| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 401 | High lift work device | JP2005064369 | 2005-03-08 | JP2005162495A | 2005-06-23 | ENOMOTO KAGETOSHI |
| PROBLEM TO BE SOLVED: To provide a high lift work device, simply and quickly coping with a change in angle of a boom and immediately preforming the operation of a fixing mechanism regardless of the state of a work frame to perform work safely. SOLUTION: In this high lift work device, each one end of cylinder members 25a, 26a of two sets of buffer mechanisms 25, 26 with a fixing mechanism is connected to the work frame 23 or a support artm 21, the other ends of piston rods 25b, 26b are connected to the support arm 21 or the work frame 23, circulation of buffer fluids 25g, 26g between two chambers 25e, 25f in the cylinder members 25a, 26a is regulated through an orifice 25h, the rotating speed of the work frame 23 is held down by the buffer action in both directions of expansion and contraction of the piston rods 25b, 26b, and operating arms 25k, 26k are operated by an operating handle 43 and links 42a, 42b to stop the piston rods 25b, 26b so that the work frame 23 is put in the fixed state. COPYRIGHT: (C)2005,JPO&NCIPI | ||||||
| 402 | High-lift system for a wing of an aircraft | US13855995 | 2013-04-03 | US09376204B2 | 2016-06-28 | Christoph Winkelmann |
| A high-lift system for a wing of an aircraft is provided. The high-lift system includes movably held high-lift flaps, at least one drive unit, at least one transmission shaft connected to the drive unit, and several actuator devices, distributed on the transmission shaft and connected to the high-lift flaps, for moving the high-lift flaps. The actuator devices each comprise a driven element and a torque limiting means. In one example, the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with the use of a separate torque transmitting means. If one actuator device is blocked, for example as a result of a defective tooth arrangement or some other defect, the torque to be produced by the intact actuator device increases and triggers its torque limiting means. This ensures synchronous operation and in the case of malfunction prevents damage to or detachment of a flap. | ||||||
| 403 | HIGH-LIFT SYSTEM FOR A WING OF AN AIRCRAFT | US13855995 | 2013-04-03 | US20130277498A1 | 2013-10-24 | Christoph Winkelmann |
| A high-lift system for a wing of an aircraft is provided. The high-lift system includes movably held high-lift flaps, at least one drive unit, at least one transmission shaft connected to the drive unit, and several actuator devices, distributed on the transmission shaft and connected to the high-lift flaps, for moving the high-lift flaps. The actuator devices each comprise a driven element and a torque limiting means. In one example, the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with the use of a separate torque transmitting means. If one actuator device is blocked, for example as a result of a defective tooth arrangement or some other defect, the torque to be produced by the intact actuator device increases and triggers its torque limiting means. This ensures synchronous operation and in the case of malfunction prevents damage to or detachment of a flap. | ||||||
| 404 | PROCESS FOR ASSEMBLING AIRCRAFT CONTROL SURFACES | PCT/IB2015/057699 | 2015-10-08 | WO2016055964A1 | 2016-04-14 | CONVERSANO, Pasquale; LO CASALE, Alessandro |
A process for assembling aircraft control surfaces (1, 1'), in particular high-lift devices and wing portions, allows implementing smooth control surfaces in short times, wherein the control surface is defined by an upper skin (2) and by a lower skin (9), the upper skin being destined to form the leading edge (4) of the control surface by means of the connection to a front spar (3), wherein the upper skin and the lower skin are made of a laminar composite material which, not yet hardened, is fastened to structural elements (3, 5, 6, 7) of the control surface by means of an adhesive; and wherein the resin of the composite material and the adhesive are hardened simultaneously in autoclave. |
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| 405 | MAIN ROTOR SYSTEM FOR HELICOPTERS | PCT/US9504929 | 1995-04-24 | WO9529842A2 | 1995-11-09 | ARLTON PAUL E; ARLTON DAVID J |
| A high-lift main rotor system (1) is provided for a full-size or model helicopter (15). Main rotor system (1) includes rotor blades (100) and subrotor blades (84) for producing aerodynamic lift. The subrotor blades (84) act to augment control and stability of main rotor (1). Main rotor blades (100) are configured to include airfoiled cross sections (103-107) of varying shape and are mounted to a rotor hub (77) to fold within limits about a horizontal flapping axis (10). A linkage including swashplate (140) is provided for transmitting pilot control commands to the rotating rotor blades (100). | ||||||
