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51. 发明公开

EP3251946A1 AUTOMATIC FLIGHT CONTROL ACTUATOR SYSTEMS 审中-公开
标题翻译：自动飞行控制执行器系统
公开(公告)号：EP3251946A1
公开(公告)日：2017-12-06
申请号：EP17170302.8
申请日：2017-05-09
申请人： Honeywell International Inc.
发明人： WILKENS, Dean
IPC分类号： B64C13/24 , B64C13/34 , F16H49/00
CPC分类号： F16H49/001 , B64C13/04 , B64C13/18 , B64C13/24 , B64C13/28 , B64C13/34 , B64C27/605
摘要： An automatic actuator system is provided. The automatic actuator system includes an input linkage that receives an input and an output linkage adapted to control a flight surface actuator. The automatic actuator system includes a first strain wave gear having a first circular spline coupled to the input linkage and a first flex spline rotatably coupled to the first circular spline. The automatic actuator system includes a second strain wave gear having a second circular spline coupled to the first flex spline. The second strain wave gear includes a second flex spline, and the second flex spline is coupled to the output linkage such that at least a portion of the input from the input linkage is transferred to the output linkage via the first strain wave gear and the second strain wave gear.
摘要翻译：提供自动致动器系统。该自动致动器系统包括输入联动装置，该输入联动装置接收适于控制飞行表面致动器的输入和输出联动装置。自动致动器系统包括第一应变波动齿轮，第一应变波动齿轮具有耦合到输入连杆的第一圆形花键和可旋转地耦合到第一圆形花键的第一柔性花键。该自动致动器系统包括第二应变波齿轮，该第二应变波齿轮具有耦合到第一柔性花键的第二圆形花键。第二应变波动齿轮包括第二挠性齿条，并且第二挠曲齿条联接到输出联动件，使得来自输入联动件的输入的至少一部分经由第一应变波动齿轮和第二应变波动齿轮传递到输出联动件应变波齿轮。

52. 发明授权

EP2987722B1 ROTORCRAFT AUTOPILOT CONTROL 有权
标题翻译： DREHFLÜGLERAUTOPILOTSTEUERUNG
公开(公告)号：EP2987722B1
公开(公告)日：2017-03-29
申请号：EP15181829.1
申请日：2015-08-20
申请人： Bell Helicopter Textron Inc.
发明人： GRIFFITH, Carl D. , ATKINS, Brady G. , RAZA, Awais , WILSON, Paul M.
IPC分类号： B64C13/08 , B64C13/18 , B64C13/30 , B64C27/04 , B64C27/56 , B64C27/57 , B64C27/58
CPC分类号： B64C27/57 , B64C13/08 , B64C13/18 , B64C13/30 , B64C27/04 , B64C27/56 , B64C27/58

53. 发明授权

EP2963518B1 PROCÉDÉ ET SYSTÈME DE MISE EN VOL STATIONNAIRE D'UN AÉRONEF À VOILURE TOURNANTE EN TENUE DE TRAJECTOIRE OU TENUE DE CAP SELON SA VITESSE D' AVANCEMENT 有权
标题翻译：方法和系统用于实现与轨道的飞机维修，或课程一荡稳定飞行状况，根据进纸速度
公开(公告)号：EP2963518B1
公开(公告)日：2017-03-15
申请号：EP15172660.1
申请日：2015-06-18
申请人： Airbus Helicopters
发明人： SALESSE-LAVERGNE, Marc
IPC分类号： G05D1/08 , G05D1/10 , B64C13/18 , B64C27/02
CPC分类号： B64C13/18 , B64C27/04 , G05D1/0858 , G05D1/102

54. 发明授权

EP2671796B1 Procédé de commandes de vol automatisées pour giravion, procurant une tenue de trajectoire du giravion par suivi de commandes de vol manuelles 有权
标题翻译：一种用于旋翼式飞机的自动化飞行控制系统，其产生通过跟踪手动飞行控制命令保持旋翼飞行器的飞行路径的方法
公开(公告)号：EP2671796B1
公开(公告)日：2017-03-15
申请号：EP13002644.6
申请日：2013-05-21
申请人： Airbus Helicopters
发明人： Certain, Bernard
IPC分类号： B64C13/18 , G05D1/00
CPC分类号： G05D1/0808 , B64C13/18 , B64C27/57 , G05D1/0858 , G05D1/102

