专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

11. 发明申请

WO2009075963A2 TRAILING EDGE DEVICE CATCHERS AND ASSOCIATED SYSTEMS AND METHODS 审中-公开
标题翻译：跟踪边缘设备捕获器和相关系统和方法
公开(公告)号：WO2009075963A2
公开(公告)日：2009-06-18
申请号：PCT/US2008/082146
申请日：2008-10-31
申请人： THE BOEING COMPANY , KORDEL, Jan A. , SAKURAI, Seiya , BALZER, Michael A. , DOVEY, John V.
发明人： KORDEL, Jan A. , SAKURAI, Seiya , BALZER, Michael A. , DOVEY, John V.
IPC分类号： B64C9/16
CPC分类号： B64C9/02 , B64C9/16 , Y02T50/32 , Y02T50/44
摘要： Trailing edge device catchers and associated systems and methods are disclosed. A system in accordance with one embodiment includes a wing having a wing support, a trailing edge device carried by and movable relative to the wing and having a device support, and a coupling connected between the wing and the trailing edge device. The coupling can include a pivot joint that includes a pivot element aligned along a pivot axis and connected between the wing support and the device support. The coupling can further include an actuator coupled between the wing and the trailing edge device, with the actuator having a first position in which the trailing edge device is stowed, and a second position in which the trailing edge device is deployed, with an air flow gap located between the wing and the trailing edge device when the trailing edge device is in the second position. A cam track is carried by one of the wing and the trailing edge device and has opposing cam track surfaces fixed relative to each other. A cam is carried by the other of the wing and trailing edge device and is positioned within the cam track between the opposing cam track surfaces. The cam is offset from the pivot axis and during normal operation the cam can carry no load or a first load along a load path that includes the cam track, and when a decrease in support provided by at least one of the pivot element, the wing support and the device support occurs, the cam can carry a second non-zero load greater than the first load along the load path.
摘要翻译：公开了追尾设备捕获器和相关联的系统和方法。根据一个实施例的系统包括具有机翼支撑件的机翼，后缘装置，其相对于机翼承载并可移动并具有装置支撑件，以及连接在机翼和后缘装置之间的联轴器。联接器可以包括枢转接头，其包括枢转元件，枢转元件沿着枢转轴线对准并且连接在机翼支撑件和设备支撑件之间。联接器还可以包括联接在翼和后缘装置之间的致动器，其中致动器具有第一位置，在该第一位置中后缘装置被收起，以及第二位置，其中后缘装置被展开，其中空气流当后缘装置处于第二位置时，位于翼和后缘装置之间的间隙。凸轮轨道由机翼和后缘装置中的一个承载，并且具有相对于彼此固定的相对的凸轮轨道表面。凸轮由翼和后缘装置中的另一个承载，并且位于相对的凸轮轨道表面之间的凸轮轨道内。凸轮偏离枢转轴线，并且在正常操作期间，凸轮可以沿着包括凸轮轨道的负载路径承载负载或第一负载，并且当至少一个枢轴元件，翼片支撑和设备支撑发生，凸轮可以承载大于沿着负载路径的第一负载的第二非零负载。

12. 发明申请

WO2008105789A3 INTERNAL FINDER JOINT 审中-公开
标题翻译：内部探测者联合
公开(公告)号：WO2008105789A3
公开(公告)日：2009-03-19
申请号：PCT/US2007014122
申请日：2007-06-14
申请人： BOEING CO , SCHMITZ CHAD D
发明人： SCHMITZ CHAD D
IPC分类号： B64C9/02 , E04C2/292
CPC分类号： E04C2/292 , B64C9/02 , E04B1/6179 , E04B2001/6195 , E04B2002/725 , E04C2/296 , E04C2002/004 , Y02T50/44 , Y10T29/49622 , Y10T29/49826 , Y10T403/7045 , Y10T403/7094 , Y10T428/2419
摘要： To fabricate a joint in a panel (10), a groove (18) is generated and the panel is bent along the groove. The panel includes a first skin (12), second skin (14), and core (16). The core is sandwiched between the first skin and the second skin. The groove passes through the first skin and at least a portion of the core. The groove includes a set of tabs (20) and a corresponding set of slots (22). The set of tabs intermesh with the set of slots in response to bending the panel along the groove.
摘要翻译：为了在面板（10）中制造接头，产生凹槽（18），并且面板沿着凹槽弯曲。面板包括第一皮肤（12），第二皮肤（14）和芯部（16）。芯部夹在第一皮肤和第二皮肤之间。凹槽穿过第一皮肤和芯的至少一部分。凹槽包括一组凸片（20）和相应的一组凹槽（22）。响应于沿着凹槽弯曲面板，该组突片与该组槽相互啮合。

