| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 341 | HIGH LIFT SYSTEM FOR AN AIRCRAFT AND METHOD FOR INFLUENCING THE HIGH LIFT CHARACTERISTICS OF AN AIRCRAFT | EP12717709.5 | 2012-04-27 | EP2701975A1 | 2014-03-05 | HUE, Xavier; SCHLIPF, Bernhard |
| A high lift system for an aircraft includes a basic body, a flap which is movably mounted on the basic body and has a flap edge, and a retaining element. The high lift system is set up to form a gap between the flap edge and the basic body. The retaining element is mounted on a region of the flap close to the flap edge and extends towards the basic body to restrict the distance between the flap edge and the basic body. The retaining element is preferably configured as a linear attachment means. Consequently, a gap dimension between a flap and a basic body can be influenced to restrict flexing effects during loading of the flap and of the basic body. | ||||||
| 342 | Einrichtung zur Verstellung von Hochauftriebsklappen an Flugzeugtragflügel | EP87107332.6 | 1987-05-20 | EP0253986A1 | 1988-01-27 | Heynatz, Johann Theodor, Prof. Dr.-Ing. |
Einrichtung zur Verstellung von Klappen, insbesondere von Hochauftriebsklappen bzw. Klappensystemen an der Hinterkante von Flugzeugtragflügeln, mit Tragarmen bzw. Auslegerarmen zur schwenkbaren Aufnahme der Hochauftriebsklappen und Klappenverstelleinrichtungen. Zur Verminderung des Luftwiderstandes sind insbesondere für die Marschflugphase eines Flugzeuges die außerhalb der Flügelkontur liegenden Klappen-Schwenklagerungen (25, 26) um Achsen (24; 22, 23), die sich in Richtung der Flügeltiefe erstrecken, in eine widerstandsarme Stellung einklappbar vorgesehen. Die Klappen-Schwenklagerungen (25, 26) und deren Träger (10, 11) sind von einem Hauptträger (9) aufgenommen und sind mit diesem einklappbar. |
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| 343 | HIGH-LIFT SYSTEM FOR AN AIRCRAFT | EP10798973.3 | 2010-12-23 | EP2516260A2 | 2012-10-31 | GÖLLING, Burkhard |
| A high-lift system (100) with a main wing (112) and adjustable flaps (110) as well as guiding devices (130) for holding the adjustable flaps (110) and adjustment devices (120) for adjusting the adjustable flaps (110), wherein the respective guiding device (130) and/or adjustment device (120) at least in part comprise/comprises a fairing (118), comprising a flow influencing (10) device for influencing the flow around the high- lift system (100), with at least one inlet line (20) with at least one inlet that is situated on or below the bottom of the high- lift system (100), wherein, furthermore, at least one outlet line (30) for air is provided that comprises a fluid-communicating connection to the inlet line (10) and comprises at least one outlet situated at the top in the region of at least one adjustable flap (110) of the high-lift system (100). | ||||||
| 344 | RETRACTABLE INFILL PANEL FOR HIGH-LIFT DEVICE | US14084828 | 2013-11-20 | US20140138487A1 | 2014-05-22 | Mark HODKISSON; James WILSON; Samuel EVANS |
| The present invention provides an aircraft assembly with a fixed structure and a high-lift device. The fixed structure has a spar, a forward part which provides a foremost edge of an aircraft wing, and a lower part which provides a lower surface of the aircraft wing. A high-lift device is downwardly movable relative to the fixed structure from a stowed configuration to a deployed configuration. The high-lift device has a forward part which provides a foremost edge of the aircraft wing and a lower part which provides a lower surface of the aircraft wing. Downward movement of the high-lift device causes progressive opening of a lateral gap between the lower part of the high-lift device and the lower part of the fixed structure. A retractable infill panel is arranged to progressively extend from a retracted configuration to an extended configuration to fill the lateral gap. | ||||||
| 345 | Flugzeughochauftriebssystem sowie Verfahren zur Ermittlung eines Betriebszustandes eines Flugzeughochauftriebssystems | EP10004888.3 | 2010-05-07 | EP2251258A2 | 2010-11-17 | Schievelbusch, Bernd; Hauber, Bernhard |