55. 发明公开

EP3126231A1 ELEVATOR LOAD ALLEVIATING CONTROL FOR A ROTARY WING AIRCRAFT 有权
标题翻译： HÖHENRUDERLASTREDUZIERUNGSSTEUERUNGFÜREINDREHFLÜGELFLUGZEUG
公开(公告)号：EP3126231A1
公开(公告)日：2017-02-08
申请号：EP14888084.2
申请日：2014-04-02
申请人： Sikorsky Aircraft Corporation
发明人： ELLER, Erez , GREENFIELD, Aaron L. , WULFF, Ole , WHITE, Matthew A. , LUSZCZ, Matthew T.
IPC分类号： B64C27/00
CPC分类号： B64C13/503 , B64C13/18 , B64C27/08 , B64C27/10 , B64C27/57 , B64C27/82 , B64C2027/8236 , B64C2027/8272 , B64C2027/8281 , Y02T50/44
摘要： One aspect is a flight control system for a rotary wing aircraft including a main rotor system and an elevator control system. A flight control computer of the flight control system includes processing circuitry configured to execute control logic. The control logic includes an inverse plant model that produces a main rotor feed forward command based on a pitch rate command, and a load alleviation control filter configured to reduce loads on a main rotor system and produce an elevator command for an elevator control system. A transformed elevator command filter produces a main rotor pitch adjustment command based on the elevator command, and a main rotor command generator generates an augmented main rotor feed forward command for the main rotor system based on the main rotor feed forward command and the main rotor pitch adjustment command.
摘要翻译：一个方面是用于包括主转子系统和电梯控制系统的旋翼飞机的飞行控制系统。飞行控制系统的飞行控制计算机包括配置成执行控制逻辑的处理电路。控制逻辑包括基于俯仰速率指令产生主转子前馈命令的逆电厂模型，以及负载减轻控制滤波器，其被配置为减小主转子系统上的负载并产生电梯控制系统的电梯命令。变换后的电梯指令滤波器基于电梯命令产生主转子音调调整指令，主转子指令发生器基于主转子前馈指令和主转子间距产生主转子系统的增大主转子前馈指令调整指令。

56. 发明公开

EP3101504A3 GUST COMPENSATION SYSTEM AND METHOD FOR AIRCRAFT 审中-公开
标题翻译：超声波流量计
公开(公告)号：EP3101504A3
公开(公告)日：2017-01-11
申请号：EP16172697.1
申请日：2016-06-02
申请人： The Boeing Company
发明人： ABDEL-MOTAGALY, Khaled , CAICEDO, Rafael E. , DALLARA, Christopher D. , HO, Alexander C. , KIOUMARS, Najmabadi , SIU, Tze L. , STREFLING, Paul C. , YAMASHIRO, Hisako
IPC分类号： G05D1/04 , B64C13/16
CPC分类号： G05D1/0825 , B64C13/16 , B64C13/18 , B64D2700/62228 , G05D1/0066
摘要： A gust compensation system 200 is configured to adaptively reduce gust loads exerted into an aircraft 100/500. The gust compensation system may include a first sensor 110 proximate to a front of the aircraft 100. The first sensor 110 is configured to output a first signal. A second sensor 120 may be distally located from the front of the aircraft 100. The second sensor 120 is configured to output a second signal. A gust signal sub-system 202 is configured to receive the first and second signals and generate a gust signal 226 based on analysis of the first and second signals. The gust signal sub-system 202 outputs the gust signal 226 and may modify a load parameter signal 220 in response to the gust signal 226 exceeding a load alleviation threshold.
摘要翻译：阵风补偿系统200被配置为自适应地减小施加到飞行器100/500中的阵风负载。阵风补偿系统可以包括靠近飞行器100的前部的第一传感器110.第一传感器110被配置为输出第一信号。第二传感器120可以从飞机100的前部向远侧定位。第二传感器120被配置为输出第二信号。阵风信号子系统202被配置为基于第一和第二信号的分析来接收第一和第二信号并产生阵风信号226。阵风信号子系统202输出阵风信号226，并且可以响应于阵风信号226超过负载减轻阈值来修改负载参数信号220。

57. 发明公开

EP2812764A4 AUTOPILOT AND METHODS 审中-公开
标题翻译： AUTO PILOT和程序
公开(公告)号：EP2812764A4
公开(公告)日：2016-07-06
申请号：EP13787117
申请日：2013-02-08
申请人： MERLIN TECHNOLOGY INC
发明人： ALBION NICOLAS , BARTEL MARK , FEIFEL MARC , MARVIN MARK , MERCER JOHN
IPC分类号： B64C13/18 , B64C13/42 , B64C27/04 , B64C27/56 , B64C27/57 , B64C27/64 , B64C27/68 , G05D1/08 , G05D1/10
CPC分类号： B64C27/57 , B64C13/18 , B64C13/42 , B64C27/56 , B64C27/59 , B64C27/64 , B64C27/68 , G05D1/0077 , G05D1/0816 , G05D1/0858 , G05D1/102 , Y02T50/44
摘要： A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

