| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Timonerie pour gouverne d'aéronef | EP01402771.8 | 2001-10-25 | EP1201537A1 | 2002-05-02 | Milliere, Jérôme |
Organe et dispositif de transmission d'efforts radiaux entre des régions centrale et d'extrémité de cet organe. Un organe (22) muni d'ailettes est placé sur une tige cylindrique (20), de façon à être lié à celle-ci en flexion. L'organe (22) est formé d'au moins trois ailettes reliées entre elles à leurs extrémités, et d'au moins une paire d'éléments en forme d'étoile reliant les ailettes au moins à proximité de sa région centrale. Cet organe permet à la tige (20) de transmettre à des voiles (24) prenant appui sur ses extrémités un effort sensiblement radial appliqué au centre de la tige par un actionneur, en minimisant la masse pour un écartement donné des voiles (24). Le dispositif s'applique notamment à la commande de gouvernes d'aéronefs. |
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| 82 | Capteur de déplacement pour verins de servo-commande | EP00402023.6 | 2000-07-13 | EP1069397A1 | 2001-01-17 | Vaslin, Jean-Philippe; Roy, Alain |
Structure comportant d'une part un capteur différentiel de déplacement linéaire qui comprend un corps (1) et un noyau (4) monté coulissant par rapport audit corps (1) et d'autre part une tige (3) de vérin de servocommande dans laquelle le noyau (4) est monté, ladite tige (3) se terminant par un embout (5) qui présente une chemise dans laquelle le noyau (4) est reçu au voisinage de son extrémité, cette chemise et le noyau (4) présentant des filetages complémentaires qui coopèrent pour maintenir ledit noyau (4) par rapport à ladite chemise, des moyens permettant de régler l'engagement du noyau (4) dans ladite chemise, caractérisée en ce que ces moyens comportent une vis de réglage (10) qui s'étend à travers la tige (3) du vérin et dont un filetage coopère avec des moyens complémentaires (9) portés par le noyau (4) pour qu'un mouvement de rotation imposé à la vis de réglage par un opérateur entraîne un déplacement axial du noyau (4) dans la chemise de l'embout (5). |
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| 83 | Antriebsvorrichtung für an Flugzeugtragflügeln angeordnete Klappen | EP91116183.4 | 1991-09-24 | EP0483504A1 | 1992-05-06 | Martens, Wilhelm |
Die Erfindung bezieht sich auf eine Antriebsvorrichtung für an Flugzeugtragflügeln angeordnete Klappen (2) eines in Spannweitenrichtung in einzelne Klappensegmente unterteilten Klappensystems. Jeder Klappe sind zwei Stellvorrichtungen (3) zugeordnet, die über eine Transmissionsvorrichtung (4) untereinander und mit der anderen Flügelseite gekoppelt sind. In der Transmissionsvorrichtung (4) sind jeweils im Außenbereich ein Zentralantrieb (5) auf jeder Flügelseite angeordnet, die jeweils von separaten Signalgebern (10) mit zugeordneten Steuereinheiten (9) parallel redundant ansteuerbar sind. |
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| 84 | SLIDABLE DIVERGENT TRAILING EDGE DEVICE | EP18175169.4 | 2015-04-28 | EP3388331A1 | 2018-10-17 | JAMISON, Flint M.; AMOROSI, Stephen R.; KLEIN, Michael K. |
A wing 130 includes a trailing edge 210, and a divergent trailing edge device 240 slideable along an aft surface of the trailing edge 210 between a stowed position and a fully deployed position. The divergent trailing edge device 240 is located entirely within the trailing edge 210 when stowed, and it increases lift over drag of the wing 130 when deployed.
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| 85 | AIRCRAFT SLAT AND FLAP CONTROL WITH RADIO FREQUENCY IDENTIFICATION TAGS | EP18163372.8 | 2018-03-22 | EP3381795A1 | 2018-10-03 | ANKNEY, Darrell E.; CRANDALL, Adam; PILGRIM, David L. |
Disclosed is a system for monitoring wing control on an aircraft (100) that includes a plurality of radio frequency identification device (RFID) tags (308, 310) attachable to a movable wing portion (308). The system includes a RFID reader (306) attachable to a stationary wing portion (304) and configured to communicate with at least two RFID tags, and a controller (402). The controller (402) includes a processor (403) connected to the RFID reader (306). The processor (403) transmits at least two carrier signals via the RFID reader (306) to the at least two RFID tags. Each of the transmitted carrier signals have a different carrier frequency. The processor (403) also receives at least two reflected signals from the at least two RFID tags. The processor (403) determines, based on the reflected signal from the at least two RFID tags, at least one of a motion of the movable wing portion (302) and a distance of the movable wing portion (302).
