| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Jam tolerant electromechanical actuation systems and methods of operation | EP04256336.1 | 2004-10-14 | EP1524188A3 | 2014-09-03 | Flatt, James E. |
In a vehicle, having a fixed supporting structure (30a, 30b) and a load movable relative thereto, a jam tolerant actuating system, (20, 220) a method for controlling this system (20,220) including: locating a physical coupling/decoupling mechanism (128, 128") between the load and an actuator assembly (22, 222) as close a practicable to the load; constructing the coupling/uncoupling mechanism (128, 128") to be reversible, and hence testable; and controlling the coupling/uncoupling via decision making electronics (160, 160", 162, 162") which will detect any system failure by monitoring, at a minimum: actuator main motor load (168, 168") and speed (166, 166"), and actuator output load (170, 170"). Also set forth are specific embodiments of pivotable rotary geared actuators (22) as well as linear ball screw type actuators (222) embodying the coupling/uncoupling mechanisms (128, 128") of this invention.
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| 122 | Aircraft reaction link | EP10192687.1 | 2010-11-26 | EP2332830A3 | 2014-04-30 | Itoh, Koji; Ogawa, Toshiaki; Nagashima, Makoto |
An aircraft reaction link includes a pair of linear portions (22a,22b), a coupling portion (23) that couples ends of the pair of linear portions on the same side to each other, a fulcrum shaft attachment portion (24), and a cylinder attachment portion (25a,25b). A metal frame (29) that is made of a metallic material and that is provided so as to extend across the coupling portion and the pair of linear portions and a composite frame (30) that is made of fiber-reinforced plastic and that is provided so as to extend at least in the pair of linear portions are bonded together, and thereby, the pair of linear portions and the coupling portion are formed. The metal frame is provided so as to extend from the fulcrum shaft attachment portion to the cylinder attachment portion.
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| 123 | Integrated torque limiter/no-back device | EP13168099.3 | 2013-05-16 | EP2666716A2 | 2013-11-27 | Finney, Adam M. |
An integrated torque limiter/no-back device (36) for use in an actuator (20) with an input shaft (30), an output (34) and gear reduction (32). The device includes an input ramp (38) to receive torque from the input shaft (30); a combined ramp (40) to transfer torque; an output ramp (42) to transfer torque to the gear reduction (32); one or more balls (46; 48) between the input ramp (38) and the combined ramp (40) and between the combined ramp (40) and the output ramp (42) to transfer torque; and a brake (44; 45) for causing torque to be grounded and for preventing backdriving of the input shaft by preventing movement of one or more of the input ramp (38), the combined ramp (40) and the output ramp (42) when a torque threshold has been met. The input ramp and the output ramp are one of a no-back ramp (42) and a torque limiter ramp (38), respectively, and the device (36) also includes a pin (50) between the combined ramp (40) and one or more of the no-back ramp (42) and the gear reduction (32) for transferring torque.
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| 124 | FLIGHT CONFIGURATION AND FLIGHT STRATEGY FOR FLIGHT WIND SPEEDS | EP11838810.7 | 2011-11-03 | EP2635491A1 | 2013-09-11 | VANDER LIND, Damon |
| A crosswind kite system adapted to operate in an alternate mode in high winds. The system may operate at reduced efficiency in high winds in order to moderate loading on the system during those high winds. The system may use multi-element airfoils which are actuated to reduce the coefficient of lift of the airfoils in order to moderate loading in high wind conditions. Other flight aspects may be controlled, including flying the crosswind kite in side slip to induce drag which may lower loading on the system. | ||||||
| 125 | MECHANICAL FLIGHT CONTROL AUXILIARY POWER ASSIST SYSTEM | EP05858230.5 | 2005-10-13 | EP1802940B1 | 2013-05-01 | SHULTZ, Peter, M.; FENNY, Carlos, A.; WALKER, Todd; ARJUNAN, Sam |
| 126 | ROTORCRAFT CONTROL SYSTEM WITH STEPPED MIXING LINKAGE | EP03774477.8 | 2003-09-19 | EP1542901B1 | 2012-02-15 | FENNY, Carlos, A.; HICKS, Duane |
| A control system for a rotorcraft is disclosed. The control system includes a stepped mixing linkage (53), such that a selected amount of right-left lateral cyclic output is generated for certain amounts of forward-aft cyclic input. The stepped mixing linkage (53) includes two supporting links and a floating link (73) pivotally coupled between the two supporting links. The ratio of the lengths of the two supporting links to the length of the floating link (73) is small, thereby generating a selected lateral sinusoidal output, a selected rotation of the sinusoidal output, and a selected ramped output in response to each forward-aft pilot input command. | ||||||
| 127 | Actuator-link assembly manufacturing method, actuator-link assembly designing method, and actuator-link assembly | EP11156337.5 | 2011-03-01 | EP2368796A2 | 2011-09-28 | Ogawa, Toshiaki; Itoh, Koji; Nagashima, Makoto |
In a material determining step, the material constituting an actuator and the material constituting a link are determined such that at least one of the materials contains fiber reinforced plastic. In a computing step, a computation model that defines the relationship between a control surface, the actuator, and the link is used to compute the change in gain margin with the change in a rigidity ratio, which is the ratio of the rigidity of the link to the rigidity of the actuator. The rigidities of the actuator and the link are determined in a rigidity determining step based on a result of the above-described computation, the shapes of the actuator and the link are determined in a shape determining step, and the actuator and the link are formed in a formation step, and are assembled in an assembly step.
