EP1984289A1 - Système de levage - Google Patents

Système de levage

Info

Publication number
EP1984289A1
EP1984289A1 EP06829806A EP06829806A EP1984289A1 EP 1984289 A1 EP1984289 A1 EP 1984289A1 EP 06829806 A EP06829806 A EP 06829806A EP 06829806 A EP06829806 A EP 06829806A EP 1984289 A1 EP1984289 A1 EP 1984289A1
Authority
EP
European Patent Office
Prior art keywords
lifting
docking head
lifting system
aircraft
load
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.)
Withdrawn
Application number
EP06829806A
Other languages
German (de)
English (en)
Inventor
Lothar Mikowski
Klaus Müller
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-Geratebau & Co KG Hebezeuge GmbH
Original Assignee
Hydro-Geratebau & Co KG Hebezeuge GmbH
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-Geratebau & Co KG Hebezeuge GmbH filed Critical Hydro-Geratebau & Co KG Hebezeuge GmbH
Publication of EP1984289A1 publication Critical patent/EP1984289A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • B66F3/46—Combinations of several jacks with means for interrelating lifting or lowering movements
    • 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
    • B66F7/00—Lifting frames, e.g. for lifting vehicles; Platform lifts
    • B66F7/10—Lifting frames, e.g. for lifting vehicles; Platform lifts with platforms supported directly by jacks
    • B66F7/16—Lifting frames, e.g. for lifting vehicles; Platform lifts with platforms supported directly by jacks by one or more hydraulic or pneumatic jacks
    • B66F7/20—Lifting frames, e.g. for lifting vehicles; Platform lifts with platforms supported directly by jacks by one or more hydraulic or pneumatic jacks by several jacks with means for maintaining the platforms horizontal during movement

