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1. 发明申请

WO2012031759A3 ACTUATION SYSTEM FOR AN ADJUSTABLE AIRCRAFT FLAP AND METHOD FOR RECONFIGURING THE ACTUATION SYSTEM 审中-公开
标题翻译：可调节飞行器飞行器的执行系统和重新启动执行系统的方法
公开(公告)号：WO2012031759A3
公开(公告)日：2012-05-31
申请号：PCT/EP2011004527
申请日：2011-09-08
申请人： AIRBUS OPERATIONS GMBH , RECKSIEK MARTIN , HEINTJES MARK , WINKELMANN CHRISTOPH
发明人： RECKSIEK MARTIN , HEINTJES MARK , WINKELMANN CHRISTOPH
IPC分类号： B64D45/00
CPC分类号： B64D45/0005 , B64D2045/001
摘要： The invention pertains to an actuation system of an aircraft that comprises a function for monitoring a guiding device (A11, A12, B11, B12, A21, A22, B21, B22) of a regulating flap (K; A1, A2; B1, B2) with a load sensor (S1; S2), wherein the monitoring device (5) comprises an interface to the load sensor (S1; S2) and an interface to a driving device (P; PA1, PA2, PB1, PB2) for adjusting the regulating flap, wherein the monitoring device (5) is realized in such a way that it determines or receives in-flight information that actively signals a predefined flight attitude and/or a predefined operational state of the aircraft, wherein the monitoring device (5) comprises: a comparing function for carrying out a comparison between a load value that corresponds to a sensor value acquired by the load sensor and a limiting value that corresponds to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function, and wherein the monitoring function is realized in such a way that it assigns a fault mode to the regulating flap if this limiting value corresponding to the minimum operational load is not reached. The invention furthermore pertains to a method for reconfiguring such an actuation system.
摘要翻译：本发明涉及飞机的致动系统，其包括用于监视调节翼片（K; A1，A2; B1，B2）的引导装置（A11，A12，B11，B12，A21，A22，B21，B22）），其中所述监测装置（5）包括与所述负载传感器（S1; S2）的接口和与驱动装置（P; PA1，PA2，PB1，PB2）的接口，用于调节所述调节翼片，其中所述监视装置（5）以这样的方式被实现，即其确定或接收主动发出飞行器的预定飞行姿态和/或预定义操作状态的飞行中信息，其中所述监视装置（5 ）包括：比较功能，用于执行对应于由负载传感器获取的传感器值的负载值与对应于预定飞行姿态的最小操作负载的限制值和/或预定义的操作状态飞机和监控功能，以及其中，如果没有达到对应于最小操作负载的极限值，则以这样的方式实现监视功能，即将故障模式分配给调节挡板。本发明还涉及一种用于重新配置这种致动系统的方法。

2. 发明申请

WO2012000664A3 ADJUSTMENT SYSTEM OF AN AEROPLANE WITH AN ADJUSTABLE FLAP 审中-公开
标题翻译：调整系统的飞机带有可调整的皮瓣
公开(公告)号：WO2012000664A3
公开(公告)日：2012-03-08
申请号：PCT/EP2011003203
申请日：2011-06-29
申请人： AIRBUS OPERATIONS GMBH , RECKSIEK MARTIN , ELLMERS WILFRIED , WINKELMANN CHRISTOPH
发明人： RECKSIEK MARTIN , ELLMERS WILFRIED , WINKELMANN CHRISTOPH
IPC分类号： B64D45/00 , B64C9/16
CPC分类号： B64C13/28 , B64C9/16 , B64D45/0005 , B64D2045/001 , Y02T50/44
摘要： An adjustment system of an aeroplane, having: at least one adjustable flap (A1, A2; B1, B2) on each of the wing of an aeroplane, adjustable with an adjustment device (A11, A12, B11, B12, A21, A22, B21, B22), a drive device (PA1, PA2, PB1, PB2) for purposes of driving the adjustment devices (A11, A12, B11, B12, A21, A22, B21, B22), and a load sensor (S-D) for purposes of recording the load occurring in the load path between the actuator and the adjustable flap of the respective adjustment device. The load sensor (S-D) is embodied as a sensor for purposes of measuring the longitudinal force occurring in a drive rod along its longitudinal direction (L1).
摘要翻译：具有以下特征的飞机调节系统：在飞机的每个机翼上至少有一个可调节襟翼（A1，A2; B1，B2），可通过调节装置（A11，A12，B11，B12，A21，A22， B21，B22），用于驱动调整装置（A11，A12，B11，B12，A21，A22，B21，B22）的驱动装置（PA1，PA2，PB1，PB2）用于记录致动器与相应调节装置的可调节襟翼之间的负载路径中发生的负载。负载传感器（S-D）构造为用于测量驱动杆沿其纵向方向（L1）上产生的纵向力的传感器。

