[go: up one dir, main page]

WO2018192692A1 - Appareil de levage et procédé permettant de soulever un aéronef - Google Patents

Appareil de levage et procédé permettant de soulever un aéronef Download PDF

Info

Publication number
WO2018192692A1
WO2018192692A1 PCT/EP2018/051638 EP2018051638W WO2018192692A1 WO 2018192692 A1 WO2018192692 A1 WO 2018192692A1 EP 2018051638 W EP2018051638 W EP 2018051638W WO 2018192692 A1 WO2018192692 A1 WO 2018192692A1
Authority
WO
WIPO (PCT)
Prior art keywords
lifting
lifting device
lifter
hydraulic
aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/EP2018/051638
Other languages
German (de)
English (en)
Inventor
Andreas Wolk
Ulrich Ockenfuss
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hydro System KG
Original Assignee
Hydro System KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hydro System KG filed Critical Hydro System KG
Publication of WO2018192692A1 publication Critical patent/WO2018192692A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/40—Maintaining or repairing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/50—Handling or transporting aircraft components
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B66—HOISTING; LIFTING; HAULING
    • B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
    • B66F3/00—Devices, e.g. jacks, adapted for uninterrupted lifting of loads
    • B66F3/24—Devices, e.g. jacks, adapted for uninterrupted lifting of loads fluid-pressure operated
    • B66F3/25—Constructional features
    • B66F3/36—Load-engaging elements
    • B66F3/38—Load-engaging elements adjustable relative to piston

