30 , B64C27/00 , B64C27/001 , B64C27/615 , B64C2027/7266 , F16H21/44 , Y02T50/34 , Y02T50/44
摘要： A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements.
摘要翻译：提供了一种方法和装置，其包括致动器系统，该致动器系统可以连接到用于控制有源元件的机翼框架。致动器系统可以包括可沿着平行于机翼的跨度轴线的轴线移动的滑动元件。滑动元件可以连接到固定元件和曲柄元件，曲柄元件通常包括梁元件和枢轴元件。梁元件可以从枢转元件偏移，使得曲柄元件可以在外力作用下具有负刚度的枢转元件旋转，其倾向于将滑动元件拉离固定元件。

4. 发明申请

US20150274280A1 AIR VEHICLE, ACTUATOR ASSEMBLY AND ASSOCIATED METHOD OF MANUFACTURE 有权
标题翻译：空中车辆，执行机构总成及相关制造方法
公开(公告)号：US20150274280A1
公开(公告)日：2015-10-01
申请号：US14242088
申请日：2014-04-01
申请人： The Boeing Company
发明人： James Joseph Sheahan, JR. , Donald V. Drouin, JR.
IPC分类号： B64C13/34 , B64C13/26 , B64C9/00
CPC分类号： B64C13/34 , B64C9/00 , B64C9/02 , B64C13/26 , B64C13/38 , B64C13/40 , B64C13/50 , Y02T50/32 , Y02T50/44 , Y10T29/49826
摘要： An air vehicle, an actuator assembly and a method of manufacture are provided in order to incorporate the actuator assembly within the outer mold line of the air vehicle. In regards to an air vehicle, the air vehicle includes a primary structure and a movable structure configured to be controllably moved relative to the primary structure. The air vehicle also includes an actuator assembly configured to cause the movable structure to be positioned relative to the primary structure. The actuator assembly includes an actuator housing and an actuation mechanism. The actuation mechanism is at least partially disposed within the actuator housing and is configured to provide for relative movement between the primary structure and the movable structure. At least a portion of the actuator assembly is built into at least one of the primary structure and the movable structure so as to be within an outer mold line of the air vehicle.
摘要翻译：提供了一种机动车辆，致动器组件和制造方法，以将致动器组件并入到空中交通工具的外部模具线内。关于空中交通工具，该空中交通工具包括主结构和可相对于主结构可控制地移动的可移动结构。空中车辆还包括构造成使可移动结构相对于主结构定位的致动器组件。致动器组件包括致动器壳体和致动机构。所述致动机构至少部分地布置在所述致动器壳体内，并且构造成提供所述主结构和所述可移动结构之间的相对运动。致动器组件的至少一部分内置在主结构和可移动结构中的至少一个中，以便在空中车辆的外部模具线内。

5. 发明申请

US20150083852A1 VARIABLE CAMBER FLAP SYSTEM AND METHOD 有权
标题翻译：可变的CAMAP襟翼系统和方法
公开(公告)号：US20150083852A1
公开(公告)日：2015-03-26
申请号：US14034940
申请日：2013-09-24
申请人： The Boeing Company
发明人： Matthew A. Moser , Michael R. Finn , Mark J. Gardner , Mark S. Good , Sarah A. Jones
IPC分类号： B64C13/34
CPC分类号： B64C13/34 , B64C3/50 , B64C9/06 , B64C9/12 , B64C9/14 , B64C13/26 , Y02T50/32
摘要： A variable camber system for an aircraft may include a variable camber trim unit (VCTU) positioned between an inboard device and an outboard device. The inboard device and the outboard device may be mounted to at least one of a leading edge and a trailing edge of a wing. The VCTU may include a speed sum gearbox having an inboard shaft coupled to the inboard device and an outboard shaft coupled to the outboard device. The VCTU may additionally include a VCTU electric motor engaged to the speed sum gearbox. The VCTU electric motor may be selectively operable in conjunction with the speed sum gearbox to rotate the outboard shaft independent of the inboard shaft in a manner causing the outboard device to be actuated independent of the inboard device.
摘要翻译：用于飞行器的可变外倾角系统可以包括位于内侧装置和外侧装置之间的可变外倾角装置单元（VCTU）。内侧装置和外侧装置可以安装到机翼的前缘和后缘中的至少一个。 VCTU可以包括速度和齿轮箱，其具有联接到内侧装置的内侧轴和联接到外侧装置的外侧轴。 VCTU可以另外包括接合到速度和齿轮箱的VCTU电动机。 VCTU电动机可以选择性地与速度总和齿轮箱一起操作，以独立于内侧轴旋转外侧轴，使得外部装置独立于内侧装置被致动。