58. 发明公开

EP2793096A2 Flight system for an aircraft having an autoland system 审中-公开
标题翻译： Flugsystemfürein Flugzeug mit einem automatischen Landesystem
公开(公告)号：EP2793096A2
公开(公告)日：2014-10-22
申请号：EP14164125.8
申请日：2014-04-10
申请人： GE Aviation Systems LLC
发明人： Ali, Sherif Fouad
IPC分类号： G05D1/00 , B64D45/00
CPC分类号： G08G5/02 , B64C13/18 , B64D45/04 , G05D1/0676 , Y02T50/44
摘要： A method and system for operating an aircraft having an autoflight system (10) comprising flight guidance functionality and autoland functionality providing input to a flight control system (34) such that both the autoflight and autoland functionality and their corresponding systems (10, 20) are operated at a Design Assurance Level A.
摘要翻译：一种用于操作具有自动飞行系统（10）的飞行器的方法和系统，该飞行器系统（10）包括飞行引导功能和向飞行控制系统（34）提供输入的自动归零功能，使得自动飞行和自动功能及其对应的系统（10,20）在设计保证级别A下运行。

59. 发明公开

EP2516261A2 AIRCRAFT WITH A CONTROL DEVICE 有权
标题翻译：与控制装置PLANE
公开(公告)号：EP2516261A2
公开(公告)日：2012-10-31
申请号：EP10803243.4
申请日：2010-12-23
申请人： Airbus Operations GmbH
发明人： GÖLLING, Burkhard , HAUCKE, Frank , BAUER, Matthias , NITSCHE, Wolfgang , PELTZER, Inken
IPC分类号： B64C9/18 , B64C13/00
CPC分类号： B64C23/005 , B64C9/16 , B64C9/38 , B64C13/18 , B64C21/04 , B64C29/0025 , Y02T50/166
摘要： An aircraft (F) with aerofoils (1a, 1b) comprising a main wing (M) and at least one control flap (S) that is arranged so as to be adjustable relative to the aforesaid, and comprising at least one adjustment flap (K), with the aircraft comprising: - an actuator (21 ) for operating the at least one control flap (S), as well as a sensor device (24) for acquiring the set position of the control flap (S), - at least one arrangement (15; 15K) of flow-influencing devices (16; 16K), which extends on the main wing (M) and/or of at least one adjustment flap (K) of each aerofoil (M; 1a, 1b), for the purpose of influencing the fluid that flows over the surface segment (10; 10K) and - at least one arrangement of flow-state sensor devices (17; 17K) for measuring the flow state on the respective segment (10; 11a, 12a; 11b, 12b), - a flight control device (50) which on the input side is functionally connected to the sensor device (24) for acquiring the set position of the control flap (S) and to the flow-state sensor devices (16; 16K) and which flight control device (50) for the purpose of transmitting actuating commands (50a) on the output side is functionally connected to the actuator (21) and the flow-influencing devices (16;16K), - a flight-state sensor device (40) functionally connected to the flight control device (50) for transmitting flight states, wherein the flight control device (50) comprises a function that for the purpose of optimising local lift coefficients on the aerofoil depending on the flight state carries out a selection of the flow-influencing devices (16; 16K) that are to be operated.

60. 发明公开

EP2257469A1 PROCÉDÉ ET DISPOSITIF POUR LA DÉTECTION D'ABSENCES DE PILOTAGE MANUEL ET AUTOMATIQUE D'UN AÉRONEF 审中-公开
标题翻译：方法和设备手动或自动空气控制的检测失败
公开(公告)号：EP2257469A1
公开(公告)日：2010-12-08
申请号：EP09729507.5
申请日：2009-03-23
申请人： Airbus Opérations SAS
发明人： DEHAIS, Frédéric
IPC分类号： B64C13/18 , B64D45/00 , G05D1/00 , G08B21/00
CPC分类号： B64C13/18 , G05D1/0061 , G08G5/025
摘要： According to the invention, as a function of the altitude, the vertical speed and the heading of the aircraft, as well as of the deviation of the actual trajectory of the aircraft with respect to the automatic trajectory, a time interval (T) is determined, during which it is tolerable for said aircraft to be able to fly without any control command, both on the part of the stick (1) and on that of said automatic pilot (2) and an alert is emitted for the attention of the crew in the case where it is noted that the absences of manual piloting and of automatic piloting extend simultaneously over a duration at least equal to said time interval (T).
摘要翻译：。根据本发明，随着海拔高度的函数，垂直速度和飞行器的航向，以及飞行器的实际轨迹的相对于所述自动轨迹的偏差的，时间间隔（T）是确定性的矿洞，这期间它是可以容忍的说飞机能够在没有任何控制命令飞，双方在棍子的部分（1）和没有说自动驾驶（2）和警报的发出对船员的关注在值得注意的是没有手动驾驶的缺勤和自动驾驶的情况下，同时上延伸的持续时间至少等于所述调间隔（T）。

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