Definitions

  • the invention relates to a lifting device and a method for lifting an aircraft.
  • the lifter includes a foot structure and a hydraulic lifter carried by the foot structure.
  • the hydraulic jacks Before lifting the aircraft, the hydraulic jacks have to be very accurate in reference to the point of attack of the aircraft posi ⁇ tioniert. In order to avoid the introduction of high longitudinal forces during the lifting process, the hydraulic lifters must be placed in a vertical position. Here Müs ⁇ sen inclination and unevenness of the floor can be compensated. Is the inclination of the hydraulic jack changed, changed ⁇ also the position of the point of attack of the aircraft changed. This interaction complicates the alignment process, which often takes longer than 30 minutes for large heavy lifters, and up to five with high physical effort Operator, significantly.
  • the lifting device can hold mounted on the wheels height adjustable wheels and backing pad to ⁇ . After the height of the wheels is adjusted so that the hydraulic jack is in a vertical position, it is supported by turning the backing pads down on the ground.
  • the invention has the object vorzu ⁇ a lifter, which can be adjusted with reduced effort.
  • the object is solved with the features of the independent claims.
  • Advantageous embodiments are specified in the subclaims.
  • the hydraulic lifter is suspended on the foot structure via a pivotable mounting. Due to the pivotal mounting of the hydraulic lifter can be aligned without changing the position of the foot structure relative to the ground. The effort in adjusting the lifting device is reduced.
  • the pivot axis of the bearing perpendicular to the axis of the hydraulic jack may be directed ⁇ .
  • Axis of the hydraulic lifter designates the direction in which the lifting piston is extended out of the hydraulic lifter.
  • the pivot axis may be arranged at a distance from the ground. Based on the retracted state of the lifting device, the distance from the pivot axis to the ground at least 40%, preferably at least 60%, more preferably ⁇ correspond to at least 80% of the distance that has An docking to the ground. In the retracted state to the ⁇ dock decorations is in its lowermost position, so it has the lowest possible distance from the floor. Docking area refers to the part the lifting device, which is at the point of attack of the aircraft ⁇ when the aircraft is raised.
  • the lifting device according to the invention may be designed so that the center of gravity of the hydraulic jack is located lower than the pivot axis when the hydraulic jack stand to ⁇ is in the retracted. A vertical orientation of the lift can then be achieved by the influence of gravity. When the hydraulic jack can swing freely relative to the foot structure, it will automatically assume a vertical position by gravity.
  • the lifting device according to the invention can be arranged so that even in the extended state of the hydraulic lifter, the center of gravity of the hydraulic lifter is lower than the
  • Pivot axis When extended, the docking area is in the uppermost position and thus has the greatest distance to the ground. In order to shift the center of gravity downward, an additional weight arranged below the pivot axis can be attached to the hydraulic jack. In an exemplary
  • the additional weight extends annularly around the hydraulic lifter around.
  • the hydraulic jack may be pivotally to the leg structure about a first pivot axis and a second pivot axis relative ge ⁇ superimposed.
  • the second pivot axis may be aligned at right angles to the first pivot axis.
  • the first pivot axis and the second pivot axis can span a plane.
  • the first pivot axis may have a fixed orientation relative to the leg structure, and in particular parallel to the ground out ⁇ be directed.
  • the second pivot axis may have a fixed Reg ⁇ tung relative to the hydraulic jack, and in particular be aligned at right angles to the hydraulic jack.
  • the Both pivot axes may be connected by an intermediate piece, which may extend around the hydraulic lifter in an annular manner.
  • the lifter may further comprise a stop limiting the pivot area which is adapted to restrict the pivotal movements possible by the pivotal mounting.
  • the stop may define a working area that extends around a center position of the hydraulic jack.
  • the hydraulic lifter can hit the stopper when the working area limit is reached.
  • the stop may extend annularly around the hydraulic jack.
  • the center position of the work area may coincide with the horizontal orientation of the foot structure with the vertical position of the hydraulic lifter.
  • the work area may extend in a cone around the center position. The stop can, starting from the middle position in a
  • Swivel angle between, for example, 1 ° and 5 ° to be arranged.
  • the lifter may include a holding device spaced from the pivotable bearing and having a mode in which pivotal movement of the hydraulic lifter relative to the foot structure is permitted.
  • the holding device includes a locked mode in which it holds the hydraulic lifter in a defined pivotal position relative to the leg structure.
  • the holding device can also have a partially locked mode, so that the hydraulic lifter is held in a fixed orientation when on the holding device acting force is below a predetermined threshold, and so that a pivoting movement is permitted when the force acting on the holding means above the