6. 发明授权

US08657229B2 Method and apparatus for actively manipulating aerodynamic surfaces 有权
标题翻译：用于主动操纵气动表面的方法和装置
公开(公告)号：US08657229B2
公开(公告)日：2014-02-25
申请号：US13703813
申请日：2010-11-01
申请人： Troy C Schank , Peter H Kintzinger , Paul B Sherrill , Thomas Parham
发明人： Troy C Schank , Peter H Kintzinger , Paul B Sherrill , Thomas Parham
IPC分类号： B64C3/50 , B64C9/00 , B64C27/615
CPC分类号： B64C13/26 , B64C13/30 , B64C27/00 , B64C27/001 , B64C27/615 , B64C2027/7266 , F16H21/44 , Y02T50/34 , Y02T50/44
摘要： A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements.
摘要翻译：提供了一种方法和装置，包括可以连接到翼架以用于控制有源元件的致动器系统。致动器系统可以包括可沿着平行于机翼的跨度轴线的轴线移动的滑动元件。滑动元件可以连接到固定元件和曲柄元件，曲柄元件通常包括梁元件和枢轴元件。梁元件可以从枢转元件偏移，使得曲柄元件可以在倾向于将滑动元件拉离固定元件的外力作用下具有负刚度的情况下围绕枢转元件旋转。

7. 发明申请

US20050151028A1 Apparatus for driving and adjusting flaps hinged to an aircraft 有权
标题翻译：用于驱动和调整翼片的装置铰接到飞机上
公开(公告)号：US20050151028A1
公开(公告)日：2005-07-14
申请号：US11021723
申请日：2004-12-22
申请人： Ulrich Pohl , Carsten Thomas , Christian Lulla , Martin Kloenne
发明人： Ulrich Pohl , Carsten Thomas , Christian Lulla , Martin Kloenne
IPC分类号： B64C13/26 , B64D45/00 , B64C3/58
CPC分类号： B64D45/0005 , B64C13/26 , B64D2045/001
摘要： Flaps, for example leading edge flaps and/or trailing edge flaps of an aircraft wing, are driven and adjusted by respective drive units. Drive shafts of neighboring flaps are coupled to each other by a differential gear. The differential gear is thus coupled to a main drive shaft which is driven by a main drive unit. Additionally, the differential gear is coupled to a secondary drive unit. The main drive power and the secondary drive power and thus the respective flap motions are super-imposable on each other, which permits operating the flaps independently of each other or in synchronism with each other.
摘要翻译：翼片，例如飞机机翼的前缘翼片和/或后缘翼片由相应的驱动单元驱动和调节。相邻翼片的驱动轴通过差速齿轮相互连接。因此，差速齿轮联接到由主驱动单元驱动的主驱动轴。此外，差速齿轮联接到辅助驱动单元。主驱动功率和二次驱动功率以及因此相应的皮瓣运动彼此是超重的，这允许彼此独立地彼此操作或彼此同步地操作翼片。

8. 发明申请

US20180017987A1 DETENT ALIGNMENT MECHANISM ASSEMBLY 审中-公开
公开(公告)号：US20180017987A1
公开(公告)日：2018-01-18
申请号：US15209186
申请日：2016-07-13
申请人： Hamilton Sundstrand Corporation
发明人： Cory M. Crandall-Seibert , Jeffrey Paul Jacobs
IPC分类号： G05G5/03 , B64C13/14 , B64C13/26 , B64C13/50
CPC分类号： G05G5/06 , B64C13/04 , B64C13/0421 , B64C13/10 , B64C13/14 , B64C13/26 , B64C13/50 , G05G1/04 , G05G5/005 , G05G5/18 , G05G2505/00
摘要： A detent alignment mechanism assembly is provided and includes a shaft, a lock mechanism configured to selectively occupy an unlocked position at which the shaft is movable and a locked position at which the shaft is immovable, a detent mechanism coupled to the shaft and formed to define detent positions for the shaft to assume and move between and a detent alignment mechanism configured to provide to an operator of the shaft feedback and assistance corresponding to assumptions of the detent positions by the shaft during movements thereof by the operator.