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| 128 | AIRFOIL FOR AN AIRCRAFT AND AIRCRAFT | EP06830855.0 | 2006-12-29 | EP1966043B1 | 2011-08-03 | POHL, Ulrich |
| The invention relates to the monitoring of the landing flaps on an airfoil (2) for an aircraft (1), and to an aircraft (1) having such an airfoil (2). The airfoil (2) has a wingbox (3), a support (5) which is mounted relative to the wingbox (3) such that it can rotate with respect to a flap rotation axis (7), a flap (4) which is attached to the support (5) and rotates with respect to the flap rotation axis (7) during rotation of the support (5) relative to the wingbox (3), a movement mechanism (8) which is coupled to the support (5) in order to set an angle position of the flap (4) with respect to the wingbox (3) and a measurement apparatus (18) for detection of the angle position of the flap (4). The measurement apparatus (18) has a rotation sensor (19), which is arranged on the support (5), and a four-element coupling transmission (22, 24, 26, 27) which couples the rotation sensor (19) to the movement mechanism (8). | ||||||
| 129 | Aircraft reaction link | EP10192687.1 | 2010-11-26 | EP2332830A2 | 2011-06-15 | Itoh, Koji; Ogawa, Toshiaki; Nagashima, Makoto |
An aircraft reaction link includes a pair of linear portions (22a,22b), a coupling portion (23) that couples ends of the pair of linear portions on the same side to each other, a fulcrum shaft attachment portion (24), and a cylinder attachment portion (25a,25b). A metal frame (29) that is made of a metallic material and that is provided so as to extend across the coupling portion and the pair of linear portions and a composite frame (30) that is made of fiber-reinforced plastic and that is provided so as to extend at least in the pair of linear portions are bonded together, and thereby, the pair of linear portions and the coupling portion are formed. The metal frame is provided so as to extend from the fulcrum shaft attachment portion to the cylinder attachment portion.
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| 130 | Verfahren zur Ansteuerung eines Antriebssystems und Antriebssystem | EP08010291.6 | 2008-06-05 | EP2008931A3 | 2011-04-13 | Hauzenberger, Stefan, Dipl.-Ing.; Hauber, Bernhard, Dipl.-Ing. |
Die Erfindung zeigt ein Verfahren zur Ansteuerung eines Antriebssystems für Steuerflächen oder Arbeitssysteme eines Flugzeugs, wobei die Drehzahl einer Antriebseinheit des Antriebssystems geregelt wird und nach einem Anfahrvorgang die während des weiteren Betriebs zur Drehzahlregelung der Antriebseinheit maximal zur Verfügung stehende Antriebsleistung reduziert wird. Ebenso umfasst die Erfindung ein Antriebssystem für Steuerflächen oder Arbeitssysteme eines Flugzeugs, mit einer Antriebseinheit mit Drehzahlregelung und einer entsprechenden Steuerung.