  • Threshold is.
  • the threshold value can be adjustable.
  • the leg structure may include struts, wherein each strut extends from a foot to a structural member, and wherein the structural member supports the pivotal mounting.
  • the lifter may comprise three struts extending from the structural member towards the ground.
  • the holding device may be configured to extend between one or more of the struts and the hydraulic jack.
  • the holding device comprises a length-adjustable element which extends between a strut and the hydraulic jack.
  • a length-adjustable element may extend from the plurality of struts to the hydraulic lifter.
  • the length-adjustable element may comprise a spindle drive.
  • the spindle drive can be guided in a thread which is formed on the strut.
  • the length-adjustable element may comprise a chain.
  • Chain stands here as a generic term for a component which is rigid in the tensioned state against tensile forces and which permits length changes in a relaxed state.
  • the chain can be brought into a ⁇ ent-tensioned state when the orientation of the hydraulic jack is adjusted.
  • the chain can be brought into a ge ⁇ tensioned state when the hydraulic jack in a certain orientation.
  • the holding device may comprise a plurality of chains, in particular three chains, which extend in different directions, starting from the hydraulic jack. One end of the chain can be connected to a spindle drive.
  • the length-adjustable element may comprise a spring.
  • the holding device may comprise a plurality of springs, in particular three springs, which extend in different directions, starting from the hydraulic jack. One end of the spring can be connected to a spindle drive.
  • the length-adjustable element is designed as an actuating cylinder, in which an actuating piston is guided in a cylinder.
  • One end of the adjusting cylinder may be connected to the foot structure, the other end of the adjusting cylinder may be connected to the hydraulic jack.
  • the articulation point between the actuator cylinder and the hydraulic lifter may be near the bottom of the hydraulic lifter.
  • the articulation point on the Stre- be may be located higher than the articulation point of the hy draulic ⁇ lifter, so that the adjusting cylinder extends obliquely upward.
  • the actuating cylinder can be a hydraulic
  • the actuator cylinder may include a clearance mode in which the piston is free to move in the cylinder under the influence of an external force. Through the clearance mode, the possibility may be given to the hydraulic jack, is automatically vertically reinforcedrich ⁇ th under the influence of gravity.
  • the actuator cylinder may include a locked mode in which the piston does not change its position in the cylinder even under the influence of external forces. After the hydraulic jack is vertically aligned, the jack can be placed in locked mode to lock the hydraulic jack in this position. Additionally or alternatively, the adjusting cylinder may comprise a partially locked mode, in which the actuating cylinder is locked as long as the force acting on the piston is able to dress ⁇ ner than a predetermined threshold value. When the threshold is exceeded, the piston can move within the cylinder.
  • the actuating cylinder can for this purpose with a
  • Overload valve be provided, which opens when a predetermined pressure value is exceeded.
  • the overload valve can be sett ⁇ bar.
  • a holding device which is arranged between the lower end of the hydraulic jack and the ground.
  • the holding device may be adjustable in height, so that it rests in a first state on the ground and is lifted in egg ⁇ nem second state from the ground. If the holding device on the ground, impedes a Schwenkbewe ⁇ supply of the hydraulic jack relative to the leg structure. In the lifted state, the pivoting movement is not restricted by the holding device.
  • the pressure with which the holding device is supported on the floor can be adjustable.
  • the holding device may comprise rollers, so that a movement of the holding device relative to the floor is also possible when the holding device rests on the floor.
  • the holding device can in this way give an adjustable resistance to pivoting movements of the hydraulic lifter.
  • the rollers may be spring loaded.
  • the rollers may be formed as balls, so that the holding device can roll in any direction.
  • a ball joint may be formed between the hydraulic jack and the holding device. This makes it possible that a surface of the holding device facing the bottom can be aligned parallel to the ground independently of the pivoting position of the hydraulic lifter.
  • the lifting device according to the invention can be used for lifting aircraft.
  • a hydraulic piston can be moved out of the hydraulic jack by supplying hydraulic fluid.
  • the docking surface may be located at the upper end of the piston.
  • the hydraulic jack can be designed in several stages.
  • An arranged in the hydraulic jack piston may be designed as a piston tube, in whose interior a second piston is guided with a smaller diameter.
  • the second piston can in turn be designed as a piston tube for guiding an even smaller piston.
  • the lifting cylinder can comprise, for example, between three and six stages.
  • the lifting device may have a force acting on the docking spring storage.