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| 86 | AUTOMATIC FLIGHT CONTROL ACTUATOR SYSTEMS | EP17170302.8 | 2017-05-09 | EP3251946B1 | 2018-08-29 | WILKENS, Dean |
| 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. | ||||||
| 87 | SLIDEABLE DIVERGENT TRAILING EDGE DEVICE | EP15165345.8 | 2015-04-28 | EP2952429B1 | 2018-08-01 | Jamison, Flint M; Amorosi, Stephen R; Klein, Michael K |
| A wing (130) includes a trailing edge, which may include a moveable flight control surface (230), and a divergent trailing edge device (240) slideable along an aft surface of the trailing edge or moveable flight control surface (230) between a stowed position and a fully deployed position. The divergent trailing edge device (240) is located entirely within the trailing edge or moveable flight control surface (230) when stowed, and it increases lift over drag of the wing (130) when deployed. | ||||||
| 88 | A FIBRE-OPTIC COMMUNICATION SYSTEM AND AN AIRCRAFT | EP17203398.7 | 2017-11-23 | EP3327958A1 | 2018-05-30 | Barad, Kayvon; Cipullo, Alessio |
Various embodiments provide a fibre-optic communication system for an aircraft. The system comprises: a light source operable to generate light; a transceiver in optical communication with the light source so as to receive the light therefrom, the transceiver comprising a control input and a reflector; an optical fibre in optical communication with the transceiver; and a light detector in optical communication with the optical fibre. The transceiver is operable to generate an amplitude modulated light signal by selectively reflecting the light received from the light source into the optical fibre using the reflector according to information received at the control input. The light detector is operable to receive the amplitude modulated light signal from the optical fibre and to detect an amplitude of the amplitude modulated light signal to extract the information.
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| 89 | AUTOMATIC FLIGHT CONTROL ACTUATOR SYSTEMS | EP17170302.8 | 2017-05-09 | EP3251946A1 | 2017-12-06 | WILKENS, Dean |
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.
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| 90 | CONTROL OF AN UNMANNED AERIAL VEHICLE | EP12835896.7 | 2012-09-14 | EP2760739B1 | 2017-11-22 | CHAN, Keen Ian |
| An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes. | ||||||
| 91 | AN ELECTROMECHANICAL ACTUATOR FOR AN AIRCRAFT CONTROL SURFACE, AND AN AIRCRAFT PROVIDED WITH SUCH AN ACTUATOR | EP12788544.0 | 2012-11-21 | EP2783135B1 | 2017-03-22 | SENEGAS, David; MEHEZ, Jérôme; JESTIN, Maxime; SEVAGEN, Bertrand |
| 92 | RUDDER BIAS GAIN CHANGER | EP11740776.7 | 2011-07-26 | EP2736804B1 | 2015-09-02 | BUTLER, Harris; VELETAS, Mihalis |
| 93 | AN UNMANNED AERIAL VEHICLE | EP12835896 | 2012-09-14 | EP2760739A4 | 2015-07-01 | CHAN KEEN IAN |
| An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes. | ||||||
| 94 | Actuator-link assembly manufacturing method, actuator-link assembly designing method, and actuator-link assembly | EP11156337.5 | 2011-03-01 | EP2368796A3 | 2014-10-01 | 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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| 95 | AN UNMANNED AERIAL VEHICLE | EP12835896.7 | 2012-09-14 | EP2760739A1 | 2014-08-06 | CHAN, Keen Ian |
| An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes. | ||||||
| 96 | Aircraft control surface drive mechanism | EP12166774.5 | 2012-05-04 | EP2530012A2 | 2012-12-05 | Ito, Koji |
An actuator includes a plurality of cylinder units (11) each including a cylinder and a rod (21), and is pivotably attached, at a first end thereof, to a control surface (102). A reaction link (12) is pivotably attached, at a first end thereof, to a fulcrum shaft (104) rotatably supporting the control surface. The reaction link (12) is pivotably attached, at a second end thereof, to a second end of the actuator between the plurality of cylinder units (11).
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| 97 | Capteur de déplacement pour verins de servo-commande | EP00402023.6 | 2000-07-13 | EP1069397B1 | 2012-10-24 | Vaslin, Jean-Philippe; Roy, Alain |
| 98 | MECHANICAL FLIGHT CONTROL AUXILIARY POWER ASSIST SYSTEM | EP05858230 | 2005-10-13 | EP1802940A4 | 2011-11-30 | SHULTZ PETER M; FENNY CARLOS A; WALKER TODD; ARJUNAN SAM |
| 99 | COMPACT ACTUATOR | EP05757487.3 | 2005-06-07 | EP1753979B1 | 2009-08-05 | 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. | ||||||
| 100 | Vorrichtung zur Betätigung von Klappenelementen an den Tragflächen eines Flugzeuges | EP04013800.0 | 2004-06-11 | EP1486416B1 | 2008-11-26 | Pohl, Ulrich, Dipl.-Ing. |