13. 发明申请

WO2008127482A2 STRUCTURAL DYNAMIC STABILITY FOR AN AIRCRAFT 审中-公开
标题翻译：飞机的结构动态稳定性
公开(公告)号：WO2008127482A2
公开(公告)日：2008-10-23
申请号：PCT/US2007/088727
申请日：2007-12-21
申请人： BURGESS, Calvin , BAKER, John
发明人： BURGESS, Calvin , BAKER, John
IPC分类号： B64C9/02
CPC分类号： B64C5/02 , B64C9/02
摘要： An improvement and method for improved structural dynamic stability for 20 and 30 Series Learjets are disclosed. The improvement includes a redistribution of the elevator mass balance to uncouple the elevator rotational motion from the stabilizer translation motion for the higher order horizontal frequencies having node lines in the proximity of the mass outboard counterbalance weights. The original tail section (12) includes a rudder (36), and a horizontal stabilizer (16) supporting an elevator (18) mounted adjacent the rudder. The improved elevator (110) includes a proximal end (132) adjacent the rudder and a distal end (133) that includes a counterbalance portion (120). The improvement further includes replacement of an original mass counterbalance weight from within the counterbalance portion with new mass counterbalance weights (102) of less mass, and the inclusion of the additional mass counterbalance weights disposed within the elevator and interposed between the proximal and distal ends, and the counterbalance portions.
摘要翻译：公开了用于改进20和30系列Learjet的结构动态稳定性的改进和方法。改进包括电梯物料平衡的重新分配，以使电梯旋转运动与高位水平频率的稳定器平移运动分离，所述高阶水平频率在节点外部平衡配重附近具有节点线。原始尾部12包括方向舵36和支撑与方向舵相邻安装的升降机18的水平稳定器16。改进的电梯（110）包括邻近方向舵的近端（132）和包括平衡部分（120）的远端（133）。该改进进一步包括用配重量较小的新质量平衡配重（102）替换配重部分内的原始质量配重，并且包括设置在升降机内并介于近端和远端之间的附加质量配重，和平衡部分。

14. 发明申请

WO2008043164A2 AIRCRAFT RUDDER AUTHORITY CONTROL SYSTEM 审中-公开
标题翻译：飞机RUDDER权限控制系统
公开(公告)号：WO2008043164A2
公开(公告)日：2008-04-17
申请号：PCT/BR2007/000260
申请日：2007-09-25
申请人： EMBRAER-EMPRESA BRASILEIRA DE AERONÁUTICA S.A. , MEINBERG MACEDO, Edwin José , CAVANHA ALMEIDA, Leonardo
发明人： MEINBERG MACEDO, Edwin José , CAVANHA ALMEIDA, Leonardo
IPC分类号： B64C9/04
CPC分类号： B64C9/04 , B64C9/02
摘要： A system that acts on a rudder (L) having its stop parts commanded or moved by an actuator (A) is described. The rudder system comprises a reversible mechanical system with movable stop parts working based on control /command signals, having stop parts (M, M' ) inside of the field of movement of the actuator (A), interfering in the movement of said actuator; the mentioned control signals are based on informations of the aircraft such as traction of the engines or other signal from each engine (pressure, temperature or axis rotation speed); flight speed ("airspeed"); altitude; skidding angle; aircraft on the ground. The system limits the deflection of the rudder in flight with symmetrical traction, enough for normal maneuvers, and it allows total authority of the rudder (L), allowing a larger movement (larger deflection angle) just when necessary, in other words, when there is a traction asymmetry between the engines and, for aircrafts having wheels mechanically connected to the pedals and rudder, when they are maneuvering on the ground during taxi operations.
摘要翻译：描述了作用于具有由致动器（A）指令或移动的停止部件的舵（L）的系统。方向舵系统包括可逆机械系统，其具有基于控制/指令信号工作的可移动停止部件，其具有在致动器（A）的运动区域内的停止部件（M，M'），从而干扰所述致动器的运动; 所提到的控制信号基于飞机的信息，例如发动机的牵引或来自每个发动机的其他信号（压力，温度或轴线转速）; 飞行速度（“空速”）; 高度; 打滑角度飞机在地面上。该系统限制舵在飞行中的对称牵引力的偏转，足以用于正常的机动，并且允许方向舵（L）的完全权威，允许在必要时更大的运动（更大的偏转角），换句话说，当那里是在发动机之间的牵引不对称性，并且对于具有机械连接到踏板和方向舵的轮子的飞机，当他们在出租车操作期间在地面上操纵时。