  • the spring accumulator can expand.
  • the spring accumulator can compensate both pressure losses due to a temperature drop as well as a Nach ⁇ guide the extension movement of the uppermost pressurized piston tube as a result of a last Ver vertical movement.
  • the spring accumulator comprises a spring element, which is arranged between the docking surface and the upper end of egg ⁇ nes raised with the lifting cylinder piston. If a load is lifted via the docking surface, then the spring element is compressed. If the docking surface we ⁇ kende load reduced, the spring element may expand again.
  • the spring element may be a mechanical spring, for example in the form of a spiral spring.
  • the spring accumulator can also be designed as a bladder accumulator, in which the hydraulic pressure acting on the reciprocating piston also acts on a closed gas volume. The gas is compressed by the pressure. The effect is comparable to the previously described spring element.
  • lifting devices When lifting an aircraft, usually at least three lifting devices are used. Two lifting devices can be arranged in the same longitudinal position of the aircraft, for example in the region of the wings. A third lifter occupies a different longitudinal position and is arranged, for example, in a front portion of the aircraft.
  • the lifting device according to the invention can be designed so that the hydraulic lifter during a lifting a
  • the invention further relates to a set of at least three lifting devices, comprising a first lifting device, which is in a locked state when lifting an aircraft, and comprising a second lifting device, which is designed, when lifting the same aircraft, a swivel motion superimposed on the lifting movement. to perform movement.
  • the kit may include two lifters that are locked when the aircraft is lifted. These two lifting devices preferably engage in dersel ⁇ ben longitudinal position on the aircraft at, for example in the loading area of the wings.
  • the third lifting device may engage the aircraft in another longitudinal position, for example in a forward section of the aircraft. This third lifting device is designed to perform the lifting movement superimposed Schwenkbe ⁇ movement.
  • Locked condition means that the hydraulic lifter maintains its orientation relative to the lifting structure of the lifter during the lifting operation.
  • the lifting ⁇ devices of the set can be designed for a simultaneous lifting movement.
  • the lifting apparatus in which the lifting movement is superimposed with a Schwenkbewe ⁇ supply can in particular be in a partly locked state.
  • the invention also relates to a method for lifting an aircraft, in which a lifting device beneath an attack ⁇ point of the aircraft is located, and in which a hydrau ⁇ Lischer lifter is pivoted relative to a foot structure of the lifting device before the hydraulic lifter at the Attack ⁇ point of the aircraft is applied.
  • a holding device acting on the hydraulic lifter can be brought into a state in which the hydraulic lifter can oscillate freely relative to the foot structure in order to move the hydraulic lifter align hydraulic lifters to suit the point of attack of the aircraft.
  • the holding means can be brought into a blocked or partially blocked state. If the aircraft is in the raised state, the holding device may be in a locked or partially locked state.
  • the holding device When lowering the hydraulic jack from the raised state of the aircraft, the holding device may be in a locked or partially locked state. This may in particular include the phase in which the docking area is released from the point of attack of the aircraft. This uner ⁇ wish pendulum movements of the hydraulic jack can be excluded, through which the aircraft could be damaged.
  • the invention also relates to a method for lifting an aircraft, in which a first lifting device acts on the aircraft and in which a second lifting device engages the aircraft in a longitudinal position deviating from the first lifting device.
  • the lifters perform a stroke movements ⁇ supply simultaneously.
  • the lifting movement of the first lifting device is superimposed on a pivoting movement of a hydraulic lifter relative to a foot structure of the first lifting device.
  • the lifting movement of the first lifting device may extend over a different stroke than the lifting movement of the second lifting device.
  • the method can be developed with further features that are described in the context of the lifting device according to the invention.
  • the lifting device can be fortgebil ⁇ det with other features that are described in the context of the inventive method.
  • Fig. 2 a second embodiment of an inventive
  • FIG. 3 shows a detail of the embodiment according to FIG. 2 in an enlarged view
  • Fig. 4 a further embodiment of an inventive
  • Fig. 5 a further embodiment of an inventive
  • Fig. 6 a further embodiment of an inventive
  • FIG. 7 shows a detail of the embodiment according to FIG. 7 in an enlarged view
  • Fig. 8 a schematic representation of the invention
  • a strut 15 extends to a structural component 16.
  • the base plates 14, the struts 15 and the structural component 16 together form ei ⁇ ne foot structure of the lifting device.
  • a cardan suspension 18 is formed, via which a hydraulic jack 19 is suspended on the foot structure 14, 15, 16.