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| 131 | Dispositif d'accouplement escamotable et vérin de trim associé | EP09006525.1 | 2009-05-14 | EP2128021B1 | 2011-01-19 | Gemmati, Bernard; Vincent, Philippe; Biest, Romuald |
| 132 | ROTORCRAFT CONTROL SYSTEM WITH STEPPED MIXING LINKAGE | EP03774477 | 2003-09-19 | EP1542901A4 | 2010-11-03 | FENNY CARLOS A; HICKS DUANE |
| 133 | LANDING FLAP DRIVE SYSTEM | EP06724293.3 | 2006-04-12 | EP1868888B1 | 2010-05-05 | RECKSIEK, Martin; GIEBELER, Christoph; BRÜCKNER, Ina |
| 134 | Monitoring apparatus | EP02252304.7 | 2002-03-28 | EP1245867B1 | 2009-12-16 | Capewell, Terence John |
| 135 | Dispositif d'accouplement escamotable et vérin de trim associé | EP09006525.1 | 2009-05-14 | EP2128021A1 | 2009-12-02 | Gemmati, Bernard; Vincent, Philippe; Biest, Romuald |
La présente invention concerne un dispositif d'accouplement (10) escamotable d'un premier et d'un deuxième arbres de transmission principaux (2, 3) fixes en translation le long d'un axe de rotation (AX) longitudinal du dispositif, ce dispositif étant pourvu d'un moyen de blocage (20) ainsi que d'un moyen de compression (30) et d'au moins un moyen d'entraînement (40) Ilant en rotation autour dudit axe de rotation (AX) longitudinal ledit moyen de blocage (20) et ledit moyen de compression (30) en dessous d'un couple prédéterminé, ledit moyen de blocage (20) étant pourvu d'un premier logement discontinu (21) accueillant ledit moyen d'entrainement (40) en dessous dudit couple. Le moyen de blocage (20) comportant un deuxième logement continu (22) décrivant une boucle fermée, le dispositif d'accouplement (10) est muni d'un moyen de déplacement (50) déplaçant de manière irréversible sans intervention humaine ledit moyen d'entraînement (40) dudit premier logement (21) vers ledit deuxième logement (22) lorsque le couple exercé sur le moyen d'entraînement est supérieur audit couple prédéterminé.
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| 136 | Klappen-Kopplungssytem für Luftfahrzeuge | EP05015760.1 | 2005-07-20 | EP1619117B1 | 2009-11-25 | Poppe, Bernd; Auhagen, Kurt |
| 137 | AIRFOIL FOR AN AIRCRAFT AND AIRCRAFT | EP06830855.0 | 2006-12-29 | EP1966043A2 | 2008-09-10 | POHL, Ulrich |
| The invention relates to the monitoring of the landing flaps on an airfoil (2) for an aircraft (1), and to an aircraft (1) having such an airfoil (2). The airfoil (2) has a wingbox (3), a support (5) which is mounted relative to the wingbox (3) such that it can rotate with respect to a flap rotation axis (7), a flap (4) which is attached to the support (5) and rotates with respect to the flap rotation axis (7) during rotation of the support (5) relative to the wingbox (3), a movement mechanism (8) which is coupled to the support (5) in order to set an angle position of the flap (4) with respect to the wingbox (3) and a measurement apparatus (18) for detection of the angle position of the flap (4). The measurement apparatus (18) has a rotation sensor (19), which is arranged on the support (5), and a four-element coupling transmission (22, 24, 26, 27) which couples the rotation sensor (19) to the movement mechanism (8). | ||||||
| 138 | COMPACT ACTUATOR | EP05757487 | 2005-06-07 | EP1753979A4 | 2007-12-26 | LARSON LOWELL V |
| The present invention provides an improved compact actuator (20) for selectively moving an object (27) relative to a support (21). The improved actuator includes a gear reduction unit (24) mounted on the support. The gear reduction unit has a ring gear (25) adapted to be rotated about a longitudinal axis (x-x), and a pinion (26) mounted on the ring gear. All bearings for the output member are physically located within the gear reduction unit. The output member is coupled to the object such that rotation of the output member will move the object relative to the support. | ||||||
| 139 | Jam tolerant electromechanical actuation systems and methods of operation | EP04256336.1 | 2004-10-14 | EP1524188A2 | 2005-04-20 | Flatt, James E. |
In a vehicle, having a fixed supporting structure (30a, 30b) and a load movable relative thereto, a jam tolerant actuating system, (20, 220) a method for controlling this system (20,220) including: locating a physical coupling/decoupling mechanism (128, 128") between the load and an actuator assembly (22, 222) as close a practicable to the load; constructing the coupling/uncoupling mechanism (128, 128") to be reversible, and hence testable; and controlling the coupling/uncoupling via decision making electronics (160, 160", 162, 162") which will detect any system failure by monitoring, at a minimum: actuator main motor load (168, 168") and speed (166, 166"), and actuator output load (170, 170"). Also set forth are specific embodiments of pivotable rotary geared actuators (22) as well as linear ball screw type actuators (222) embodying the coupling/uncoupling mechanisms (128, 128") of this invention. |
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| 140 | Monitoring apparatus | EP02252304.7 | 2002-03-28 | EP1245867A2 | 2002-10-02 | Capewell, Terence John |
A monitoring apparatus for monitoring operation of a no-back device (5) of an actuator assembly (1) driven by a motor (2, 3), the apparatus comprising sensor means (12; 21) operable to sense an operating parameter of the motor for determining when the motor's output drive is in a direction opposite to a selected direction of motor output drive. |
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