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

WO2022125348A2 CONTROL PLATE-BASED CONTROL ACTUATION SYSTEM 审中-公开
公开(公告)号：WO2022125348A2
公开(公告)日：2022-06-16
申请号：PCT/US2021/061332
申请日：2021-12-01
申请人： BAE SYSTEMS INFORMATION AND ELECTRONIC SYSTEMS INTEGRATION INC.
发明人： BATCHELDER, Jason, H. , CHROBAK, Matthew, F. , DIPPEL, Ryan
IPC分类号： F42B10/64 , F42B15/01 , B64C13/26
摘要： The system and method of a steering a moving object using a control plate-based control actuation system on the moving object. The control plate-based control actuation system having a control plate with at least four fin linkages for connecting at least four fins to the control plate; and three actuators configured to move the control plate to produce movement in two or more of the at least four fins. The system produces roll, pitch, and yaw moments for the moving object using three actuators acting on the control plate and thus moving two or more of the at least four fins all with no loss of performance as compared to systems with four actuators.

2. 发明申请

WO2006029132A1 SYSTEMS AND METHODS FOR PROVIDING DIFFERENTIAL MOTION TO WING HIGH LIFT DEVICES 审中-公开
标题翻译：用于提供差异运动以达到高起动装置的系统和方法
公开(公告)号：WO2006029132A1
公开(公告)日：2006-03-16
申请号：PCT/US2005/031659
申请日：2005-09-07
申请人： THE BOEING COMPANY , GITNES, Seth, E. , VIJGEN, Paul, M. , GOOD, Mark, S. , THOMAS, Glynn, M.
发明人： GITNES, Seth, E. , VIJGEN, Paul, M. , GOOD, Mark, S. , THOMAS, Glynn, M.
IPC分类号： B64C13/26
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 (110) having a leading edge, a trailing edge, a first deployable lift device (212) with a first spanwise location, and a second deployable lift device (213) with a second spanwise location different than the first. The wing system can further include a drive system (350) having a drive link (353) operatively coupleable to both the first and second deployable lift devices(212, 213), and a control system (320) operatively coupled to the drive system (350). The control system (320) can have a first configuration for which the drive link (353) is operatively coupled to the first and second deployable lift devices (212, 213), and activation of at least a portion of the drive link (353) moves the first and second deployable lift devices (212, 213) together. In a second configuration, the drive link (353) is operatively coupled to at least the first deployable lift device (212) and operatively decoupled from the second deployable lift device (213), so that actuation of at least a portion of the drive link (353) moves the first deployable lift device (212) relative to the second deployable lift device (213).
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的翼片（110），后缘，具有第一翼展位置的第一可展开提升装置（212）和具有第一展开式提升装置第二展开位置不同于第一展开位置。机翼系统还可以包括驱动系统（350），驱动系统（350）具有可操作地连接到第一和第二可展开提升装置（212,213）两者的驱动连杆（353）;和控制系统（320），可操作地联接到驱动系统 350）。控制系统（320）可以具有第一构造，驱动连杆（353）可操作地联接到第一和第二可展开提升装置（212,213），并且驱动链轮（353）的至少一部分的启动，将第一和第二可展开升降装置（212,213）移动到一起。在第二构造中，驱动连杆（353）可操作地联接到至少第一可展开提升装置（212）并且可操作地与第二可展开提升装置（213）分离，使得致动驱动连杆的至少一部分（353）相对于第二可展开提升装置（213）移动第一可展开提升装置（212）。

3. 发明申请

WO2019100149A1 SYSTEM AND METHOD FOR ACTUATING HIGH-LIFT FLIGHT CONTROL SURFACES 审中-公开
公开(公告)号：WO2019100149A1
公开(公告)日：2019-05-31
申请号：PCT/CA2018/051467
申请日：2018-11-19
申请人： BOMBARDIER INC.
发明人： TZABARI, Ehud
IPC分类号： B64C13/26 , B64C13/28 , B64C3/50
摘要： A system and method for actuating one or more high-lift flight control surfaces of an aircraft are disclosed. The system comprises actuators operatively coupled between a driveline and one or more high-lift flight control surfaces associated with a wing of the aircraft. The actuators are configured to cause actuation of the one or more first high-lift flight control surfaces in response to being driven by the first driveline. Each actuator is associated with a no-back device configured to prevent an air load on the one or more high-lift flight control surfaces from driving the one or more high-lift flight control surfaces. The system also comprises a backup brake applicable to the driveline. The backup brake can be applied upon the identification of a developing unsafe condition such as an asymmetry condition between the flight control surfaces of each wing of the aircraft or an uncommanded movement the flight control surfaces.