  • the gimbal 18 includes a first pivot axis 20 and a second pivot axis 20
  • the focus of the hydraulic jack 19 is disposed below the gimbal 18 so that the hydrauli cal ⁇ lifter 19 aligns in a vertical position under the influence of gravity from al- leash. It is thus si ⁇ cher adopted that the piston 22 of the hydraulic jack 19 is extended vertically upwards.
  • a tank 23 for hydraulic fluid is arranged at the lower end of the hydraulic jack 19, a tank 23 for hydraulic fluid is arranged.
  • a stop 24 extends annularly around the tank 23 around. The stop 24 limits the pivoting angle by which the hydraulic jack 19 can move away from vertical alignment.
  • the lifting device according to the invention can be used to a
  • the lifting device is arranged to below the flight ⁇ product 31, so that a arranged at the upper end of the lifter 19 hydrauli ⁇ rule docking surface 25 is disposed below a point of attack of the aircraft.
  • the docking surface 25 is brought to the attack ⁇ point of the aircraft into engagement, so that the aircraft can be raised.
  • the hydraulic lifter 19 is designed in multiple stages, so that a larger stroke is possible.
  • the center of gravity of the hydraulic jack 19 is arranged below the gimbal 18 only when the hydraulic jack 19 is in the retracted state.
  • the vertical orientation of the hydraulic jack 19 should therefore be made in the retracted state.
  • the extended state which is shown in Fig. 2, is the
  • the lifter also includes a bladder accumulator 26 in which a sealed volume of gas is exposed to the hydraulic pressure applied in the hydraulic lifter 19.
  • the hydraulic pressure compresses the gas volume.
  • the volume of gas may expand.
  • pressure losses can be compensated, which occur for example as a result of ei ⁇ nes temperature drop.
  • the docking surface 25 is supported by a coil spring 27 relative to the upper portion of the reciprocating piston 22.
  • the coil spring 27 When lifting a load, the coil spring 27 is compressed.
  • the coil spring 27 forms a spring accumulator, the effect of which is comparable to the bladder accumulator 26.
  • the embodiment shown in Fig. 4 is provided with an additional weight 28 which extends around the tank 23 at the lower end of the hydraulic see lifter 19 around.
  • a spindle drive 29 extends to the hydraulic jack 19.
  • the spindle drive 29 is mounted in a thread of the strut 15.
  • a chain and a spring 35 are arranged one behind the other. The spring 35 can be tensioned differently by pressing the spindle drive 29.
  • ⁇ ven may be provided only one chain, instead of the combination of chain and spring.
  • FIG. 5 extends from each of the struts 15, a control cylinder 30 to the hydraulic jack
  • the actuating cylinder 30 are hydraulically driven, so that the actuating piston can specifically approach certain positions.
  • the adjusting cylinders 30 can be brought into a first state in which the adjusting pistons can be moved freely. In this state, the hydraulic jack 19 can align itself under the influence of gravity in the vertical position. Once this is done, the actuator cylinders 30 can be placed in a locked state, so that the hydraulic jack 19 is held firmly in this position.
  • the actuating cylinders 30 can be placed in a partially locked state in which the hydraulic jack 19 is held firmly in its orientation as long as the on the
  • Actuator 30 is acting force below a predetermined threshold. When the threshold value is exceeded, a pivoting movement of the hydraulic lifter 19 is permitted.
  • FIGS. 6 and 7 comprises a Stützplat ⁇ te 36 which is connected via a handwheel 37 height adjustable with the lower end of the hydraulic jack 19.
  • the support plate 36 is provided with three spring-loaded rollers 38, which protrude downwards from the support plate 36.
  • the rotary wheel 37 can be actuated to lift the support plate 36 from the ground. If the hydraulic jack 19 has the correct position, the tricycle 37 can be actuated to drive the support plate 36 down so that the rollers 38 rest on the ground. A higher force is then required to pivot the hydraulic jack 19.
  • an aircraft 31 stands on its chassis 32.
  • the front section of the aircraft 31 is arranged somewhat lower than the rear section, so that the aircraft 31 has a longitudinal incline.
  • Fig. 8B shows the aircraft 31 in the raised state and with retracted landing gear.
  • Three lifters 33, 34 are disposed below the aircraft 31 and extended so that the fuselage of the aircraft 31 extends horizontally.
  • the stroke of the front arranged lifting device 34 is thus slightly larger than the stroke of the two lifting devices 33, which are arranged in the region of Tragflä ⁇ chen.
  • a lifter acting as a support may be attached to a fourth point of application.
  • the two lifting devices 33 in the region of the wings are in the locked state, so that the docking surfaces 25 are exactly vertical. be lifted right up.
  • the lifting device 34 which engages in the front section of the aircraft 31, the hydrau ⁇ metallic lifters 19 can perform a pivotal movement relative to the leg structure 14, 15, 16th
  • the lifting movement of the reciprocating piston 22 is superimposed with such Schwenkbe ⁇ movement. Due to the superimposed pivoting movement, a distance compensation between the lifting devices 33, 34 is effected, which is required due to the different stroke paths of the lifting device 33, 34.