15. 发明申请

WO2006076018A3 UNITIZED ROTARY ACTUATOR HINGE FITTING 审中-公开
标题翻译：优化的旋转执行器铰链配件
公开(公告)号：WO2006076018A3
公开(公告)日：2006-10-19
申请号：PCT/US2005015595
申请日：2005-05-04
申请人： LOCKHEED CORP , AMBROSE DAVID R
发明人： AMBROSE DAVID R
IPC分类号： B64C3/50
CPC分类号： B64C9/02 , B64C9/22 , B64C13/00
摘要： An apparatus and method for installing a plurality of rotary actuator segments in a device includes a unitary hinge fitting. The unitary hinge fitting includes a first side couplable to a control surface, and a plurality of bays. Each bay is configured to receive at least one of the rotary actuator segments. The unitary hinge fitting reduces the number of components required to install rotary actuators by eliminating the shims, the shear clips, and some of the fasteners required to attach the shims and the shear clips to the hinge fittings. The resulting assembly is typically much simpler and lower in cost and weight than conventional rotary actuator installations.
摘要翻译：用于将多个旋转致动器区段安装在装置中的设备和方法包括整体式铰链配件。整体式铰链配件包括可与控制表面耦合的第一侧和多个隔间。每个隔间构造成接收至少一个旋转致动器部分。整体铰链配件通过消除垫片，剪切夹以及将垫片和剪切夹附接到铰链配件所需的一些紧固件来减少安装旋转致动器所需的部件的数量。与传统的旋转执行器安装相比，所得到的组件通常简单得多，成本和重量更低。

16. 发明申请

WO2006004570B1 FORWARD PIVOTED FULL FLYING CONTROL TAIL BOOM 审中-公开
标题翻译：前进的全部飞行控制尾翼
公开(公告)号：WO2006004570B1
公开(公告)日：2006-04-20
申请号：PCT/US2005001350
申请日：2005-01-18
申请人： NORTHROP GRUMMAN CORP , REYNOLDS ROSS STEVEN , SHULTZ DOUG ELLWOOD
发明人： REYNOLDS ROSS STEVEN , SHULTZ DOUG ELLWOOD
IPC分类号： B64C9/02 , B64C9/08 , B64C13/16 , B64C39/10 , B64C3/58
CPC分类号： B64C9/02 , B64C9/08 , B64C39/10 , Y02T50/12 , Y02T50/32
摘要： An aircraft motion control mechanism for regulating aircraft motion from a location remote from an aircraft body portion. The aircraft auxiliary control mechanism has at least one control surface support arm connected to and extending from the aircraft body portion, and an auxiliary flow control surface connected to the support arm. By pivotally controlling the movement of the support arm, the auxiliary flow control surface is operative to deflect airflow to regulate orientation of the aircraft. In addition, the auxiliary flow control surface may further deflect the airflow by deflecting about the support arm.
摘要翻译：一种用于从远离飞机主体部分的位置调节飞机运动的飞机运动控制机构。飞机辅助控制机构具有至少一个控制表面支撑臂和辅助流动控制表面，所述控制表面支撑臂连接到飞机主体部分并从飞行器主体部分延伸，辅助流动控制表面连接到支撑臂。通过枢转地控制支撑臂的运动，辅助流动控制表面可操作以偏转气流以调节飞行器的定向。另外，辅助流动控制表面可以通过围绕支撑臂偏转来进一步偏转气流。