4. 发明申请

WO2015078724A1 MAGNETOSTRIKTIVER SENSOR FÜR AKTUATOREN IN FLUGZEUGEN 审中-公开
标题翻译：磁致伸缩传感器，用于飞机作动器
公开(公告)号：WO2015078724A1
公开(公告)日：2015-06-04
申请号：PCT/EP2014/074867
申请日：2014-11-18
申请人： NCTE AG
发明人： STEINACHER, Bastian
IPC分类号： G01L1/12 , B64C13/26 , B64D45/00 , G01L3/10
CPC分类号： G01L1/125 , B64C13/26 , B64D2045/001 , G01L3/102
摘要： Die vorliegende Erfindung betrifft eine Vorrichtung zum Bestimmen einer mechanischen Kraft eines Aktuators auf eine bewegliche Flugzeugkomponente. Die erfindungsgemäße Vorrichtung umfasst eine Welle, insbesondere eine Voll- oder Hohlwelle, zum Übertragen von Kraft und/oder Drehmoment auf den Aktuator, wobei die Welle einen ersten remanent in einer ersten Umfangsrichtung magnetisierten Bereich aufweist; und wenigstens einen ersten Magnetfeldsensor zum Erfassen einer unter Einwirkung von Kraft und/oder Drehmoment auf die Welle auftretenden Feldrichtungsänderung des ersten magnetisierten Bereichs..
摘要翻译：本发明涉及一种装置，用于确定在一个可移动的飞机部件的致动器的机械力。本发明的装置包括一轴，特别是一个实心或空心轴，用于传输功率和/或扭矩传递到致动器，其中所述轴包括在第一圆周方向上被磁化区域具有第一保持; 和用于检测的力和/或扭矩传递到第一磁化区域的轴的影响下产生的磁场方向变化的至少一个第一磁场传感器..

5. 发明申请

WO2022271429A1 VEHICLE WITH TRACTOR TILTROTORS AND PUSHER TILTROTORS 审中-公开
公开(公告)号：WO2022271429A1
公开(公告)日：2022-12-29
申请号：PCT/US2022/032110
申请日：2022-06-03
申请人： KITTY HAWK CORPORATION
发明人： FRANK, Evan, E. , SRIDHARAN, Ananth , PAUL-DUBOIS-TAINE, Arthur
IPC分类号： B64C29/00 , B64C11/06 , B64C11/46 , B64C27/20 , B64C27/22 , B64C27/26 , B64C13/26 , B64C29/0033 , B64D27/26
摘要： A vehicle includes a fuselage, a wing, a pylon that is coupled to the wing, and a tractor tiltrotor. The tractor tiltrotor is coupled to the pylon and is located forward of the wing; the tractor tiltrotor tilts upwards during a hover mode. There is also a pusher tiltrotor where the pusher tiltrotor is coupled to the pylon and is located aft of the wing; the pusher tiltrotor tilts downwards during the hover mode. The tractor tiltrotor and the pusher tiltrotor rotate about a longitudinal and coaxial axis of rotation in a cruise mode.

6. 发明申请

WO2007009520A1 CONTROL SURFACE OPERATING MECHANISM 审中-公开
标题翻译：控制面工作机理
公开(公告)号：WO2007009520A1
公开(公告)日：2007-01-25
申请号：PCT/EP2006/004442
申请日：2006-05-11
申请人： AIRBUS DEUTSCHLAND GMBH , MÄNZ, Christian
发明人： MÄNZ, Christian
IPC分类号： B64C13/26
CPC分类号： B64C9/02 , B64C13/24 , Y02T50/44
摘要： Rudder unit control surfaces (12) are usually driven by several hydraulic cylinders. However, this construction is expensive and implies a weight that cannot be neglected. Therefore, the invention proposes to achieve a pivoting motion of an airplane control surface (12, 13, 14, 15, 16) not indirectly by converting a translatory motion of a hydraulic cylinder into a rotatory motion, but rather to generate the rotatory pivoting motion of the airplane control surface (12, 13, 14, 15, 16) in a direct way. For this purpose, the invention makes use of a drive motor (1), the energy of rotation of which is used for generating the pivoting motion of the airplane control surface (12, 13, 14, 15, 16).
摘要翻译：舵单元控制面（12）通常由多个液压缸驱动。然而，这种结构是昂贵的，意味着不容忽视的重量。因此，本发明提出通过将液压缸的平移运动转换为旋转运动而不间接地实现飞机控制表面（12,13,14,15,16）的枢转运动，而是产生旋转枢转运动的飞机控制表面（12,13,14,15,16）。为此，本发明利用驱动马达（1），其旋转能量用于产生飞机控制表面（12,13,14,15,16）的枢转运动。