3. 发明申请

WO2008141792A4 METHOD AND DEVICE FOR FAULT DETECTION IN THE LOAD PATH OF A SPINDLE ACTUATOR 审中-公开
标题翻译：用于在主动执行器的负载路径中故障检测的方法和装置
公开(公告)号：WO2008141792A4
公开(公告)日：2009-02-12
申请号：PCT/EP2008004004
申请日：2008-05-19
申请人： AIRBUS GMBH , EADS DEUTSCHLAND GMBH , BRUECKNER INA , GIEBELER CHRISTOPH , HEINTJES MARK , RECKSIEK MARTIN , RECHTER HARALD , CHRISTMANN MARKUS
发明人： BRUECKNER INA , GIEBELER CHRISTOPH , HEINTJES MARK , RECKSIEK MARTIN , RECHTER HARALD , CHRISTMANN MARKUS
IPC分类号： F16H25/20 , B64C13/50 , B64D45/00
CPC分类号： B64C13/28 , F16H25/2021 , F16H25/205
摘要： The invention relates to a method and a device for fault detection in the load path of a spindle actuator which is provided for actuating an aerodynamically active surface, in particular a high- lift surface (1, 2) of an aircraft, wherein the spindle actuator (3) has a redundant load path which is formed by a spindle (11) and a concentrically arranged secondary connection (21) which are connected rotationally fixedly to one another on the driven side and are coupled to the surface (1, 2) to be actuated and which are assigned separate load paths (10, 20) on the drive side, whereof the primary load path (10) contains a primary spindle (11) which can be driven by a motor (14) and can be fixed in its rotational movement by a primary brake (13), and the secondary load path (20) contains the secondary inner connection (21), which can be fixed in its rotational movement by a secondary brake (23), and comprising at least one turning position sensor (15) which is provided on the drive side with the primary spindle (11) for generating output signals representing the turning position of the spindle (11). According to the invention, it is provided to fix the secondary connection (21) in its rotational movement by means of the secondary brake (23) and when the primary brake (13) is released, put the redundant load path (10, 20) under load with a predefined torque by the motor (4) driving the primary spindle (11) via the driven- side rotationally fixed connection (29) of the primary spindle (11) and the secondary connection (21) as far as the secondary brake (23) fixing the secondary connection (21), and when a change in the turning position which lies outside the tolerance range predefined for an intact spindle actuator, is detected at the turning position sensor (15) coupled to the primary spindle (11), to deliver an output signal indicating the detection of a fault.
摘要翻译：本发明涉及一种在主轴致动器的负载路径中进行故障检测的方法和装置，其被设置用于致动空中动力学活动表面，特别是飞行器的高升程表面（1,2），其中所述主轴致动器（3）具有由主轴（11）和同轴布置的次级连接件（21）形成的冗余载荷路径，所述第二连接件在驱动侧上彼此旋转地固定连接并且联接到所述表面（1,2）至被驱动并且在驱动侧上分配有单独的负载路径（10,20），其中主负载路径（10）包含可由电动机（14）驱动的主轴（11），并且可以固定在主轴通过主制动器（13）的旋转运动，并且次级负载路径（20）包含辅助内部连接件（21），该二次内部连接件可以通过辅助制动器（23）固定在其旋转运动中，并且包括至少一个转动位置传感器（15），其设置在驱动侧主轴（11），用于产生表示主轴（11）的转动位置的输出信号。根据本发明，提供了通过二次制动器（23）将二次连接件（21）固定在其旋转运动中，并且当主制动器（13）被释放时，将冗余负载路径（10,20）通过电动机（4）经由主主轴（11）和辅助连接件（21）的从动侧可旋转地固定的连接（29）驱动主轴（11）的预定义转矩直到二次制动（23），固定所述二次连接件（21），并且当在与所述主轴（11）连接的所述转动位置传感器（15）处检测到对于完整主轴致动器预定的所述公差范围之外的转动位置的变化时，，以传递指示故障检测的输出信号。