17. 发明申请

WO2004008097A3 APPARATUS FOR MONITORING AN AIRCRAFT FLAP AND APPLICATION OF A DYNAMOMETRIC ROD 审中-公开
标题翻译：用于监测飞机平面图和应用动态范围的装置
公开(公告)号：WO2004008097A3
公开(公告)日：2004-04-08
申请号：PCT/FR0302231
申请日：2003-07-15
申请人： FGP INSTRUMENTATION , GIBERT FRANCIS
发明人： GIBERT FRANCIS
IPC分类号： B64C9/02 , B64D45/00 , G01L1/22 , G01L5/22 , B64C13/00
CPC分类号： C04B38/103 , B64C9/02 , B64D45/0005 , B64D2045/001 , C04B2103/0028 , C09K8/473 , G01L1/2225 , G01L5/22 , C04B24/16 , C04B24/32 , C04B28/02 , C04B2103/40 , C04B2103/48
摘要： The invention relates to aircraft flap monitoring. More specifically, the invention relates to a dynamometric rod which is intended to form a pivot for fixing a wing flap, said dynamometric rod comprising a cylindrical body (10) with a hexagonal head (12) and a threaded end-piece (14). The dimensions and other characteristics of the body (10), head (12) and end-piece (14) correspond to those of pivots normally used for fixing said wing flaps. The aforementioned body (10) is provided with a groove (16) which can be provided with a small depth of several tenths of a millimetre and which forms a simple gap which prevents contact between a branch of a clamp or an arm of the flap and the rod at the groove (16). In addition, a sensitive element (18) is positioned at the groove and is very tightly sealed closed. The invention is suitable for aircraft flaps.
摘要翻译：本发明涉及飞机翼片监测。更具体地，本发明涉及一种旨在形成用于固定翼片的枢轴的测力杆，所述测力杆包括具有六角头（12）和螺纹端件（14）的圆柱体（10）。主体（10），头部（12）和端部件（14）的尺寸和其他特征对应于通常用于固定翼片的枢轴的尺寸和其他特性。上述主体（10）设置有可以设置有十分之几毫米的小深度的凹槽（16），并且形成一个简单的间隙，该间隙防止了夹子的一个分支或瓣片的一个臂的接触，所述杆在所述凹槽（16）处。此外，敏感元件（18）定位在凹槽处并且被非常紧密地密封封闭。本发明适用于飞机襟翼。

18. 发明申请

WO2017176583A1 ACTUATOR FOR ADAPTIVE AIRFOIL 审中-公开
标题翻译：适应性翼的执行器
公开(公告)号：WO2017176583A1
公开(公告)日：2017-10-12
申请号：PCT/US2017/025375
申请日：2017-03-31
申请人： AVIATION PARTNERS, INC.
发明人： DAVIS, Edward
IPC分类号： B64C3/46 , B64C3/44
CPC分类号： B64C9/18 , B64C3/50 , B64C9/02 , B64C9/16 , B64C13/30 , B64C2003/445
摘要： An apparatus and method for an actuator system to modify an adaptive flap of an aircraft wing. The system may include a drive rod extending from a nose portion of the flap to an interior thereof. A bell crank may be attached to the interior and configured to receive an end of the drive rod. A pivot disposed opposite of the drive rod may couple the bell crank to a mount fixed to a lower surface of a trailing edge portion of the flap. A skin overlap may be configured to allow the lower surface of the trailing edge portion to slide adjacent to a lower surface of a remaining portion of the flap under the action of the drive rod. A bumper may be disposed within the aircraft wing and configured to exert a continuous force on the drive rod when the flap is moved to a retracted state.
摘要翻译：用于致动器系统修改飞机机翼的自适应襟翼的装置和方法。该系统可以包括从护翼的鼻部延伸到其内部的驱动杆。钟形曲柄可以连接到内部并构造成接收驱动杆的一端。布置在驱动杆对面的枢轴可将钟形曲柄连接到固定到翼片的后缘部分的下表面的支架。表皮重叠可以被配置为允许后缘部分的下表面在驱动杆的作用下邻近瓣的其余部分的下表面滑动。保险杠可以设置在飞机机翼内并且被配置成当翼片移动到缩回状态时在驱动杆上施加连续的力。

