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1. 发明申请

WO2012031759A2 MONITORING DEVICE FOR AN ACTUATION SYSTEM OF AN AIRCRAFT, ACTUATION SYSTEM AND METHOD FOR RECONFIGURING THE ACTUATION SYSTEM 审中-公开
标题翻译：用于飞机执行系统的监控装置，执行系统和重新启动执行系统的方法
公开(公告)号：WO2012031759A2
公开(公告)日：2012-03-15
申请号：PCT/EP2011/004527
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
CPC分类号： B64D45/0005 , B64D2045/001
摘要： The invention pertains to a monitoring device (5) for an actuation system of an aircraft that comprises a function for monitoring a guiding device (A1 1, 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 it is determined that the predefined flight attitude and/or the predefined operational state of the aircraft exists as a result of the comparison showing that this limiting value corresponding to the minimum operational load is not reached. The invention furthermore pertains to an actuation system with such a monitoring device (5) and to a method for reconfiguring such an actuation system.
摘要翻译：本发明涉及一种用于飞行器的致动系统的监视装置（5），该监视装置包括用于监视调节翼片（K1）的引导装置（A1 1，A 12，B 11，B 12，A 21，A 22，B 21，B 22）的功能 ;具有负载传感器（S1; S2）的A1，A2; B1，B2），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; PA2，PB1，PB2），其中监视装置（5）以这样的方式实现，即其确定或接收主动发出预定飞行姿态的信息和/或预定义的操作状态飞行器，其中所述监视装置（5）包括：比较功能，用于执行对应于由所述载荷传感器获取的传感器值的载荷值与对应于所述预定飞行姿态的最小操作载荷的极限值之间的比较和/或飞机的预定义操作状态a 监视功能，并且其中监视功能以这样的方式实现，即如果确定飞机的预定飞行姿态和/或预定义的操作状态存在作为结果，则将故障模式分配给调节翼片比较表明没有达到对应于最小操作负荷的极限值。本发明还涉及具有这种监视装置（5）的致动系统以及用于重新配置这种致动系统的方法。

2. 发明申请

WO2008141792A1 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：WO2008141792A1
公开(公告)日：2008-11-27
申请号：PCT/EP2008/004004
申请日：2008-05-19
申请人： AIRBUS DEUTSCHLAND 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。

3. 发明申请

WO2010115815A3 FLÜGEL EINES FLUGZEUGS ODER EINES RAUMFAHRZEUGS MIT EINEM BEWEGLICHEN STRÖMUNGSKÖRPER 审中-公开
公开(公告)号：WO2010115815A3
公开(公告)日：2010-10-14
申请号：PCT/EP2010/054338
申请日：2010-03-31
申请人： AIRBUS OPERATIONS GMBH , HEINTJES, Mark
发明人： HEINTJES, Mark
IPC分类号： B64C9/16
摘要： Die vorliegende Erfindung betrifft einen Flügel eines Luft- oder Raumfahrzeugs, wobei der Flügel (12) wenigstens einen beweglichen Strömungskörper (10) aufweist, wobei der Flügel eine bewegliche Stützeinrichtung (22) aufweist (10) die mit dem Strömungskörper (10) verbunden ist, zum Drehen des Strömungskörpers (10) an dem Flügel (12), wobei der Flügel (12) eine Strömungskörpersteuereinrichtung (18, 20) aufweist, wobei die Strömungskörpersteuereinrichtung (18, 20) an dem Flügel (12) in einem ersten Punkt (C) befestigt ist und die Stützeinrichtung (22) in einem zweiten Punkt (B), wobei die beiden Punkte (C, B) der Strömungskörpersteuereinrichtung (18, 20) und der Stützeinrichtung (22) eine Achse (HL-1) bilden, wobei die Strömungskörpersteuereinrichtung (18, 20) in einem vorbestimmten Winkel (ß) geneigt zu der Achse (HL-1) ausgebildet ist und wobei die Strömungskörpersteuereinrichtung (18, 20) den Strömungskörper (10) in einer vorbestimmten Ebene um diese Achse (HL-1) führt.