4. 发明申请

WO2011057817A3 FLAP ADJUSTING SYSTEM OF AN AIRCRAFT WITH A REGULATING FLAP 审中-公开
标题翻译：具有调节片的飞机的FLAP调节系统
公开(公告)号：WO2011057817A3
公开(公告)日：2011-09-29
申请号：PCT/EP2010006939
申请日：2010-11-15
申请人： AIRBUS OPERATIONS GMBH , RECKSIEK MARTIN , GREIF STEFAN , SCHWINN ROBERT
发明人： RECKSIEK MARTIN , GREIF STEFAN , SCHWINN ROBERT
IPC分类号： B64C9/16
CPC分类号： B64C9/16 , B64D2045/001 , Y02T50/44
摘要： The invention pertains to a flap adjusting system of an aircraft that features: - at least one regulating flap (A1, A2; B1, B2) that is respectively mounted on one of the airfoils of an aircraft by means of at least two bearing devices (LS) and movable relative to the airfoil, - at least one adjusting device (A11, A12, B11, B12, A21, A22, B21, B22) for adjusting the regulating flap (A1, A2; B1, B2), wherein each adjusting device features: an actuator (20; 120) and adjusting kinematics (VK) for kinematically coupling the actuator (20; 120) to the regulating flap (A1, A2; B1, B2) with a drive rod (30, 130) that couples the actuator to the regulating flap (A1, A2; B1, B2) by means of a first and a second joint (31, 32; 131, 132), as well as a load sensor (S-K), wherein the adjusting kinematics (VK) are realized in such a way that, at a maximum adjustment travel of the regulating flap (A1, A2; B1, B2; K), the second joint (32; 132) between the drive rod (30; 130) and the regulating flap (A1, A2; B1, B2) is adjusted by an angle that amounts to less than 50% of the angle, by which the first joint (31; 131 ) is adjusted, and wherein the load sensor (S-K) is arranged in at least one of the at least one adjusting device (A11, A12, B11, B12, A21, A22, B21, B22) that is respectively arranged on a regulating flap (A1, A2; B1, B2; K) and in the second joint (32; 132), by means of which the drive rod is coupled to the regulating flap (A1, A2; B1, B2; K), wherein the load sensor (S-K) is realized in such a way that it measures the forces occurring in this load path.
摘要翻译：本发明涉及一种飞机的翼片调节系统，其特征在于： - 至少一个调节翼片（A1，A2; B1，B2），其通过至少两个轴承装置分别安装在飞行器的翼型之一上 LS），可相对于翼型移动;至少一个用于调整调节翼片（A1，A2; B1，B2）的调节装置（A11，A12，B11，B12，A21，A22，B21，B22）装置特征：致动器（20; 120）和调节运动学（VK），用于利用驱动杆（30,130）将致动器（20; 120）运动学地耦合到调节翼片（A1，A2; B1，B2）所述致动器通过第一和第二接头（31,32; 131,132）以及负载传感器（SK）到所述调节翼片（A1，A2; B1，B2），其中所述调节运动学（VK ）以这样的方式实现：在调节翼片（A1，A2; B1，B2; K）的最大调节行程下，驱动杆（30; 130）与调节翼皮瓣（A 1，A2; B1，B2）的角度调整成小于调整第一接头（31; 131）的角度的50％的角度，并且其中负载传感器（SK）布置在至少一个分别布置在调节翼片（A1，A2; B1，B2; K）上和第二接头（32; 132）中的至少一个调节装置（A11，A12，B11，B12，A21，A22，B21，B22），通过该驱动杆联接到调节翼片（A1，A2; B1，B2; K），其中负载传感器（SK）以这样的方式实现，即测量在该负载路径中发生的力。

5. 发明申请

WO2012136804A2 HIGH LIFT SYSTEM FOR AN AIRCRAFT 审中-公开
标题翻译：用于飞机的高起升系统
公开(公告)号：WO2012136804A2
公开(公告)日：2012-10-11
申请号：PCT/EP2012056350
申请日：2012-04-05
申请人： AIRBUS OPERATIONS GMBH , EADS DEUTSCHLAND GMBH , CHRISTMANN MARKUS , GIEBELER CHRISTOPH , RECKSIEK MARTIN , DORR BJOERN
发明人： CHRISTMANN MARKUS , GIEBELER CHRISTOPH , RECKSIEK MARTIN , DORR BJOERN
IPC分类号： B64C13/24
CPC分类号： B64C3/50 , B64C9/16 , B64C9/22 , B64C13/24 , B64C13/50 , H02K3/28 , Y02T50/44
摘要： The present invention provides a high lift system for an aircraft, which extends and retracts the landing flaps of the aircraft in a fully electric manner. In this context, a fully electric drive is used, comprising an electric motor having an internal redundancy, in such a way that the electric motor is configured as a fault-tolerant electric motor. It may thus be possible to do without a coupling gear unit in the electric motor.
摘要翻译：本发明提供了一种用于飞机的高升力系统，其以完全电动的方式延伸和缩回飞行器的着陆翼。在这种情况下，使用全电驱动器，其包括具有内部冗余的电动机，使得电动机被配置为容错电动机。因此，可以在电动机中没有联接齿轮单元的情况下进行。