7. 发明申请

WO2017058588A1 NON-JAMMING STOP MODULE FOR HIGH REVOLUTION APPLICATIONS 审中-公开
标题翻译：用于高转速应用的非串联停止模块
公开(公告)号：WO2017058588A1
公开(公告)日：2017-04-06
申请号：PCT/US2016/052750
申请日：2016-09-21
申请人： MOOG INC.
发明人： LARSON, Lowell, Van Lund
IPC分类号： B64C13/28 , B64C13/24 , B64C13/26 , F16H25/20 , F16H35/00 , G05G5/04
CPC分类号： G05G5/04 , B64C13/28 , F16D41/06 , F16D41/206 , F16D67/02 , F16D2127/001 , F16D2127/004 , F16H35/00 , F16H2035/006
摘要： A stop mechanism for a drive system includes a one-way clutch, a brake, a stop feature, and a linkage. The one-way clutch couples with a drive shaft of the system when the drive shaft is rotating in a first direction but not in an opposite direction. The brake is connected to the drive shaft through the first one-way clutch and is operable to stop drive shaft rotation in the first direction. The stop feature is carried by an output element driven by the drive shaft and actuates the linkage to operate the first brake when the output element reaches a predetermined limit position when moving in a direction corresponding to the first drive direction of the drive shaft. A bidirectional stop mechanism is provided by adding a second one-way clutch, a second brake, and a second stop feature arranged to act in the opposite rotational direction of the drive shaft.
摘要翻译：驱动系统的停止机构包括单向离合器，制动器，停止部件和连杆机构。当驱动轴沿第一方向旋转而不是相反方向时，单向离合器与系统的驱动轴相连。制动器通过第一单向离合器连接到驱动轴，并且可操作以在第一方向上停止驱动轴的旋转。当在与驱动轴的第一驱动方向对应的方向上移动时，当输出元件到达预定极限位置时，停止特征由驱动轴驱动的输出元件承载并且致动联动装置以操作第一制动器。通过添加第二单向离合器，第二制动器和布置成沿着驱动轴的相反旋转方向作用的第二止动件来提供双向停止机构。

8. 发明申请

WO2013162659A2 SYSTEM AND METHOD FOR CONFIGURING A DIRECT LIFT CONTROL SYSTEM OF A VEHICLE 审中-公开
标题翻译：一种用于配置车辆直升机控制系统的系统和方法
公开(公告)号：WO2013162659A2
公开(公告)日：2013-10-31
申请号：PCT/US2013023391
申请日：2013-01-28
申请人： BOEING CO , BEAUFRERE HENRY L
发明人： BEAUFRERE HENRY L
IPC分类号： B64C13/26 , B64C13/04
CPC分类号： B64C13/16 , B64C9/00 , B64C13/04 , B64C13/503 , G05D1/042 , G08G5/02
摘要： A system and methods for configuring a direct lift control system of a vehicle are presented. A plurality of fly-by-wire control surfaces is provided, and fly-by-wire control surface deflection commands of the fly-by-wire control surfaces are scheduled. The fly-by-wire control surfaces are symmetrically actuated based on the fly-by-wire control surface deflection commands such that a fluid dynamic lift of the vehicle is modulated without using a short-period pitch control.
摘要翻译：提出了一种用于配置车辆直升机控制系统的系统和方法。提供多个逐线控制面，并且调度线控控制面的逐线控制面偏转指令。基于线控控制表面偏转命令对称地致动电线控制表面，使得在不使用短时间间距控制的情况下调制车辆的流体动力升程。

9. 发明申请

WO2009083261A3 SYSTEM FOR ACTUATING AT LEAST ONE REGULATING FLAP OF AN AIRCRAFT AND A METHOD FOR CHECKING THE SYSTEM. 审中-公开
标题翻译： SYSTEM FOR运行的航空器和方法，至少一个锁定门测试系统
公开(公告)号：WO2009083261A3
公开(公告)日：2009-10-15
申请号：PCT/EP2008011151
申请日：2008-12-30
申请人： AIRBUS OPERATIONS GMBH , HEINTJES MARK
发明人： HEINTJES MARK
IPC分类号： B64C13/26
CPC分类号： B64C13/28 , B64D45/0005 , B64D2045/001
摘要： The invention relates to a method for actuating at least one regulating flap on each wing of an aircraft, which is actuated by at least two flap coupling devices (11, 12, 13, 14), each having one servo drive device (30), wherein at least one braking device per regulating flap is disposed at a servo drive device (30). By actuating the braking device, an adjusted state of the respective servo drive device (30) can be locked in position. The method comprises the following steps: actuating each braking device of a regulating flap individually; subsequently actuating the servo drive device by means of the drive motor; once the adjusted state of the regulating flap has been changed by a specified amount, the actuation of said regulating flap is concluded. The invention also relates to a system for implementing the method.
摘要翻译：一种用于在飞行器，其被操作的至少两个翼片的耦合装置（11，12，13，14）的相应翼致动至少一个控制襟翼的方法，每个具有致动器装置（30），其特征在于，（至少在一个致动器设备30 ）一个制动装置被安排用于每个致动翼片，与相应的致动器装置（30的调整状态的致动）可被锁定，其包括以下步骤：致动器装置的操作的调节瓣的每个制动装置中的独立然后致动通过在所述驱动马达的装置由所讨论的阻尼器的操作的预定量完成，以及用于实施该方法的系统中的蝶形阀的调节状态而改变。

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