9. 发明申请

US20140365035A1 AIR VEHICLE CONTROL SYSTEM AND METHOD 有权
标题翻译：空气车辆控制系统和方法
公开(公告)号：US20140365035A1
公开(公告)日：2014-12-11
申请号：US13911160
申请日：2013-06-06
申请人： Raytheon Company
发明人： Richard E Hindman
IPC分类号： B64C13/26 , B64C13/02
CPC分类号： B64C13/26 , B64C13/02 , F42B15/01 , G05D1/107
摘要： A control actuation system (CAS) for positioning control effectors of an air vehicle, for steering the air vehicle, includes application of a control allocation matrix to measured positions of the control effectors or their actuators, as part of a feedback mechanism. The output from the control allocation matrix is used as an input for one or more controllers, the output of which is passed through an inverse control allocation matrix, to produce signals that are sent to control actuators to position the control effectors. The controller may use different gains for different of its inputs, for example applying a lower gain for a brake signal than for one or more of a pitch signal, a roll signal, and a yaw signal. The control actuation may make for a control system that is able to better withstand impaired performance or non-performance of some the control effectors.
摘要翻译：用于定位用于转向空中飞行器的空中飞行器的控制执行器的控制致动系统（CAS）包括将控制分配矩阵应用于控制效应器或其致动器的测量位置，作为反馈机构的一部分。来自控制分配矩阵的输出被用作一个或多个控制器的输入，该控制器的输出通过反向控制分配矩阵，以产生发送到控制致动器来定位控制效应器的信号。控制器可以对其不同的输入使用不同的增益，例如对于制动信号施加相对于音调信号，滚动信号和偏航信号中的一个或多个的较低增益。控制致动可以使得能够更好地抵御一些控制效应器的性能受损或不执行的控制系统。

10. 发明申请

US20090206209A1 SYSTEMS AND METHODS FOR PROVIDING DIFFERENTIAL MOTION TO WING HIGH LIFT DEVICE 有权
标题翻译：用于提供差分运动以实现高提升装置的系统和方法
公开(公告)号：US20090206209A1
公开(公告)日：2009-08-20
申请号：US12352447
申请日：2009-01-12
申请人： Mark S. Good , Paul M. Viigen , Seth E. Gitnes , Glynn Michael Thomas
发明人： Mark S. Good , Paul M. Viigen , Seth E. Gitnes , Glynn Michael Thomas
IPC分类号： B64C13/38
CPC分类号： B64C3/50 , B64C9/14 , B64C13/26 , Y02T50/14 , Y02T50/32
摘要： Systems and methods for providing differential motion to wing high lift devices are disclosed. A system in accordance with one embodiment of the invention includes a wing having a leading edge, a trailing edge, a first deployable lift device with a first spanwise location, and a second deployable lift device with a second spanwise location different than the first. The wing system can further include a drive system having a drive link operatively coupleable to both the first and second deployable lift devices, and a control system operatively coupled to the drive system. The control system can have a first configuration for which the drive link is operatively coupled to the first and second deployable lift devices, and activation of at least a portion of the drive link moves the first and second deployable lift devices together. In a second configuration, the drive link is operatively coupled to at least the first deployable lift device and operatively decoupled from the second deployable lift device, so that actuation of at least a portion of the drive link moves the first deployable lift device relative to the second deployable lift device.
摘要翻译：公开了用于向机翼高升降装置提供差速运动的系统和方法。根据本发明的一个实施例的系统包括具有前缘，后缘，具有第一翼展位置的第一可展开升降装置和具有不同于第一翼展位置的第二翼展位置的第二可展开提升装置的翼。机翼系统还可以包括驱动系统，该驱动系统具有可操作地连接到第一和第二可展开提升装置两者的驱动链路，以及可操作地耦合到驱动系统的控制系统。控制系统可以具有第一构造，驱动连杆可操作地联接到第一和第二可展开提升装置，并且驱动连杆的至少一部分的启动使第一和第二可展开举升装置移动到一起。在第二构造中，驱动连杆可操作地联接到至少第一可展开提升装置并且可操作地与第二可展开提升装置分离，使得驱动连杆的至少一部分的致动使第一可展开提升装置相对于第二可展开提升装置。

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