6. 发明申请

WO2010046111A3 ADJUSTER DEVICE FOR AN AIRCRAFT COMBINATION OF AN ADJUSTER DEVICE AND AN ADJUSTER DEVICE FAULT RECOGNITION FUNCTION, FAULT -TOLERANT ADJUSTER SYSTEM AND METHOD FOR RECONFIGURING THE ADJUSTER SYSTEM 审中-公开
标题翻译：调整飞机，调整合并及调整装置故障检测功能，容错的停车系统和方法进行重新配置停车系统
公开(公告)号：WO2010046111A3
公开(公告)日：2010-07-29
申请号：PCT/EP2009007571
申请日：2009-10-22
申请人： AIRBUS OPERATIONS GMBH , RECKSIEK MARTIN
发明人： RECKSIEK MARTIN
IPC分类号： B64D45/00
CPC分类号： B64D45/0005 , B64D2045/001
摘要： Adjuster device (A11, A12, B11, B12, A21, A22, B21, B22) for coupling an adjuster flap (A1, A2; B1, B2) on an aircraft to an actuator (20), an adjuster mechanism (VK) for the kinematic coupling of the actuator (20) to the adjustment flap (A1, A2; B1, B2) and a gearbox (25), wherein the adjuster device (A11, A12, B11, B12, A21, A22, B21, B22) may be coupled to a control and monitoring device (5) for operation thereof, characterised in that the adjuster device comprises a first load sensor (S1; S11-a, S12-a, S21-a, S22-a), arranged at the input side (31) of the actuator (20) for recording the load occurring on the input side of the actuator (20) as a result of the operation of the adjustment flap (A1, A2; B1, B2), a second load sensor (S2; S11-b, S12-b, S21-b), arranged at the output side (32) of the actuator (20) for recording the load occurring on the output side (32) of the actuator (20) as a result of the operation of the adjustment flap (A1, A2; B1, B2), wherein the first load sensor (S1; S11-a, S12-a, S21-a, S22-a) and the second load sensor (S1; S11-b, S12-b, S21 -b, S22-b) are functionally connected to an adjuster device fault recognition function for receiving the sensor values delivered by the load sensors, in order to attribute a fault condition to the adjuster device and a combination of an adjuster device and an adjuster device fault recognition function, a fault-tolerant adjuster system and a method fro reconfiguring an adjuster system.
摘要翻译：调节（A11，A12，B11，B12，A21，A22，B21，B22），用于耦合到一个换档阀;飞机的（A1，A2 B1，B2）与运动的致动器（20），调整运动学（VK）所述致动器（20），耦合到所述移位（A1，A2; B1，B2）和变速器（25），其中所述调整装置（A11，A12，B11，B12，A21，A22，B21，B22）的控制和监视装置（5），用于致动其被耦合，其特征在于，所述调节装置包括：第一负载传感器（S1; S11-A，S12-A，S21-A，S22-A），其在输入侧（31）为在致动器（20）的输入侧检测由于换档阀的动作的致动器（20）（A1，A2; B1，B2）被布置负荷发生时，第二负载传感器（S2; S11-b，S12-b ，S21-b）中，其中（在致动器（20）的，用于检测（在致动器（20）的出口侧32）由于换档阀的动作的出口侧32）（A1 ，A2; 负载发生B1，B2）被布置，其中，所述第一负载传感器（S1; S11-A，S12-A，S21-A，S22-a）和第二负载传感器（S1; S11-B，S12-B ，S21-b，S22-b）中可操作地连接到一个调节装置，用于接收错误检测由负荷传感器检测到被分配到的故障条件的调整的传感器值的功能; 和调节装置的组合和调节装置错误检测功能，一个容错致动系统和用于致动系统的重新配置的方法。

7. 发明专利

CA2462217C ADAPTIVE FLAP AND SLAT DRIVE SYSTEM FOR AIRCRAFT 未知
公开(公告)号：CA2462217C
公开(公告)日：2011-01-11
申请号：CA2462217
申请日：2004-03-29
申请人： RECKSIEK MARTIN , RECHTER HARALD , BESING WOLFGANG
发明人： RECKSIEK MARTIN , RECHTER HARALD , BESING WOLFGANG
IPC分类号： B64C13/00 , B64C13/38 , B64C3/00 , B64C9/16 , B64C13/50 , B64D45/00
摘要： A drive station includes two drives connected via drive transmissions to one or more flaps or slats of a flap/slat group. The drives may be mechanically coupled to a rotational shaft, with a shaft brake arranged thereon. Guide transmissions are connected to the shaft and to respective flaps or slats of the flap/slat group. Alternatively, the two drives are not mechanically coupled, but are merely electrically or electronically synchronized. Each flap/slat group can be actuated individually and independently of the other groups by actuation commands provided by a central control unit connected to the drives and to a flight controller. Position sensors provide actual position feedback. Each flap/slat is driven by two transmissions, namely two drive transmissions, or two guide transmissions, or one drive transmission and one guide transmission. A redundant drive path is ensured if a component fails.