Landscapes

  • Engineering & Computer Science (AREA)
  • Transportation (AREA)
  • Manufacturing & Machinery (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Geology (AREA)
  • Mechanical Engineering (AREA)
  • Structural Engineering (AREA)
  • Handcart (AREA)

Abstract

L'invention concerne un appareil de levage d'un aéronef (31), comportant une structure de base (14, 15, 16) et un élévateur hydraulique (19) porté par la structure de base (14, 15, 16). L'élévateur hydraulique (19) est suspendu à la structure de base (14, 15, 16) par l'intermédiaire d'un support pivotant (18). L'invention permet de mettre plus facilement l'élévateur hydraulique (19) dans une orientation verticale et de l'arrimer au point d'attaque de l'aéronef. L'invention concerne par ailleurs un procédé permettant de soulever un aéronef (31).
PCT/EP2018/051638 2017-04-21 2018-01-24 Appareil de levage et procédé permettant de soulever un aéronef Ceased WO2018192692A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017206771.3A DE102017206771A1 (de) 2017-04-21 2017-04-21 Hebegerät und Verfahren zum Anheben eines Flugzeugs
DE102017206771.3 2017-04-21

Publications (1)

Publication Number Publication Date
WO2018192692A1 true WO2018192692A1 (fr) 2018-10-25

Family

ID=61189410

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2018/051638 Ceased WO2018192692A1 (fr) 2017-04-21 2018-01-24 Appareil de levage et procédé permettant de soulever un aéronef

Country Status (2)

Country Link
DE (1) DE102017206771A1 (fr)
WO (1) WO2018192692A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109319165A (zh) * 2018-11-05 2019-02-12 西安飞机工业（集团）有限责任公司 一种飞机框保型定位架和定位方法
CN112550754A (zh) * 2020-12-24 2021-03-26 芜湖中科飞机制造有限公司 一种小型飞机装配用的尾部托坠平衡装置
CN113581488A (zh) * 2021-07-30 2021-11-02 江西昌河航空工业有限公司 一种直升机主桨毂安装工装及使用方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111547262B (zh) * 2020-04-15 2022-04-19 中国商用飞机有限责任公司 飞机尾撑杆组件

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB926254A (en) * 1960-09-06 1963-05-15 Douglas Aircraft Co Inc Air glided load support
EP0287044A1 (fr) * 1987-04-16 1988-10-19 Hydro-Gerätebau GmbH & Co. KG Hebezeuge Installation pour soulever des avions
WO2007093212A1 (fr) * 2006-02-16 2007-08-23 Hydro-Gerätebau GmbH & Co. KG Hebezeuge Système de levage
CN105152067A (zh) * 2015-08-25 2015-12-16 中国航空工业集团公司西安飞机设计研究所 一种飞机主千斤顶调节装置

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DD79130A (fr) *
US2802635A (en) * 1954-12-06 1957-08-13 Northrop Aircraft Inc Flex jack
US3191706A (en) * 1960-09-06 1965-06-29 Douglas Aircraft Co Inc Pneumatic support
DE3044425C2 (de) * 1980-11-26 1982-11-25 Hydro Gerätebau GmbH & Co KG Hebezeuge, 7616 Biberach Heckstütze für Flugzeuge
DE4215644C2 (de) * 1992-05-14 1995-03-16 Greschbach Ind Gmbh & Co Vorrichtung zum Hochbocken von Flugzeugen
DE102006012994A1 (de) * 2006-03-22 2007-09-27 Hydro-Gerätebau GmbH & Co. KG Hebezeuge Stütze zum Unterstützen von Lasten
US9114964B2 (en) * 2012-05-11 2015-08-25 Tronair, Inc. Dual-speed hand pump aircraft jack

