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71. 发明授权

US6076767A Flight control surface actuation system 失效
标题翻译：飞行控制面驱动系统
公开(公告)号：US6076767A
公开(公告)日：2000-06-20
申请号：US931670
申请日：1997-09-17
申请人： Brian Farley , Antony Morgan , Arthur Derek Mountney , Timothy Robert Matthews
发明人： Brian Farley , Antony Morgan , Arthur Derek Mountney , Timothy Robert Matthews
IPC分类号： B64C13/40 , B64C13/38 , B64D45/00 , F15B11/22 , B64C13/36
CPC分类号： F15B11/22 , B64C13/38 , B64D45/0005 , B64D2045/001
摘要： A flight control surface actuation system is provided in which a plurality of actuators (6-13) are connected to one another in order to synchronize their operation. Each actuator has its own gearbox such that the torque transmitted in the synchronizing element is kept low.
摘要翻译：提供了一种飞行控制表面致动系统，其中多个致动器（6-13）彼此连接以便使其操作同步。每个致动器具有其自己的变速箱，使得在同步元件中传递的扭矩保持为低。

72. 发明授权

US5686907A Skew and loss detection system for individual high lift devices 失效
标题翻译：用于单个高升力装置的倾斜和损失检测系统
公开(公告)号：US5686907A
公开(公告)日：1997-11-11
申请号：US442208
申请日：1995-05-15
申请人： Jeffrey C. Bedell , Wayne M. Berta
发明人： Jeffrey C. Bedell , Wayne M. Berta
IPC分类号： B64D45/00 , G08B21/00
CPC分类号： B64D45/0005 , B64D2045/001
摘要： This invention is a method and apparatus for determining whether or not auxiliary airfoils on an aircraft wing are skewed or lost. It employs either of two types of systems and their associated computer monitor and control requirements. One system utilizes a cable and a spring-loaded mechanism with a cable displacement position sensor. The second system utilizes a drive system position sensor, proximity sensors and segmented proximity targets. These two systems are capable of skew and loss detection for adjacent or individual auxiliary airfoil arrangements. A computer electronic unit is used to perform logic functions to verify the authenticity of sensor signals, and, if appropriate, to shut down the drive system and to compute new flight control parameters including those relating to stall speed and the stick shaker, while alerting the flight crew.
摘要翻译：本发明是用于确定飞机机翼上的辅助翼型是否偏斜或丢失的方法和装置。它采用两种类型的系统及其相关的计算机监视和控制要求。一个系统利用电缆和带有电缆位移传感器的弹簧加载机构。第二个系统采用驱动系统位置传感器，接近传感器和分段接近目标。这两个系统能够对相邻或各个辅助翼型装置进行偏斜和损耗检测。计算机电子单元用于执行逻辑功能以验证传感器信号的真实性，并且如果合适的话，关闭驱动系统并计算新的飞行控制参数，包括与失速速度和摇杆振荡器相关的参数，同时警告机组人员。

73. 发明授权

US5422794A Aircraft bag-rack with an illuminated handrail 失效
标题翻译：带有照明扶手的飞机包架
公开(公告)号：US5422794A
公开(公告)日：1995-06-06
申请号：US245166
申请日：1994-05-17
申请人： Samuel M. Drake
发明人： Samuel M. Drake
IPC分类号： B60Q3/02 , B64D11/00 , E04F11/18 , G08B5/36 , B60Q1/00
CPC分类号： B64D45/0005 , B60Q3/0233 , B60Q3/025 , B64D11/00 , G08B7/066 , B64D2011/0038 , B64D2011/0053 , B64D2045/001 , E04F2011/1872
摘要： A bag-rack mounted on an aircraft ceiling has a handrail secured to a recessed lower front portion thereof by a mount which also spaces the handrail from the bag-rack. The handrail is dimensionally shaped to conform to the inner surface contours of a user's hand and the recessed portion is curved to accommodate the back of the user's hand when reach into the recessed area to grip the handrail. The handrail also has an electroluminescent panel light mounted in a channel therein. The channel and light are positioned so that the light illuminates the recessed portion of the bag-rack and back-illuminates the handrail. The back-illumination of the handrail and the color contrast between the bag-rack and handrail provide visual differentiation between the handrail and bag-rack as well as other nearby structures enabling the user to more easily discern the handrail from other vehicle structures.
摘要翻译：安装在飞行器天花板上的行李架具有通过安装件固定到其下部前部的扶手，扶手还将扶手与行李架隔开。扶手的尺寸形状与使用者的手的内表面轮廓相符合，并且凹陷部分弯曲以在到达凹陷区域时夹紧使用者的手背以夹紧扶手。扶栏还具有安装在其中的通道中的电致发光面板灯。通道和光被定位成使得光照亮袋架的凹陷部分并且背面照亮扶手。扶手的背部照明以及行李架和扶手之间的颜色对比提供了扶手和行李架以及其他附近结构之间的视觉差异，使得用户能够更容易地从其他车辆结构识别扶手。