4. 发明申请

WO2009083261A2 SYSTEM ZUR BETÄTIGUNG VON ZUMINDEST EINER STELLKLAPPE EINES FLUGZEUGS SOWIE EIN VERFAHREN ZUR ÜBERPRÜFUNG DES SYSTEMS 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：WO2009083261A2
公开(公告)日：2009-07-09
申请号：PCT/EP2008/011151
申请日：2008-12-30
申请人： AIRBUS DEUTSCHLAND GMBH , HEINTJES, Mark
发明人： HEINTJES, Mark
IPC分类号： B64C13/24 , B64D45/00
CPC分类号： B64C13/28 , B64D45/0005 , B64D2045/001
摘要： Verfahren zur Betätigung von zumindest einer Stellklappe an jeweils einem Flügel eines Flugzeugs, die zumindest zwei Klappenkupplungs-Vorrichtungen (11, 12, 13, 14) mit jeweils einer Stellantriebs-Vorrichtung (30) betätigt wird, wobei zumindest an einer Stellantriebs-Vorrichtung (30) je Stellklappe eine Brems-Vorrichtung angeordnet ist, mit deren Betätigung ein Verstellzustand der jeweiligen Stellantriebs-Vorrichtung (30) arretiert werden kann, mit den Schritten: Betätigung jeder Brems-Vorrichtung einer Stellklappe einzeln anschließend Betätigung der Stellantriebs-Vorrichtung mittels des Antriebsmotors bei einer Veränderung des Verstellzustands der Stellklappe um ein vorbestimmtes Maß Beendigung der Betätigung der betroffenen Stellklappe, sowie System zur Durchführung des Verfahrens.
摘要翻译：
一种贝特＆AUML过程;在各自的FL HILL致动至少一个控制襟翼的飞行器，所述至少两个翼片的耦合装置（11，12，13，14），每一个具有致动器装置（30）赌注＆AUML;是无题，其中，至少一个致动器装置（30）上的制动装置被安排用于每个致动翼片，与所述赌注＆AUML;致动所述相应的致动器装置（30）的调整状态可以被锁定，其包括以下步骤：赌注＆AUML;致动一个调节瓣单独后续ROAD端赌注＆AUML的每个制动装置;通过在版BEAR驱动马达的装置帐户的致动器装置以预定的马道改变蝶形阀的调整状态赌注＆AUML的完成;帐户有关的定位翼片，和系统，用于执行导航使用出处理。

5. 发明申请

WO2006133940A1 LIFT-AUGMENTING FLAP, IN PARTICULAR LEADING EDGE FLAP, FOR AN AERODYNAMICALLY EFFECTIVE WING 审中-公开
标题翻译：提升翼片，特别是领先翼片，用于有效的翼
公开(公告)号：WO2006133940A1
公开(公告)日：2006-12-21
申请号：PCT/EP2006/005758
申请日：2006-06-14
申请人： AIRBUS DEUTSCHLAND GMBH , RAUDSZUS, Morten , SCHLIPF, Bernhard , ANDREANI, Luc , HUE, Xavier , HEINTJES, Mark
发明人： RAUDSZUS, Morten , SCHLIPF, Bernhard , ANDREANI, Luc , HUE, Xavier , HEINTJES, Mark
IPC分类号： B64C3/50 , B64C9/22
CPC分类号： B64C3/50 , Y02T50/14
摘要： A lift-augmenting flap, in particular a leading edge flap, for an aerodynamically effective wing with a defined wing profile, in particular for a carrying wing of an aircraft, wherein the wing (10) comprises a wing box (10a) which on a first side comprises a first skin (11) and on a second, opposite, side comprises a second skin (12) and on its end facing the flap (20) comprises a wing end cover (14) which at least in part follows on from the first skin (11) in a wing profile shape, and wherein the flap (20) comprises an essentially rigid main body (21) which makes a transition from the first side to the second side of the wing (10), and a first transition region (20a) that faces the first side of the wing (10), and a second transition region (20b) that faces the second side of the wing (10), with said flap (20) being adjustable, by means of a retention-and actuation mechanism (23) that is coupled between the flap (20) and the wing box (10a), between a first, retracted, position and a second, extended, position, wherein the first transition region (20a) of the flap (20), which region faces the first side of the wing (10), is slidable, so as to rest in each position essentially free of any gap, against the first skin (11) or against the wing end cover (14), in relation to said wing end cover. The flap (20) is positional between the first and the second position, while maintaining an angle in relation to the wing box (10a) and concurrent extension of the wing profile on a virtual rotary axis (30) that is situated on the side opposite the first skin (11), outside the wing profile, wherein the second transition region (20b) of the flap (20), which region faces the second side of the wing (10), in each flap position is sealed off from the second skin (12) so as to be essentially free of any gap.
摘要翻译：用于具有限定翼型的空气动力学有效的翼，特别是用于飞机的承载翼的升降翼，特别是前缘翼，其中所述翼（10）包括翼盒（10a），所述翼盒第一侧包括第一皮肤（11），并且在第二相对侧上包括第二皮肤（12），并且在其面向所述皮瓣（20）的一端包括翼端盖（14），所述翼端盖（40）至少部分地从所述第一皮肤（11）处于机翼轮廓形状，并且其中所述翼片（20）包括基本上刚性的主体（21），所述主体（21）从所述机翼（10）的所述第一侧向所述第二侧过渡，过渡区域（20a），以及面对翼片（10）的第二侧的第二过渡区域（20b），其中所述翼片（20）可调节，借助于保持和致动机构（23），其联接在所述翼片（20）和所述翼盒（10a）之间，在第一缩回位置和第二，延伸位置，其中所述翼片（20）的面向翼（10）的第一侧的区域的第一过渡区域（20a）可滑动，以便在基本上没有任何间隙的每个位置中放置，相对于所述翼端盖相对于第一皮肤（11）或抵靠翼端盖（14）。翼片（20）位于第一位置和第二位置之间，同时保持与翼盒（10a）相关的角度并且在位于相对侧的虚拟旋转轴线（30）上的翼型材的同时延伸所述第一皮肤（11）在所述翼型材外部，其中所述翼片（20）的所述翼片（10）的面对所述翼片（10）的第二侧的所述第二过渡区域（20b）在每个折翼位置被密封，皮肤（12），以便基本上没有间隙。