Definitions

  • the invention relates to a lifting system for lifting loads, with a lifter that can be positioned below the load.
  • the load to be lifted may be an aircraft, in particular an accidental aircraft to be retrieved.
  • At take-off or landing crashed aircraft, for example, over the runway out rolled aircraft may have damage to the chassis, with one or more landing gear can be bent or demolished, so that the aircraft comes to rest with a wing at the bottom.
  • Object of the present invention is to provide a lifting system with a lift, can be raised and recovered with the fast and reliable loads and in particular accidental aircraft.
  • the lifter has at least three lifting elements and a docking head for coupling with a load pickup point, that a measuring system for detecting the position of the docking head and for measuring the load vector occurring at the docking head is provided and that one with the measuring system Connected control device for independent, load-controlled or path-controlled actuation of the individual Hubium drives is provided.
  • the combination of the lift with the measuring system for position detection and for load measurement on the docking head and the independently operable lifting elements allows automatic adjustment to the position of the load pick-up point or an aircraft of the aircraft pick-up point (Wing Jacking Point) when lifting.
  • the load or the aircraft is lifted side load.
  • the lift follows with its docking head the load pick-up point of the load (aircraft), because this docking head is freely horizontally and vertically positionable.
  • the curve of the pickup point when lifting the aircraft depends on the respective existing, spaced from the receiving point support points, so for example, the still intact trolleys or other support points of the aircraft on the ground.
  • the curve of the pickup point is not fixed but depends on the particular accident situation.
  • force sensors may be provided for load measurement at the docking head.
  • axial load sensors or pressure sensors are provided on the lifting elements for load measurement at the docking head.
  • loads in the coordinate directions X, Y, Z and thus transverse loads and bearing loads can be detected.
  • position control a position detection of the docking head is provided.
  • a cluster detection of the docking head is provided.
  • a cluster detection of the docking head is provided.
  • a telescoping center strut can be provided in addition to the three lifting elements.
  • a length measuring device and two angle measuring devices may be provided on the center strut for detecting the position of the docking head.
  • the center bar only serves to guide the docking head.
  • the inner cavity can therefore be used to accommodate the length measuring device and the angle measuring devices with the advantage that these measuring devices are well protected thereby protected against damage.
  • the lifting elements can be designed as hydraulic lifting cylinders or as electromechanical lifting cylinders.
  • the lifter is assigned a control unit as part of the lifting system, which comprises at least one hydraulic pump, control valves and a hydraulic tank, wherein the control unit is accommodated in particular in a carriage and a connection to the lifter is provided by means of supply and measuring and control lines.
  • the control unit is thus a separate unit which is easy to transport and can be connected to the lifter and the sensors mounted there via the supply and measuring and control lines, which are preferably provided with quick-release closures.
  • the hydraulic pump can be driven electrically via a generator or, as an alternative embodiment, can be an air-driven hydraulic pump driven by a compressor.
  • the embodiment with compressor and air hydraulic pump is advantageous if, for example, in an aircraft rescue additional devices are used with compressed air demand, which can then be supplied by the compressor with.
  • control device has an electronic control, in particular with microprocessor, proportional nalventilen and the like control means, which operates both last- and path-controlled.
  • Travel-controlled driving is provided for applying the lifter to the load-receiving point, while force-controlled driving is provided for tracking the pick-up point in X-Y motions.
  • FIG. 2 is a perspective view of a lifting system with a tripod lift and a control unit, which is connected via supply and test leads to the lifter,
  • FIG. 3 is a side view of a retracted tripod lift
  • FIG. 4 is a plan view of the tripod jack shown in FIG. 3; FIG.
  • Fig. 5 is a side view of an extended tripod lift
  • Fig. 6 is a plan view of the tripod lifter shown in Fig. 5.
  • a lifting system 1 shown in FIG. 2 is used in the exemplary embodiment for recovering aircraft 2 that have crashed, as is indicated schematically in FIG.
  • only two of the three landing gear legs 3 are extended in the aircraft 2, so that the aircraft rests on an engine nacelle 4 on the other side where the landing gear is retracted.
  • the lift 6 is part of the lifting system 1 shown in Fig. 2 which in the embodiment comprises a tripod lift 6 and a control unit 7.
  • the tripod lift 6 has three multiply telescopic lifting cylinders 8, which are arranged in the shape of a pyramid and engage at their upper end on a docking head 9 and are supported on the bottom side on a floor frame 10.
  • a telescoping center strut 11 is still provided which absorbs no axial forces and only has a guiding function for the docking head 9.
  • the floor frame 10 has three foot plates 12 for the lifting cylinder 8, a center pad 13 for the center strut 11 and struts 14, which connect the foot plate 12 and the center pad 13.
  • the struts 14 may be rigid or adjustable in length.
  • the root circle can be varied and thus the lateral stability of the jack 6.
  • an adaptation to the existing, local conditions is possible.
  • the height of the lift 6 can be changed, which is particularly in the retracted position may be advantageous.
  • the minimum height can be slightly reduced, so that then the lift fits in special cases under the object to be lifted.
  • the docking head 9 has an upper side, for example, spherical projection 15 which is attached to an aircraft receiving point 18 for lifting the aircraft 2.
  • the recovery system 1 has a measuring system for detecting the position of the docking head 9 and for measuring the load on the docking head, wherein the measuring system is connected to a control device of the control unit 7.
  • the individual lifting cylinders 8 can be controlled or controlled away from each other independently.
  • force sensors can be provided at the docking head or else it is also possible that axial force sensors for measuring the load on the docking head are respectively provided on the lifting cylinders 8.
  • the position detection of the docking head 9 can be realized via length measuring devices on the lifting cylinders 8. However, it is preferably provided that in the embodiment shown in the figures with a center strut 11 for detecting the position of the docking head 9, a length measuring device and two angle measuring devices are provided on the center strut 11. In Fig. 2, this arrangement of the length measuring device and the two angle measuring devices on the center strut by a measuring devices receiving housing 16 and leading from the housing 16 to the control unit 7 measuring leads 17 is symbolically indicated.
  • the receiving point 18 provided on the aircraft pivots about the attachment of the jack 6 about an axis which is arranged between the two ground support points of the extended chassis 3. running.
  • Figs. 3 and 5 the course of the curved lifting curve 19 is shown by double-dashed lines.
  • the docking head 9 follows the course of the lifting curve 19.
  • An electronic control takes over the load-controlled method of the lifting cylinder 8, so that adjusts the lift curve 19 shown in two-dimensionally in FIGS. 3 and 5.
  • the aircraft is thereby raised largely free of side loads, the tripod lift or its docking 9 follows the course of the aircraft receiving point 18.
  • the tripod lift 6 is operated in a force-controlled manner by a minimum height hi shown in FIGS. 3 and 4 up to a height h 2 .
  • this lifting height h 2 is smaller than the maximum lifting height h 3 .
  • the wings are in a horizontal position. If the landing gear is to be extended, a further increase of the aircraft altogether is required.
  • another tripod lift is attached to the other support surface 5a and the aircraft 2 is then raised in the vertical direction, for example up to the position h 3 .
  • the controller is switched to path-controlled control. This is necessary because the previously existing bearing points formed by the two intact landing gear legs 3 are no longer present or effective during further lifting.
  • vertical lifting occurring lateral forces for example by wind load, have no effect on the Control of the lifting cylinder 8 have.
  • the working area 25 of the tripod lift 6 is hatched in FIGS. 3 to 6.
  • FIGS. 3 and 5 it can be clearly seen that in the example shown the course of the lifting curve lies within this working area 25. Should the pick-up point 18 on the aircraft 2 emigrate during lifting from the area defined as the working area, which is the case, for example, when the lifting curve is more curved, it would be necessary in such special cases to support the aircraft in this intermediate position and the tripod lift 6 to position so that in this intermediate position a central positioning of the tripod jack 6 is given below the receiving point 18.
  • the lifting height hi of the jack 6 can be, for example, 220 centimeters, the lifting height h 2 520 centimeters and the maximum lifting height 620 centimeters.
  • the lifting cylinders 8 For a statically determined system by which transverse forces can be transmitted, different articulations can be provided on the lifting cylinders 8 on the foot side and on the head side.
  • the center strut 11 where in addition to the three lifting cylinders 8, the center strut 11 is provided, the three base points 20 of the lifting cylinder 8 and the base 21 of the center strut 11 are mounted in ball joints 24, while the connection between two of the upper Cylinder ends and the docking head via rod ends 22 and between the third of the top cylinder ends and the docking head via a pivot connection 23 with a flange and a transverse bolt.
  • the upper end of the center strut 11 is rigidly connected to the docking head 9.
  • a crash Backup can be provided, for example, with a manual or electrical safety nut.
  • the tripod lift 6 can be broken down into transport units with a defined maximum weight of, for example, 2000 kilograms each. This makes a simplified transport to the job site possible. For example, salvage carriages can be used in conventional embodiments for transport to the place of use of the complete lift or transport units of the dismounted lift.
  • the control unit 7 shown in FIG. 2 and offset from the tripod lift 6 may comprise at least one hydraulic pump, control valves, a hydraulic tank and the like equipment components.
  • the measuring lines 17 and also supply lines 26 can be rolled up on drums 27, these drums 27 are accommodated together with the control unit 7 on a carriage 28.
  • the lifting system 1 can also be used for simulating different positions of an aircraft jacked up on three jacks 6 according to the invention. Thus, not only a change in position about the transverse axis and the longitudinal axis of the aircraft, but also about its vertical axis can be made.