8. 发明专利

CA2462217A1 ADAPTIVE FLAP AND SLAT DRIVE SYSTEM FOR AIRCRAFT 未知
公开(公告)号：CA2462217A1
公开(公告)日：2004-09-27
申请号：CA2462217
申请日：2004-03-29
申请人： BESING WOLFGANG , RECKSIEK MARTIN , RECHTER HARALD
发明人： BESING WOLFGANG , RECKSIEK MARTIN , RECHTER HARALD
IPC分类号： B64C13/00 , B64C3/00 , B64C13/50 , B64D45/00 , B64C13/38 , B64C9/16
摘要： A drive station includes two drives connected via drive transmissions to one or more flaps or slats of a flap/slat group. The drives may be mechanically coupled to a rotational shaft, with a shaft brake arranged thereon. Guide transmissions are connected to the shaft and to respective flaps or slats of the flap/slat group. Alternatively, the two drives are not mechanically coupled, but are merely electrically or electronically synchronized. Each flap/slat group can be actuated individually and independently of the other groups by actuation commands provided by a central control unit connected to the drives and to a flight controller. Position sensors provide actual position feedback. Each flap/slat is driven by two transmissions, namely two drive transmissions, or two guide transmissions, or one drive transmission and one guide transmission. A redundant drive path is ensured if a component fails.

9. 发明申请

WO2007068451A8 METHOD AND DEVICE FOR REDUNDANTLY SUPPLYING SEVERAL ELECTRIC SERVOMOTORS OR DRIVE MOTORS BY MEANS OF A COMMON POWER ELECTRONICS UNIT 审中-公开
标题翻译：通过一般电力电子装置冗余供电几台电动伺服电机或驱动电机的方法和装置
公开(公告)号：WO2007068451A8
公开(公告)日：2008-07-24
申请号：PCT/EP2006011955
申请日：2006-12-12
申请人： AIRBUS GMBH , DEUTSCH ZENTR LUFT & RAUMFAHRT , RECKSIEK MARTIN , GIEBELER CHRISTOPH
发明人： RECKSIEK MARTIN , GIEBELER CHRISTOPH
IPC分类号： G05D1/02 , G05B9/03
CPC分类号： G05B9/03 , B64C13/503 , Y02T50/44 , Y10T307/313 , Y10T307/469
摘要： The invention describes a method and a device for redundantly supplying several electric servomotors or drive motors (14, 15) by a common power electronics unit (10), particularly in an aircraft, wherein the power electronics unit (10, 20) contains a number of electronic motor control units (11, 12), and wherein the electric motors (14, 15) are operated with nominal power if the electronic motor control units (11, 12) are fully functional. According to the invention, the motors (14, 15) are operated with the available residual power of the motor control units (11, 12) if partial failure of the motor control units (11, 12) occurs. The motors may be operated sequentially or simultaneously according to preferred embodiments of the invention.
摘要翻译：本发明描述了一种用于通过公共电力电子单元（10）冗余地提供多个电动伺服电动机（14,15）的方法和装置，特别是在飞行器中，其中电力电子单元（10,20）包含一个数字的电子电动机控制单元（11,12），并且其中如果电子电动机控制单元（11,12）完全起作用，则电动机（14,15）以额定功率运行。根据本发明，如果发生电动机控制单元（11,12）的部分故障，则马达（14,15）以马达控制单元（11,12）的可用剩余功率运行。根据本发明的优选实施例，电动机可以顺序地或同时地操作。

10. 发明专利

BRPI0912507A2 sistema deajuste para um estabilizador horizontal hidraulicamente ativável e processo de teste para verificação da integridade de um sistema de ajuste 未知
公开(公告)号：BRPI0912507A2
公开(公告)日：2015-10-13
申请号：BRPI0912507
申请日：2009-05-15
申请人： AIRBUS OPERATIONS GMBH , LIEBHERR AEROSPACE GMBH
发明人： RECKSIEK MARTIN , EPPLE THOMAS
IPC分类号： B64C13/42

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