6. 发明授权

EP2625103B1 ACTUATION SYSTEM FOR AN ADJUSTABLE AIRCRAFT FLAP AND METHOD FOR RECONFIGURING THE ACTUATION SYSTEM 有权
标题翻译：控制系统用于飞机和控制系统的重新配置的可调瓣法
公开(公告)号：EP2625103B1
公开(公告)日：2017-06-14
申请号：EP11754623.4
申请日：2011-09-08
申请人： Airbus Operations GmbH
发明人： RECKSIEK, Martin , HEINTJES, Mark , WINKELMANN, Christoph
IPC分类号： B64D45/00
CPC分类号： B64D45/0005 , B64D2045/001

7. 发明公开

EP2625103A2 ACTUATION SYSTEM FOR AN ADJUSTABLE AIRCRAFT FLAP AND METHOD FOR RECONFIGURING THE ACTUATION SYSTEM 有权
标题翻译：控制系统用于飞机和控制系统的重新配置的可调瓣法
公开(公告)号：EP2625103A2
公开(公告)日：2013-08-14
申请号：EP11754623.4
申请日：2011-09-08
申请人： Airbus Operations GmbH
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 a monitoring device (5) for an actuation system of an aircraft that comprises a function for monitoring a guiding device (A1 1, 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 it is determined that the predefined flight attitude and/or the predefined operational state of the aircraft exists as a result of the comparison showing that this limiting value corresponding to the minimum operational load is not reached. The invention furthermore pertains to an actuation system with such a monitoring device (5) and to a method for reconfiguring such an actuation system.

8. 发明公开

EP2240365A2 SYSTEM ZUR BETÄTIGUNG VON ZUMINDEST EINER STELLKLAPPE EINES FLUGZEUGS SOWIE EIN VERFAHREN ZUR ÜBERPRÜFUNG DES SYSTEMS 有权
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：EP2240365A2
公开(公告)日：2010-10-20
申请号：EP08866338.0
申请日：2008-12-30
申请人： Airbus Operations GmbH
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.

9. 发明授权

EP2240365B1 SYSTEM ZUR BETÄTIGUNG VON ZUMINDEST EINER STELLKLAPPE EINES FLUGZEUGS SOWIE EIN VERFAHREN ZUR ÜBERPRÜFUNG DES SYSTEMS 有权
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：EP2240365B1
公开(公告)日：2012-07-04
申请号：EP08866338.0
申请日：2008-12-30
申请人： Airbus Operations GmbH
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.

10. 发明授权

EP2162641B1 METHOD AND DEVICE FOR FAULT DETECTION IN THE LOAD PATH OF A SPINDLE ACTUATOR 有权
标题翻译：方法和装置用于检测的负载路径螺杆致动器
公开(公告)号：EP2162641B1
公开(公告)日：2010-12-22
申请号：EP08749484.5
申请日：2008-05-19
申请人： Airbus Operations GmbH , EADS Deutschland GmbH
发明人： Ruckes, 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.

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