19. 发明申请

WO2014113464A1 AIRCRAFT FUSELAGE 审中-公开
标题翻译：飞机熔接
公开(公告)号：WO2014113464A1
公开(公告)日：2014-07-24
申请号：PCT/US2014/011670
申请日：2014-01-15
申请人： OTTO, William M.
发明人： OTTO, William M.
IPC分类号： B64C1/00
CPC分类号： B64C25/20 , B64C1/00 , B64C1/065 , B64C1/069 , B64C1/10 , B64C3/185 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/02 , B64C25/10 , B64C25/12 , B64C25/14 , B64C25/18 , B64C25/22 , B64C2025/125 , B64D33/10 , B64D37/04 , F02B37/001 , Y02T50/32 , Y02T50/44
摘要： A fuselage for an airplane including a frame comprising an upper truss and a lower truss extending from a front end of the fuselage towards the rear end of the fuselage, wherein the lower truss comprises one or more forward box beams, a plurality of support rings attached to the upper truss and lower truss, a front bulkhead connected to a first end of the upper truss and lower truss, a main bulkhead connected to the upper truss and lower truss, a pressure vessel adapted to fit within the frame between the front bulkhead and main bulkhead, and a skin adapted to fit over the frame.
摘要翻译：一种用于飞机的机身，包括框架，该框架包括从机身的前端朝向机身的后端延伸的上桁架和下桁架，其中下桁架包括一个或多个前箱梁，多个支撑环连接连接到上桁架和下桁架的前隔板，连接到上桁架和下桁架的第一端的前隔板，连接到上桁架和下桁架的主隔板，适于装配在前隔板和前隔板之间的框架内的压力容器主要隔板和适于装配在框架上的皮肤。

20. 发明申请

WO2014113426A1 AIRCRAFT LANDING GEAR AND METHOD OF OPERATING THE SAME 审中-公开
标题翻译：飞机接地齿轮及其操作方法
公开(公告)号：WO2014113426A1
公开(公告)日：2014-07-24
申请号：PCT/US2014/011602
申请日：2014-01-15
申请人： OTTO, William M.
发明人： OTTO, William M.
IPC分类号： B64C25/34
CPC分类号： B64C25/20 , B64C1/00 , B64C1/065 , B64C1/069 , B64C1/10 , B64C3/185 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/02 , B64C25/10 , B64C25/12 , B64C25/14 , B64C25/18 , B64C25/22 , B64C2025/125 , B64D33/10 , B64D37/04 , F02B37/001 , Y02T50/32 , Y02T50/44
摘要： A main landing gear system for an aircraft including a truss element including a front portion joined to a rear portion, a first support unit and second support unit affixed to the truss at the junction of the first portion and the second portion on opposing sides of the truss, a first actuator and a second actuator rotatively affixed to respective first support unit and second support unit and to a respective first wheel and second wheel, a first trailing link and second trailing link each coupled to the respective first wheel and second wheel.
摘要翻译：一种用于飞行器的主起落架系统，其包括桁架元件，该桁架元件包括接合到后部的前部，第一支撑单元和第二支撑单元，该第一支撑单元和第二支撑单元在第一部分和第二部分的接合处固定到桁架桁架，第一致动器和第二致动器，其旋转地固定到相应的第一支撑单元和第二支撑单元以及相应的第一轮和第二轮，第一牵引杆和第二牵引杆，每个联接到相应的第一轮和第二轮。

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