74. 发明授权

US4494716A Wing flap assembly and aircraft provided therewith 失效
标题翻译：翼翼组件和提供的飞行器
公开(公告)号：US4494716A
公开(公告)日：1985-01-22
申请号：US459101
申请日：1983-01-19
申请人： Cornelis A. Breedveld , Frans W. de Haan
发明人： Cornelis A. Breedveld , Frans W. de Haan
IPC分类号： B64C9/16 , B64D45/00 , B64C9/00
CPC分类号： B64D45/0005 , B64C9/16 , B64D2045/001
摘要： A wing flap assembly, in which each flap (1, 2) has its own suspension and drive mechanism (3-6) and in which two adjacent flaps substantially in line with each other have a part (16) connected for movement with one flap and extending between two abutments (18, 19) on the other flap so that, in case of a failure or disturbance in the suspension and drive mechanism of one flap, this flap is limited in movement with respect to the adjacent flap to avoid serious distorsions and other dangerous consequences of such a failure or disturbance. Preferably the part (16) extending between the abutments is a pivoting lever, so connected to one flap that it moves therewith in a plane substantially parallel to the chord plane (8) of the flaps if one flap moves with respect to the other one. Moreover, the abutments (18, 19) have adjacent switches (20, 21), so that the part (16) extending between the abutments contacts one of these switches if one flap moves too far with respect to the other flap, so as to give a warning signal about a disturbance or failure and to stop movement of the driving mechanism for the flaps.
摘要翻译：一种翼片组件，其中每个翼片（1,2）具有其自己的悬挂和驱动机构（3-6），并且其中两个相邻的翼片基本上彼此成一直线，具有连接用于与一个翼片一起运动的部分（16）并且在另一个翼片上的两个支座（18,19）之间延伸，使得在一个翼片的悬挂和驱动机构的故障或干扰的情况下，该翼片相对于相邻翼片的运动受到限制，以避免严重的变形以及这种失败或干扰的其他危险后果。优选地，在邻接处之间延伸的部分（16）是枢转杆，如果一个翼片相对于另一个翼片移动，则连接到一个翼片，其在与翼片的弦平面（8）基本平行的平面中随之移动。此外，邻接部（18,19）具有相邻的开关（20,21），使得如果一个翼片相对于另一个翼片移动得太远，则在邻接部之间延伸的部分（16）接触这些开关中的一个，从而给出关于扰动或故障的警告信号，并停止用于襟翼的驱动机构的运动。

75. 发明授权

US4441675A High lift surface actuation system 失效
标题翻译：高升力面驱动系统
公开(公告)号：US4441675A
公开(公告)日：1984-04-10
申请号：US392356
申请日：1982-06-25
申请人： Wilfred E. Boehringer , Teunes Verhoeven
发明人： Wilfred E. Boehringer , Teunes Verhoeven
IPC分类号： B64C13/24 , B64C3/50 , F16H1/44 , G05D1/00
CPC分类号： B64D45/0005 , B64C13/24 , B64D2045/001
摘要： A drive system for high-lift devices on aircraft having two power drive units, one at each end of the connecting torque tube system, so as to force sum the outputs. A one-way brake always insures against inadvertent retraction of the device but allows extension. An asymmetrical protective device prevents the high-lift device from an asymmetrical condition even after a combined power loss and mechanical failure of the torque tube. The power drive units consist of hydraulic motors driving through a gear box and a no-back brake combination and are controlled by a servo valve.
摘要翻译：一种用于飞机上的高升程装置的驱动系统，具有两个动力驱动单元，一个在连接扭矩管系统的每一端，以便将输出加和。单向制动器始终确保设备的意外收回，但允许扩展。即使在扭矩管的组合功率损失和机械故障之后，不对称的保护装置防止高升力装置处于非对称状态。动力驱动单元由通过齿轮箱驱动的液压马达和无回刹车组合组成，并由伺服阀控制。

76. 发明授权

US4260121A Drive arrangement for lift control surfaces on all aircraft wings 失效
标题翻译：所有飞机机翼上的电梯控制面的驱动装置
公开(公告)号：US4260121A
公开(公告)日：1981-04-07
申请号：US852823
申请日：1977-11-18
申请人： Trevor A. J. Baston , John R. Wynne
发明人： Trevor A. J. Baston , John R. Wynne
IPC分类号： B64C13/00 , B64C13/16 , B64C19/00
CPC分类号： B64D45/0005 , B64C13/16 , B64D2045/001 , Y10T477/813
摘要： A drive arrangement for lift control surfaces on an aircraft wing has a drive motor and a shaft for transmitting motion from the motor to the lift control surfaces. A control circuit is responsive to the driving positions of both the motor and the shaft, and is responsive to a predetermined level of discrepancy between these positions to operate one or more braking devices which restrain the shaft against movement.
摘要翻译：用于飞机机翼上的升降机控制表面的驱动装置具有驱动马达和用于将运动从马达传递到升降控制表面的轴。控制电路响应于电动机和轴的驱动位置，并且响应于这些位置之间的预定水平的差异来操作一个或多个限制轴的运动的制动装置。