| 406 | Working vehicle | JP2009168088 | 2009-07-16 | JP2011020812A | 2011-02-03 | MAEDA MASAKATSU |
| <P>PROBLEM TO BE SOLVED: To provide a high lift work vehicle capable of avoiding run-away on a sloping road, and capable of securing the safety of work in an attitude of floating one wheel by being held so as not to rotate in the inverse direction of the travel direction of a travel motor by constituting a travel control valve for controlling the flowing direction of a hydraulic fluid according to the operation direction of an operation lever. <P>SOLUTION: The high lift work vehicle travels by driving a front wheel or a rear wheel as a drive wheel, and has a travel operation lever, a variable displacement hydraulic pump P1 driven by a prime mover and capable of delivery control according to the operation of the travel operation lever, and first and second travel motors M1 and M2 rotatively driven by receiving the supply of oil from the hydraulic pump P1 and driving the drive wheel, and has first and second travel control valves 20 and 30 for allowing a flow of the oil in a direction for driving the first and second hydraulic motors M1 and M2 based on the operation of a travel operation means but regulating the flow of the oil in the inverse direction of the flow. <P>COPYRIGHT: (C)2011,JPO&INPIT | ||||||
| 407 | Safety device of high-lift work vehicle for slope work | JP2000261843 | 2000-08-30 | JP2002068698A | 2002-03-08 | SAWAFUJI YOSHITOSHI; KOBAYASHI MASAKI |
| PROBLEM TO BE SOLVED: To provide a safety device of a high-lift work vehicle for the slope work capable of preventing a boom from being bent by the reaction force from a slope due to the drive of a slope work machine. SOLUTION: This high-lift work vehicle for the slope work is provided with an expansion boom 2 turnably and erectably fitted to a vehicle 1, a work floor 3 fitted to the tip of the expansion boom 2 turnably in the horizontal plane via an attitude keeping member 5, and the work machine 6 fitted to the work floor 3 to perform the slope drilling work via the power from a work machine driving power unit 8. When the detection signal from a work machine driving force sensor 19 detecting the driving force of the work machine 6 working on the slope exceeds the prescribed value determined based on the detection signal from a boom length sensor 15 and the detection signal from a boom angle sensor 16, the driving force of the work machine 6 is reduced so that the detection signal from the work machine driving force sensor 19 becomes the prescribed value or below. COPYRIGHT: (C)2002,JPO | ||||||
| 408 | AIRPLANE ENGINE PYLON COMPRISING AT LEAST ONE PROTRUDING ELEMENT TO GENERATE A VORTEX OF THE AIRFLOW | US12403429 | 2009-03-13 | US20090230251A1 | 2009-09-17 | Cyril Bonnaud; Stephanie Dantin; Marjorie Defos; Thierry Fol |
| A wing arrangement of an aircraft has a wing and at least one pylon for suspending an engine below the wing. The wing has a leading edge with a high-lift device, which is able to move between a deployed position in which the high-lift device projects forward of the leading edge, and which is interrupted in a forward intermediate region of the wing located at the leading edge, the pylon having a forward edge extending forward of the leading edge of the wing between a forward upper portion connected to the wing in the forward intermediate region and a forward lower portion connected to a nacelle of the engine. An element of narrow elongate shape protrudes longitudinally from the forward edge and, during flight at a high angle of attack of the aircraft, generates a vortex of aerodynamic flow that is propagated toward the forward intermediate region above the wing. | ||||||
| 409 | LEADING EDGE HIGH-LIFT DEVICE | EP16188072.9 | 2016-09-09 | EP3176077A1 | 2017-06-07 | Kawai, Ronald Tatsuji; Tompkins, Daniel Michael; Liebeck, Robert Hauschild; Elmer, Kevin Robert; Dickey, Eric David |
A leading edge high-lift device (22), that may be deployable from a wing (12) of an aircraft, may include a leading edge (26) and a trailing edge (28). A lower surface (32) and an upper surface (30) may both extend between the leading edge (26) and the trailing edge (28). A trailing edge region (34) may be defined by the trailing edge (28) and an adjacent region thereto. A shaping device (36) may be disposed at the trailing edge region (34) and may be movable between a non-activated position and an activated position.