Die vorliegende Erfindung betrifft ein Flugzeughochauftriebssystem (10) mit wenigstens einer Laststation (32,34) zur Ansteuerung einer Klappe eines Flügels, vorzugsweise einer Landeklappe und/oder einer Vorflügelklappe (20,30), wenigstens einer Transmission (17) mit Transmissionsabschnitten (42,44,46), die sich zwischen Abzweiggetrieben befinden, wobei mittels der Abzweiggetriebe Stellenergie von der Transmission (17) an die Laststation abzweigbar ist sowie ein Verfahren zur Ermittlung eines Betriebszustandes eines Flugzeughochauftriebssystems (10). |
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| 346 | HIGH LIFT SYSTEM FOR AN AIRCRAFT WITH A SEPARATE DRIVE UNIT FOR EACH WING HALF | EP11764226.4 | 2011-10-05 | EP2625104B1 | 2017-07-19 | RICHTER, Martin |
| A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves. | ||||||
| 347 | ACTUATION SYSTEM FOR LEADING EDGE HIGH-LIFT DEVICE | US12733465 | 2008-10-27 | US20100187368A1 | 2010-07-29 | Francois Cathelain; Edmund Kay |
| An actuation system configured to deploy a high-lift device on a leading edge of an aircraft wing. The system comprises: a link pivotally connected to the wing at a first pivot point and to the high-lift device at a second pivot point; a first actuation mechanism configured to rotate the high-lift device about the first pivot point; and a second actuation mechanism configured to rotate the high-lift device about the second pivot point. The second actuation mechanism is operable independently of the first actuation mechanism, and can be operated in order to generate a sealing force between the high-lift device and the leading edge of the aircraft wing. | ||||||
| 348 | Wing leading edge slat system | US11268384 | 2005-11-07 | US20070102587A1 | 2007-05-10 | Kelly Jones; Stephen Fox; Stephen Amorosi |
| A mechanism for extending and supporting a high-lift device relative to an airfoil has a pair of support ribs coupled to the airfoil. A carrier track is pivotally coupled to the high-lift device and positioned between the pair of support ribs. The carrier track has a slot opening along a lower length thereof. A gear rack is coupled within the slot opening. A pinion gear is positioned between the support ribs and below the carrier track. The pinion gear engages with the gear rack for extending the high-lift device relative to the airfoil. A plurality of rollers is rotateably coupled to the support ribs and in bearing contact with the carrier track. At least one roller is positioned above the carrier track and a second roller is positioned below the carrier track. The second roller is positioned concentrically with the pinion gear. | ||||||
| 349 | Operation guide device of high lift work vehicle | JP2006295054 | 2006-10-31 | JP2008110841A | 2008-05-15 | HIGUCHI MASAHIRO; ODA TAKUMI; TSUZUKI KEIICHI; YAMADA KEISUKE |
| PROBLEM TO BE SOLVED: To solve the problem of mistaking the operation direction of operation means 4a to 7a operating operation of a working platform moving device B, in such a case when occasionally requiring to put the working platform moving device B in a required target attitude in this kind of high lift work vehicle, by optionally selecting a three-dimensional space position and an attitude of a working platform C, by changeably operating the attitude of the working platform moving device B, in the high lift work vehicle for installing the working platform C on a vehicle A via the working platform moving device B. SOLUTION: The operation direction of the operation means 4a to 7a is guided by an operation guide device composed of attitude detecting means 8 to 11 detecting an actual attitude of the working platform moving device B, a target attitude output means 12 outputting the target attitude of the working platform moving device B, an operation direction indicating means 13 displaying the operation direction of the respective operation means 4a to 7a, and a controller 14 outputting an operation direction display signal to the operation direction display means 13 by receiving a signal from the attitude detecting means 8 to 11 and the target attitude output means 12. COPYRIGHT: (C)2008,JPO&INPIT | ||||||