77. 发明公开

US20240253818A1 DETERMINING AIRCRAFT STEERING ANGLE 审中-公开
公开(公告)号：US20240253818A1
公开(公告)日：2024-08-01
申请号：US18428495
申请日：2024-01-31
申请人： AIRBUS OPERATIONS LIMITED
发明人： Ting Yu AU
IPC分类号： B64D45/00 , G01S7/48 , G01S17/08 , G01S17/89 , G01S17/933
CPC分类号： B64D45/0005 , G01S7/4808 , G01S17/08 , G01S17/89 , G01S17/933
摘要： A computer-implemented method of determining a steering angle of an aircraft landing gear is disclosed including obtaining a set of position data points, wherein the set of position data points comprises position data points of a component of the aircraft landing gear and calculating a centroid of the set of position data points. The method also includes determining an angle of an intersection between a straight line that passes through both the centroid and an axis of rotation of the aircraft landing gear and an axis that is orthogonal to a strut of the aircraft landing gear when the aircraft landing gear is at a previously known steering angle, and determining the steering angle of the aircraft landing gear based on the determined angle of intersection.

78. 发明公开

US20240253816A1 METHOD AND SYSTEM FOR MONITORING OPERATIONS OF LANDING GEARS OF AIRCRAFT 审中-公开
公开(公告)号：US20240253816A1
公开(公告)日：2024-08-01
申请号：US18425142
申请日：2024-01-29
申请人： Airbus SAS
发明人： Cameron Graeme COOKE
IPC分类号： B64D45/00 , B64F5/60 , G06N20/00
CPC分类号： B64D45/0005 , B64F5/60 , G06N20/00
摘要： A method for providing an operational state of a monitored landing gear of an aircraft by: obtaining in real-time captured signals, such as images, of an actual position of the monitored landing gear; transforming the captured signals in a descriptor vector using Principal Components Analysis; injecting the descriptor vector in a machine learning-based model trained and configured to transform descriptor vectors into equivalent operational states of landing gears; and providing the operational state of the monitored landing gear to avionics of the aircraft.

79. 发明授权

US11987380B2 Control surface element skew and/or loss detection system 有权
公开(公告)号：US11987380B2
公开(公告)日：2024-05-21
申请号：US16973883
申请日：2019-05-30
申请人： Moog Wolverhampton Limited
发明人： Glynn Thomas
IPC分类号： B64D45/00 , G01L5/10
CPC分类号： B64D45/0005 , G01L5/10 , B64D2045/001
摘要： An aircraft control surface skew and/or loss detection system including an aircraft wing structure having a fixed part and at least two control surface elements wherein the at least two control surface elements are configured to be moveable relative to the fixed part. The detection system also includes a cable operably connected to each of the at least two control surface elements such that a tensile force is applied to the cable upon skew and/or loss of one of the control surface elements. The detections system has a sensor assembly including a first part and a second part, wherein one of the first and second parts has a sensor and wherein the cable is coupled to the second part such that skew and/or loss of one of the control surface elements causes movement of the second part relative to the first part. The sensor is configured to detect a first relative position of the first and second parts indicative of the wing structure supporting a load, and a second relative position of the first and second parts indicative of the wing structure being supported.

80. 发明授权

US11880211B2 Landing gear deployment 有权
公开(公告)号：US11880211B2
公开(公告)日：2024-01-23
申请号：US17985002
申请日：2022-11-10
申请人： AIRBUS OPERATIONS LIMITED
发明人： Fraser Wilson
IPC分类号： G05D1/06 , B64C25/28 , B64D45/00 , B64D45/04 , B64C25/00 , B64C25/26 , B64C25/10 , B64C25/30
CPC分类号： G05D1/0676 , B64C25/28 , B64D45/0005 , B64D45/04 , B64C25/10 , B64C25/26 , B64C25/30 , B64C2025/003
摘要： An aircraft controller configured to determine a period and/or distance over which deployment of a landing gear can be initiated for landing including a determined first portion during which landing gear deployment can be safely initiated and a determined second portion, closer to aircraft landing than the first portion, during which the landing gear deployment can be safely initiated in an efficient landing mode; issue a first pilot feedback when the first portion is entered by the aircraft; issue a second pilot feedback when the second portion of the determined; and initiate landing gear deployment when the aircraft is in the determined period and/or distance in response to receiving a deployment signal from the pilot.

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