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| 410 | METHOD AND DEVICE FOR PROVIDING AUTOMATIC LOAD ALLEVIATION TO A HIGH LIFT SURFACE SYSTEM, IN PARTICULAR TO A LANDING FLAP SYSTEM, OF AN AIRCRAFT | US12086467 | 2006-12-08 | US20110084173A9 | 2011-04-14 | Andreas Fleddermann; Wolfgang Hartwig; Alexandre Darbois; Martin Richter |
| A method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device at least one high lift surface, which is actuated by means of a local mechanical final control element, is brought to a predetermined position by a central drive unit that is connected by way of a rotary shaft arrangement to the local final control element by generating a torque transmitted by the central drive unit to the rotary shaft arrangement. If a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit to the rotary shaft arrangement is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed. | ||||||
| 411 | HIGH LIFT SYSTEM FOR AN AIRPLANE, AIRPLANE SYSTEM AND PROPELLER AIRPLANE HAVING A HIGH LIFT SYSTEM | US13264393 | 2010-04-16 | US20120032030A1 | 2012-02-09 | Ina Ruckes; Peter Scheffers; Michael Willmer; Olaf Spiller |
| A high-lift system of an aeroplane is described, including one or more high-lift flaps, an activation device with an activation function for generating adjustment commands for adjusting the adjustment state of the high-lift flaps, and a drive device coupled with the high-lift flaps, which is configured such that on the basis of activation commands the high-lift flaps are adjusted between a refracted adjustment state and an extended adjustment state. The activation function, on the basis of input values, generates adjustment commands and transmits these to the drive device for adjusting the high-lift flaps. The activation function has a function for the automatic retraction of the high-lift flap in flight, which in a flight condition in which the high-lift flap has assumed an extended adjustment state, whilst taking into account an engine thrust and a minimum flight altitude, generates an activation command, in accordance with which the high-lift flap retracts. | ||||||
| 412 | Method for determining a state of a component in a high lift system of an aircraft, high lift system of an aircraft and aircraft having such a high lift system | EP14190338.5 | 2014-10-24 | EP3012192A1 | 2016-04-27 | Neb, Eugen; Van Bruggen, Jan-Arend; Brady, Michael; Wyrembek, Jörg; Criou, Olivier; Haserodt, Jan; Heintjes, Mark |
A method for determining a state of a component in a high lift system (2) of an aircraft is proposed, the high lift system (2) comprising a central power control unit (4) for providing rotational power by means of a transmission shaft (8, 10); and drive stations (12) coupled with the power control unit (4) and movable high lift surfaces (18); the method comprising the steps of acquiring in an extended position in flight at least one first position of a first position pick-off unit (20) coupled with the component, which is mechanically coupled with one of the high lift surfaces (18), and which is coupled with one of the drive stations (12); acquiring in flight a second position of a second position pick-off unit (20) arranged in or at the central power control (4) unit in the extended position; determining a deviation between a first measure based on the first position and a corresponding second measure based on the second position in the extended position; determining, whether the deviation exceeds a predetermined threshold; and generating a signal indicating an abnormal state of the component in case the deviation exceeds the predetermined threshold.
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| 413 | Method for determining a state of a component in a high lift system of an aircraft, high lift system of an aircraft and aircraft having such a high lift system | EP14190333.6 | 2014-10-24 | EP3012191A1 | 2016-04-27 | Neb, Eugen; van Bruggen, Jan-Arend; Brady, Michael; Wyrembek, Jörg; Criou, Olivier; Haserodt, Jan; Heintjes, Mark |
A method for determining a state of a component in a high lift system (2) of an aircraft is proposed, the high lift system (2) comprising a central power control unit (4) for providing rotational power by means of a transmission shaft (8, 10); and drive stations (12) coupled with the power control unit (4) and movable high lift surfaces (18); the method comprising the steps of acquiring in an extended position in flight at least one first position of a first position pick-off unit (20) coupled with the component, which is mechanically coupled with one of the high lift surfaces (18), and which is coupled with one of the drive stations (12), acquiring on ground at least one second position of the first position pick-off unit (20) in the extended position, determining a deviation between a measure based on the first position and an associated measure based on the second position of the first position pick-off unit (20) between ground and flight, determining, whether the deviation exceeds a predetermined threshold and generating a signal indicating an abnormal state of the component in case the deviation exceeds the predetermined threshold.
