EP1334947B1 - Selbstnivellierende Hubvorrichtung - Google Patents

Selbstnivellierende Hubvorrichtung Download PDF

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Publication number
EP1334947B1
EP1334947B1 EP02425657A EP02425657A EP1334947B1 EP 1334947 B1 EP1334947 B1 EP 1334947B1 EP 02425657 A EP02425657 A EP 02425657A EP 02425657 A EP02425657 A EP 02425657A EP 1334947 B1 EP1334947 B1 EP 1334947B1
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EP
European Patent Office
Prior art keywords
lifting
levelling
self
cell
leveling
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.)
Expired - Lifetime
Application number
EP02425657A
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English (en)
French (fr)
Other versions
EP1334947A2 (de
EP1334947A3 (de
Inventor
Roberto Maggiori
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Individual
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Individual
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Publication of EP1334947A2 publication Critical patent/EP1334947A2/de
Publication of EP1334947A3 publication Critical patent/EP1334947A3/de
Application granted granted Critical
Publication of EP1334947B1 publication Critical patent/EP1334947B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

Definitions

  • This lifting device is used for lifting and lowering operations, for levelling purpose, for self-levelling and weighing of: aircrafts, such as aeroplanes, helicopters, civil and military aircrafts, watercraft, camping vehicles and similar, cars and trains, bridges, radar, and any other structure and/or object to which it can be applied.
  • aircrafts such as aeroplanes, helicopters, civil and military aircrafts, watercraft, camping vehicles and similar
  • cars and trains such as bridges, radar, and any other structure and/or object to which it can be applied.
  • the procedure of lifting is made in the following way: are used for operation of weighing, balancing, maintenance and levelling, hydraulic jacks or self assisted for lifting, activated by manual methods.
  • This manual operation is obtained by a minimum of five operators which proceed to this lifting operation with much time of actuation: moreover, could be possible a structural yielding of the hydraulic jack during the operation of lifting and this may be cause of damages to persons and things.
  • a lifting group of electro-mechanical "nut-screw" type is disclosed in EP 0 538 208, in the name of Maggiori Enzo.
  • Italian patent N° 1.286.320 in the name of Maggiori Enzo discloses a self-levelling integrated listing device for aircrafts and vehicles. Said device comprises three or more lifting groups of electro-mechanical type, a central general control with a control panel, an automatic weighing system and a levelling cell.
  • This Self-Levelling Integrated Lifting device brings the following improvements: It is composed by three or more lifting groups (Fig. 01 and Fig. 10) that are all manufactured with "nut-screw" system (Fig. 01, part. 1) : this lifting group works everyone autonomous or in synchronous speed to have a self-levelling operation to reference to a levelling cell (Fig. 05).
  • the agglomerate of this Self Levelling Integrated Lifting device in order to avoid that one of the jacks for effect of instability to the ground doesn't guarantee one perfect adherence, (as an example during the operations of lifting may happens a separation from the linking points scheduled on the aircrafts and helicopters, etc..), it assure the raising and therefore it allows a perfect weighing and levelling to balance the weight; it is completely automatic only when the linking points scheduled by the aircraft are perfectly adherent to the ground and its linking points;
  • the benefits of this innovation are: fully electronic management and at distance, only with an operator who with this device operate by few time for the lifting and lowering; to allow the lifting in emergency situations in which is indispensable in few time to supply the apparatus and balance the weight upon the aircraft before the takeoff; reduced maintenance and easy use owned to the considerable mobility of the lifting groups; high safety owned by the use of "nut-screw" penetrable, self-blocking, which at the end of the lifting operation, it avoid possible instabilities of the attitude obtained upon the aircraft, besides accidental lowering
  • an absolutely new feature is represented by the fact that lifting and, therefore, lowering can be obtained in synchronism, with a special floating head for centring operation in case of application to large-dimension aircraft.
  • Another feature is the display of partial and total weights and levelling measurement, this latter being possibly obtained acoustically as well.
  • Self-levelling is also useful to operate on mobile surfaces, such as floating platforms, aircraft carriers, etc. In the specific case of various camping vehicles, perfect internal attitude is required for electrical appliances (refrigerators, etc.) and for people inside, independent of the ground the vehicle rests on.