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB926254A (en) * 1960-09-06 1963-05-15 Douglas Aircraft Co Inc Air glided load support
EP0287044A1 (fr) * 1987-04-16 1988-10-19 Hydro-Gerätebau GmbH & Co. KG Hebezeuge Installation pour soulever des avions
WO2007093212A1 (fr) * 2006-02-16 2007-08-23 Hydro-Gerätebau GmbH & Co. KG Hebezeuge Système de levage
CN105152067A (zh) * 2015-08-25 2015-12-16 中国航空工业集团公司西安飞机设计研究所 一种飞机主千斤顶调节装置

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109319165A (zh) * 2018-11-05 2019-02-12 西安飞机工业（集团）有限责任公司 一种飞机框保型定位架和定位方法
CN112550754A (zh) * 2020-12-24 2021-03-26 芜湖中科飞机制造有限公司 一种小型飞机装配用的尾部托坠平衡装置
CN112550754B (zh) * 2020-12-24 2022-06-07 芜湖中科飞机制造有限公司 一种小型飞机装配用的尾部托坠平衡装置
CN113581488A (zh) * 2021-07-30 2021-11-02 江西昌河航空工业有限公司 一种直升机主桨毂安装工装及使用方法
CN113581488B (zh) * 2021-07-30 2023-05-30 江西昌河航空工业有限公司 一种直升机主桨毂安装工装及使用方法

Also Published As

Publication number Publication date
DE102017206771A1 (de) 2018-10-25

Similar Documents

Publication Publication Date Title
DE69000289T2 (de) Kran mit anhebbarem ausleger und mit einer ausleger-rueckstossvorrichtung.
DE19901496C1 (de) Klemmgreifer für von oben zu greifende Lasten
WO2018192692A1 (fr) Appareil de levage et procédé permettant de soulever un aéronef
DE2261430C3 (de) Vorrichtung zum Kippen eines Kraftfahrzeugs und Verfahren zu ihrem Betrieb
EP3068264A1 (fr) Frein de sécurité pour colonne de meuble télescopique
DE102009053665A1 (de) Anhängevorrichtung
DE2549542C3 (de) Feststelleinrichtung für Einsäulen-Zeichentische
DE2847695A1 (de) Vorrichtung zum geraderichten von beschaedigten fahrzeugkoerpern
EP3031991B1 (fr) Dispositif d'appui
DE2132021A1 (de) Vorrichtung,vorzugsweise Richtvorrichtung zum Ausfuehren der Operationen fuer das Ausbessern und Zurueckverformen bzw.Zurueckfuehren auf die urspruengliche Form von z.B.verbeulten oder beschaedigten Blechen von Karosserien,insbesondere von Kraftfahrzeugen
DE19945189A1 (de) Hebezeug
DE4314670A1 (de) Kalander
DE69001231T2 (de) Vorrichtung und verfahren zum aufheben und bewegen von objekten.
EP3608488B1 (fr) Agencement et procédé de positionnement de conteneurs
DE19737754C2 (de) Lastaufnahmemittel
DE3020562A1 (de) Vorrichtung zum manuellen bewegen von lasten
WO2017190875A1 (fr) Appareil de levage pour un aéronef
DE3611593A1 (de) Verfahren zum selbsttaetigen anhaengen und ablegen eines ausleger-gegengewichtes von hydraulik-fahrzeugkranen und einrichtung zum durchfuehren des verfahrens
DE1959981C3 (de) Arbeitsbühne
DE1431892B1 (de) Im gleichgewicht bleibende trag und einstellvorrichtung
DE943320C (de) Greifer fuer Platten und Blechpakete
DE2539754B2 (de) Gerät mit Vierpunkt-Abstützung eines schweren Körpers auf einem anderen Körper
EP1316448A2 (fr) Système de support réglable en hauteur et méthode d'ajustement en hauteur d'un véhicule en utilisant le système du support
DE69717037T2 (de) Winde mit Arbeitszylinder
DE3029998A1 (de) Abstuetzvorrichtung fuer mobile krane, bagger o.ae. arbeitsgeraete

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18704156

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 18704156

Country of ref document: EP

Kind code of ref document: A1