| 350 | Automatic control of a high lift system of an aircraft | US12679624 | 2008-09-24 | US08356776B2 | 2013-01-22 | Martin Berens; Juergen Quell; August Kroeger |
| A device for automatically controlling a system of high-lift elements of an aircraft, which high-lift elements can be set to a retracted and to several extended configurations for cruising, holding flight, takeoff or landing; comprising a flap control unit that by way of a control connection is connected, so as to be functionally effective, to a drive system of the high-lift elements; and an operating unit, connected to the flap control unit, for entering operating instructions that influence the setting of the high-lift elements, where the flap control unit is provided for calculating switching speeds that are associated with the respective configurations of the high-lift elements, where the direction of the configuration change and the operating modes of the automatic system for adjusting the high-lift elements, depending on flight state data and further flight-operation-relevant data; and where, in addition, the flap control unit can also automatically carry out switchover of the operating modes for takeoff or for the landing approach and is provided to automatically generate the instructions that instruct the configuration change, depending on the flight speed. | ||||||
| 351 | HOCHAUFTRIEBSSYSTEM EINES FLUGZEUGS, FLUGZEUGSYSTEM UND PROPELLER-FLUGZEUG MIT EINEM HOCHAUFTRIEBSSYSTEM | EP10714587.2 | 2010-04-16 | EP2445782A2 | 2012-05-02 | RUCKES, Ina; SCHEFFERS, Peter; WILLMER, Michael; SPILLER, Olaf |
| The invention relates to a high lift system for an airplane, comprising: one or more high lift flaps (14a, 14b); a control device (60, 160) having a control function for generating position commands for setting the adjustment state of the high lift flaps (14a, 14b); a drive device (63, 163) coupled to the high lift flaps (14a, 14b) and is designed such that it adjusts the high lift flaps (14a, 14b) between a retracted position and an extended position on the basis of control commands, wherein the control function creates position commands based on input values and sends them to the drive device (63, 163) for adjusting the high lift flaps (14a, 14b). The control function comprises a function for automatically retracting the high lift flap (14a, 14b) during flight, which creates a control command in a flight state in which the high lift flap (14a, 14b) is in an extended position, taking into consideration an engine thrust and a minimal flight altitude, after the high lift flap (14a, 14b) is retracted. | ||||||
| 352 | Two-step finger follower rocker arm assembly | US10305995 | 2002-11-27 | US06668779B2 | 2003-12-30 | Nick J. Hendriksma; Andrew J. Lipinski; Hermes A. Fernandez |
| A two-step finger follower rocker arm assembly for cooperating with high-lift and low-lift cam lobes of an engine camshaft. The rocker arm assembly includes a follower body for engaging an hydraulic lash adjuster and a valve stem. A central well contains a roller for following the central low-lift cam lobe. Pivotably mounted on the body are lateral high-lift followers, including sliders or rollers, for following the lateral high-lift cam lobes. A latch block disposed on the body surface is slidable by piston and spring means between first and second positions to engage and thereby alternatively latch and unlatch the high-lift followers. In latched position, the rocker arm assembly acts in high-lift mode; in unlatched position, in low-lift mode. | ||||||
| 353 | FLUGZEUG MIT EINEM HOCHAUFTRIEBSSYSTEM | PCT/EP2010/003196 | 2010-05-26 | WO2010136188A1 | 2010-12-02 | RICHTER, Martin; LÜCKEN, Peter |