Landscapes

  • Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Geology (AREA)
  • Mechanical Engineering (AREA)
  • Structural Engineering (AREA)
  • Transportation (AREA)
  • Manufacturing & Machinery (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Forklifts And Lifting Vehicles (AREA)
  • Vehicle Cleaning, Maintenance, Repair, Refitting, And Outriggers (AREA)
  • Emergency Lowering Means (AREA)

Abstract

L'invention concerne un système (1) de levage servant au levage de charges, par exemple pour le levage et le sauvetage d'un aéronef (2) accidenté, et présente un dispositif (6) de levage qui peut être positionné sous une charge, notamment sous une surface (5) porteuse d'un aéronef. Le dispositif (6) de levage présente au moins trois vérins (8) de levage ou éléments de levage équivalents et une tête (9) d'amarrage destinée à venir s'accoupler avec un point de suspension de charge. Un système de mesure est prévu pour détecter la position de la tête (9) d'amarrage et pour mesurer le vecteur de charge produit au niveau de la tête (9) d'amarrage. Un dispositif de commande est connecté au système de mesure en vue d'un actionnement par commande de charge ou par commande de course des mécanismes d'entraînement de chacun des vérins de levage indépendamment les uns des autres.
EP06829806A 2006-02-16 2006-12-21 Système de levage Withdrawn EP1984289A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006007504A DE102006007504A1 (de) 2006-02-16 2006-02-16 Hebesystem
PCT/EP2006/012371 WO2007093212A1 (fr) 2006-02-16 2006-12-21 Système de levage