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| 414 | Aircraft airfoil with close-mounted engine and leading edge high lift system | US09523421 | 2000-03-10 | US06364254B1 | 2002-04-02 | Peter May |
| An arrangement of an airfoil, such as a main wing of an aircraft, includes a close-mounted engine on a short pylon connected to the airfoil, an inboard slat arranged inboard from the engine pylon along the leading edge of the airfoil, and an auxiliary high lift device. An open cut-out space is formed between the outboard edge of the inboard slat, the engine pylon, and the leading edge of the airfoil when the inboard slat is extended. The auxiliary high lift device is configured and arranged to be extendable into an extended position in which it aerodynamically covers or closes the cut-out space. The auxiliary high lift device is a movable high lift component that can be retracted into a retracted position in which it is recessed and integrated into the outer contour of the engine nacelle and/or the pylon. Thereby, the structural arrangement and mechanisms necessary for extending and retracting the auxiliary high lift device are simplified, and the weight and costs are reduced. | ||||||
| 415 | 고소작업차 과하중 방지장치 | KR1020080006277 | 2008-01-21 | KR1020090080369A | 2009-07-24 | 이승목; 장세연; 김형장; 송시명; 유지헌; 도성득 |
| An overload prevention device for a high-lift work vehicle is provided to secure the safety of a worker for high-lift work by informing a worker whether to exceed the maximum allowable weight to load on a basket or not and controlling the working radius of a basket to turn downward only. An overload prevention device for a high-lift work vehicle comprises a vertical joint(5) installed at the end of a high-lift work vehicle boom(3) and changing the location of a basket(9) at the appointed angle in the vertical direction, a horizontal joint(6) coupled with the vertical joint by a vertical joint connecting pin(1) and changing the location of the basket at the appointed angle in the horizontal direction, a basket supporter(8) coupled with the horizontal joint by a horizontal joint connecting pin(2) and supporting the basket from the lower part and securing the safety of a worker who works on the basket, a strain gage mounted to the basket supporter and measuring the loadage of the basket, and a high-lift work vehicle control box controlling the entire movement of a high-lift work vehicle inn connection with the current loadage of the basket. | ||||||
| 416 | VARIABLE VALVE LIFT APPARATUS | KR20070131566 | 2007-12-14 | KR20090064011A | 2009-06-18 | KWAK YOUNG HONG; KWON KI YOUNG; SHIN KI UK; KONG JIN KOOK; CHANG KYOUNG JOON |
| A variable valve lift device is provided to select an optimal valve lift according to the operating state of the engine because a low lift mode, a high lift mode and a CDA mode are implemented. A variable valve lift device comprises a high lift cam(110); a low lift cam(120) which is placed between the high lift cams; a high lift tappet body(310) which always contacts with the high lift cam; a tappet body including a low lift tappet body which selectively contacts with the low lift cam; an inner column(400) which is connected to a valve and reciprocates in the low lift tappet body; a supporting part(500) equipped in the lower part of the tappet body; a lost motion elastic member(600) which is placed between the supporting part and tappet body in order to provide the restoration to the tappet body; a first joint which selectively joins the high lift tappet body and the low lift tappet body; and a second joint which selectively joins the low lift tappet body and the inner column. | ||||||
| 417 | Dispositif pour stabiliser un ski | EP85810215.5 | 1985-05-07 | EP0162012A1 | 1985-11-21 | Cholat-Serpoud, Gérard; Delery, Marc-Georges; Brossard, Jean-Pierre |
Ce dispositif comporte une face profilée (6) fixée à la spatule (2) du ski (1) par deux plaques latérales (7) qui créent un effet d'allongement transversal de la face profilée (6). Cette dernière présente le profil de la face inférieure d'une aile à forte portance de manière à stabiliser l'extrémité avant du ski en créant une portance dont la pente est positive en fonction de l'augmentation de l'angle d'incidence de l'air pour combattre l'instabilité aérodynamique de la spatule (2). |
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| 418 | High-lift system for an aircraft | US12376258 | 2007-08-06 | US08302913B2 | 2012-11-06 | Bernhard Schlipf |
| An exemplary high-lift system for an aircraft includes a wing, a high-lift flap coupled to the wing, a kinematic element which is driven by a drive device, and a flap lever structured and arranged to rotate via an actuating drive between a retracted position in which the high-lift flap complements a wing profile and a plurality of extended positions in which a slot of a given width is formed between the wing and the high-lift flap. A first end of the flap lever is coupled to the high-lift flap. A second end of the flap lever is coupled to the kinematic element and is capable of rotating relative thereto via a first rotation point. The kinematic element is structured and arranged to rotate relative to a second rotation point that is fixed in position relative to the wing. The first rotation point is separated by a predetermined distance from the second rotation point. | ||||||
| 419 | HIGH LIFT MOWER FOR PLASTIC MULCH | US12436331 | 2009-05-06 | US20090277149A1 | 2009-11-12 | James R. Adkins |
| A high-lift mower is disclosed. The mower includes a frame, at least two wheels disposed along opposite sides of the frame and having a space between them, and a blade rotation mechanism, mounted to the frame, for providing a rotational force relative to the frame. A blade assembly is coupled to the blade rotation means. The blade assembly comprises a plurality of cutting blades. Each of the plurality of blades includes a front face having a cutting blade and a rear face disposed away from the front face. The rear face has a lift portion. A roller assembly is adjustably coupled to the frame for, upon engagement with a surface located in the space between the pair of wheels, maintaining the blade assembly a predetermined distance above the surface. A blade assembly and a roller assembly for use with the high-lift mower are also disclosed. | ||||||
| 420 | HIGH LIFT SYSTEM FOR AN AIRCRAFT | US13608035 | 2012-09-10 | US20130240676A1 | 2013-09-19 | Burkhard Gölling |
| A high lift system with a main wing and control flaps, wherein the respective guiding device are at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least two inlet ducts running along the main wing chordwise direction with in each case at least one inlet, which device is located on or underneath the lower surface of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet ducts in a fluid-communicating manner, and has at least one outlet, which is located on the upper surface of at least one regulating flap and/or with respect to the main wing chordwise direction in the rear third of the main wing of the high lift system. | ||||||
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