Flugzeug mit einem Hochauftriebssystem, aufweisend: zumindest ein Flugsteuerungs-Computer (51), an jeweils einem Tragflügel des Flugzeugs angeordnete Hochauftriebskörper, eine mit diesen gekoppelte Antriebsvorrichtung, eine über eine analoge Datenverbindung mit der Antriebsvorrichtung verbundene Ansteuerungsvorrichtung zur Erzeugung von Ansteuerungskommandos zur Einstellung des Verstellzustands der Hochauftriebskörper, eine im Cockpit des Flugzeugs angeordnete Eingabevorrichtung zur Eingabe von Soll-Kommandos zur Verstellung der Hochauftriebskörper sowie Sensoren zum Erfassen eines Verstellzustands der Hochauftriebskörper, die über analoge Signalleitungen mit der Ansteuerungsvorrichtung verbunden sind. Nach der Erfindung ist die Eingabevorrichtung über eine digitale Datenverbindung mit der Ansteuerungsvorrichtung zur Übermittlung von Soll-Kommandos zur Verstellung der Hochauftriebskörper verbunden. Erfindungsgemäß ist die Ansteuerungsvorrichtung im Nutzlastbereich des Flugzeugrumpfs und in einem Bereich (L3) der in Längsrichtung (X) gesehen eingebaut, der sich in Längsrichtung (X) des Flugzeugrumpfs (F3) gesehen erstreckt von einer Stelle, die von der vorderen Seite (F4-1) des Flügelkastens (F4) aus gesehen einen Abstand ((L1 )/3) von einem Drittel der sich von dort bis zur Flugzeugspitze (F1) erstreckenden Rumpflänge (L1) hat, bis zu einer Stelle, die von der hinteren Seite (F4-2) des Flügelkastens (F4) aus gesehen einen Abstand ((L2)/3) von einem Drittel der sich von dort bis zum Rumpfende (F2) am Heck des Flugzeugs (F) erstreckenden Rumpflänge (L2) hat. |
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| 354 | High lift work device | JP2752595 | 1995-01-23 | JPH08198002A | 1996-08-06 | MIYOSHI TADASHI; MIYOSHI TETSUO |
| PURPOSE: To provide a high lift work device equipped with various auxiliary devices so as to facilitate maintenance work of the device having a complicated shape in a high lift position. CONSTITUTION: This device is provided with an elevating floor 3 elevated by a scissorlike link, a first extending floor 8 housed in the rear of the elevating floor 3 and retractable fore and aft, a first floor extending means 9 for extending and retracting the first extending floor 8, and an angle changing means 10 for changing the angle of the first extending floor 8 fore and aft center shaft X of the elevating floor 3. COPYRIGHT: (C)1996,JPO | ||||||
| 355 | Extending/contracting boom type high lift work vehicle | JP2001105490 | 2001-04-04 | JP2002302396A | 2002-10-18 | OHIRA AKIHIKO; KAMEI KENJI |
| PROBLEM TO BE SOLVED: To prevent an elbow part of an extending-contracting boom from colliding with an obstacle by protruding at turning operation time in an extending/contracting boom type high lift work vehicle. SOLUTION: A car body 2 is provided with a freely turnable turning stand 4, a rising-up/falling-down boom 5 capable of freely rising up and falling down, a boom device composed of a freely extensible/contractible extending/contracting boom 6, a workbench 8 arranged in a tip part of this boom device, and an operation control device for controlling operation of the boom device on the basis of an operation signal. The boom device is provided with a position detecting means for detecting a tip position of the rising-up/falling-down boom 5 to the car body 2. The operation control device controls the operation of the boom device so that the tip position of the rising-up/falling-down boom 5 detected by a position detector passes through the inside of a prescribed regulating range S set on the car body side when operating the boom device to constitute the extending-contracting boom type high lift work vehicle 1. COPYRIGHT: (C)2002,JPO | ||||||
| 356 | Ladder | JP2000079165 | 2000-03-21 | JP2001262963A | 2001-09-26 | NAKAO MOTOHIRO |
| PROBLEM TO BE SOLVED: To provide a ladder suitably usable together with a lifting fall preventive apparatus for lifting used in a high lift work or the like, highly safe and satisfactorily operable. SOLUTION: This ladder comprises a substantially reverse U-shaped hook F at the tip of a ladder body L and a connecting metal fitting 8 for attachably and detachably connecting the safety device B1 of the lifting fall preventive apparatus B in the vicinity of the lower end of the hook F. The hook F is mounted in such a manner as to be horizontally rotatable to the ladder body L, and the connecting metal fitting 8 is mounted in such a manner as to be vertically rockable and horizontally rotatable to the hook F. COPYRIGHT: (C)2001,JPO | ||||||