Publications (1)

Publication Number Publication Date
EP1984289A1 true EP1984289A1 (fr) 2008-10-29

Family

ID=37882278

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06829806A Withdrawn EP1984289A1 (fr) 2006-02-16 2006-12-21 Système de levage

Country Status (10)

Country Link
US (1) US20090234504A1 (fr)
EP (1) EP1984289A1 (fr)
JP (1) JP2009526722A (fr)
CN (1) CN101309851A (fr)
AU (1) AU2006338052A1 (fr)
BR (1) BRPI0621337A2 (fr)
CA (1) CA2624836A1 (fr)
DE (1) DE102006007504A1 (fr)
RU (1) RU2008113808A (fr)
WO (1) WO2007093212A1 (fr)

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NO20055021A (no) * 2005-10-27 2006-12-18 Iws As Fremgangsmåte og system for veiing
DE102007049673A1 (de) * 2007-10-04 2009-04-09 Lufthansa Leos Gmbh Verfahren zum Bergen von Flugzeugen und Flugzeugbergeheber
CN101708357B (zh) * 2009-11-19 2013-03-27 天津理工大学 应用于地震救援的起重或支撑器
CN102431930B (zh) * 2011-08-24 2013-07-10 淮阴工学院 一种用于救援的气囊装置
DE102011118758B4 (de) * 2011-08-29 2013-08-29 Thomas Sefrin Hebevorrichtung für ein Flugzeug
CN102701076B (zh) * 2012-06-18 2014-05-14 中国矿业大学 六自由度起重吊装协作柔索并联构型装备控制装置及方法
DE102013002964B4 (de) 2013-02-22 2020-06-25 Thomas Sefrin Hebevorrichtung für ein Flugzeug
CN103350972B (zh) * 2013-07-10 2015-11-18 中安（天津）航空设备有限公司 航空器救援程控三角顶升机
US9617806B2 (en) 2014-05-16 2017-04-11 Gordon FEY Downhole tool support stand, combinations, and methods
CN104001279B (zh) * 2014-06-18 2016-08-17 鞍山拜尔自控有限公司 液压接力顶升式高楼消防桥
FR3022528B1 (fr) * 2014-06-23 2018-01-26 Airbus Operations Systeme de suivi a la manutention d'un moteur d'aeronef
FR3042481B1 (fr) * 2015-10-16 2020-06-26 Airbus (S.A.S.) Outil de manutention
CN105236292A (zh) * 2015-11-17 2016-01-13 沈阳飞研航空设备有限公司 飞机千斤顶装置
DE102017206771A1 (de) * 2017-04-21 2018-10-25 Hydro Systems Kg Hebegerät und Verfahren zum Anheben eines Flugzeugs
CN110422784A (zh) * 2019-07-16 2019-11-08 广州供电局有限公司 起重装置
US20220228904A1 (en) * 2021-01-15 2022-07-21 Gulfstream Aerospace Corporation Aircraft lifting devices with coupling adapters between jacks and load cells
CN112874721A (zh) * 2021-04-02 2021-06-01 中国海洋大学 一种应用于浮托安装的甲板支撑组合装置

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Also Published As

Publication number Publication date
DE102006007504A1 (de) 2007-08-30
RU2008113808A (ru) 2009-12-10
AU2006338052A1 (en) 2007-08-23
US20090234504A1 (en) 2009-09-17
JP2009526722A (ja) 2009-07-23
CA2624836A1 (fr) 2007-08-23
BRPI0621337A2 (pt) 2011-12-06
WO2007093212A1 (fr) 2007-08-23
CN101309851A (zh) 2008-11-19

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