| 357 | Valve characteristic selector device for internal combustion engine | JP19313894 | 1994-08-17 | JPH0861023A | 1996-03-05 | MORITA SHOJI; YAMAKAWA YUKIO; TOMIZAWA NAOMI; TAKEMURA SHINICHI; NAKAMURA MAKOTO |
| PURPOSE: To identify whether a valve gear system is maintained in high lift condition or low lift condition by detecting the large or small of the maximum oscillating angle of a main rocker arm at nocontact. CONSTITUTION: In a valve characteristics selector device in which the valve characteristics of an intake vale and/or exhaust valve can be switched over by a switchover means 80 whereby the maximum oscillating angle of a main rocker arm can be switched over between, large and small, a maximum oscillating angle detector means 50 to detect the large or small of the maximum oscillating angle arranged at the side of the main rocker arm in no-contact state. | ||||||
| 358 | Operation range regulating device for high lift work vehicle with crane | JP2232599 | 1999-01-29 | JP2000219500A | 2000-08-08 | HIRAMI KAZUHIKO; KAJIKAWA HIROTAKE |
| PROBLEM TO BE SOLVED: To prevent the wrong selection of operation range and forgetting of selection in a high lift work vehicle provided with a compact crane device at a position close to a bucket provided at a tip of a boom of the high lift work vehicle by detecting housing position of the crane device, and selecting the operation range on the basis of a result of the detection. SOLUTION: In this high lift work vehicle provided with a bucket and a crane device 7 at a tip of a boom through a position maintaining member 5, at the time of starting the work in the working field, a decision whether the crane device 7 is used or not is performed in response to the kind of the work. In the case of NO, a jib 17 is stood at a housing position, namely, stood vertically, and a pin 16 is fitted in pin holes 13b, 14b corresponding to each other. A dog 30 abuts on a limit switch 31, and the crane device 7 existing at the housing position is thereby detected, and this detecting signal is sent to an operation range selecting means 8 so that the means 8 selects the limited operation range. High lift work is performed within this operation range. COPYRIGHT: (C)2000,JPO | ||||||
| 359 | High-lift device for flight vehicle | JP2012077712 | 2012-03-29 | JP2013203369A | 2013-10-07 | HAYAMA KENJI; ISOTANI KAZUHIDE |
| PROBLEM TO BE SOLVED: To reduce aerodynamic noise generated from a high-lift device without increasing the weight of an airframe or impairing practicality as further as possible.SOLUTION: A high-lift device 3 includes a flap body 11 which is provided to be deployed and accommodated in a rear part of a main wing 2 that generates lift in a flight vehicle, and extends along a wing length direction of the main wing 2. In an end portion 11a of the flap body 11 in an extension direction, void expansion parts 20, 30 are provided for expanding a void between the rear part of the main wing 2 and a front part of the flap body 11 during deployment. | ||||||
| 360 | HIGH LIFT SYSTEM FOR AN AIRCRAFT | PCT/EP2008006484 | 2008-08-06 | WO2009019011A3 | 2009-04-16 | VOSS TIMO; LOERKE JOACHIM |
| The invention relates to a high lift system for an aircraft, comprising a main wing (1), a flap (2) disposed on the main wing (1) of the aircraft that can be adjusted between a retracted position and several extended positions relative to the main wing (1) by means of flap actuating means and a drive device, said system further comprising a carrier part (3; 21) disposed on the main wing (1) to which the flap actuating means are coupled and relative to which the flap actuating means for adjusting the flap (2) can be moved, wherein the carrier part (3; 21) is disposed on the main wing by means of a bearing device (10) comprising an adjusting device with which the orientation of the carrier part relative to the orientation of the main wing can be adjusted. | ||||||
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