  • the benefits of the Self-levelling Integrated Lifting device include shorter time for automatic application, with the above-reported characteristics but different capability of resistance to loads in lifting and lowering, in addition to synchronous, automatic lifting of one or more lifting groups, which avoids possible damage to the structure or users.
  • the Self-levelling Integrated Lifting device also allows reducing time losses and overworking for operation and is perfectly safe for the stability of the lifters used by an operator alone.
  • the lifting device is made of three or more groups of ELECTRO-MECHANICAL LIFTERS (Fig. 01 and 04), a CENTRAL GENERAL CONTROL (Fig. 12), and a LEVELING CELL (Fig. 05).
  • Each ELECTROMECHANICAL LIFTER (Fig. 01) is constituted by the following elements: a load-bearing base and some supports (Fig. 01, particular (6)) equipped with moving wheels (Fig. 01, particular 4), each including the following parts: a jack with "nut-screw system", i.e. bronze-threaded, penetrating, telescopic screws and bushings with one or more sectors (Fig. 1, particular (1)), two accumulators (Fig. 01, particular (9)), a battery charger (Fig.
  • Every lifting group is self-functioning, being integrated with an electronic card apparatus (Fig. 01, particular (10)) that can be operated at various degrees of speed or in multiple, for control function in synchronism of every lifting group, with automatic weight control that follows lifting by controlled push of the load.
  • This synchronous control function allows performing lifting and lowering operations.
  • the lifting system is also provided with an automatic sensor to avoid possible structural damage of the aircraft, also aimed at overcoming difficulties in transport of the lifting system itself.
  • This self-adhesion automatic sensor is necessary for multiple control during the synchronous function, and provides perfect lifting and weighing just as all points expected to link to the vehicle are presently and perfectly attached with the liking points, so that any detachment is avoided.
  • the lifting group is equipped with a tripod base, with the specific shape and structure as shown in Fig.
  • the self-centring floating head (Fig. 11) for the specific lifting device at the rear of the aircraft functions as an automatic control (self-controlled version) of the rear shift, by never exceeding the safety load limits given in the aircraft specifications after proper calibration.
  • the following actions take place: two main lifting devices together with the rear lifting group (Fig. 10) start the aircraft detachment from ground.
  • This rear lifting group possesses an automatic weighing system that follows lifting with a controlled-load push. If the load is exceeding or insufficient for aircraft attitude, as provided for in the aircraft specifications, a load cell - suitably calibrated according to load requirements - stops automatically the whole lifting system by displaying the excess or defect load (safety threshold). After recovering regular attitude, the operation may bee repeated.
  • the CENTRAL GENERAL CONTROL (Fig. 12) is composed of a remote control for self-levelling and manual operations (Fig. 12) plus a system with electrical command card for self-levelling, linked with the lifting groups (Fig. 12) by means of wires or radio control.
  • the central general control (Fig. 12) is aimed at receiving and processing signals coming from the levelling cell (Fig. 05) through wires linked with the IN-connector of the level (Fig. 12). As soon as received, the signals are coordinated by the electrical command card.
  • a series of accumulators (Fig. 01, part. 9) placed within the lifting group, this card supplies the energy necessary for the lifters to start and drives them to their self-levelling operation, either in synchronism or singularly.
  • the whole apparatus is enclosed in a portable metal case that allows the user to control and operate the different lifting groups by means of a keyboard (Fig. 12).
  • the LEVELING CELL (Fig. 05) is an integrated, compact, airtight device with fluid-controlled oscillation that represents constant reference for the whole system, placed within the aircraft by means of a telescopic sustaining pole (Fig. 07), directly linked with the central general control (Fig. 12) or with the electronic command apparatus (Fig. 01, part. 10) through electric multipolar wire. It is made of the following components: a mechanical pendulum (Fig. 05, sect. C, part. 25C) placed on a suitable, highly sensitive, wedge pin (Fig. 05, sect. B, part. 25) enclosed in an airtight methacrylate cell (Fig. 5, sect. B, part. 2), submerged in antifreeze fluid for antishock effect.
  • a mechanical pendulum (Fig. 05, sect. C, part. 25C) placed on a suitable, highly sensitive, wedge pin (Fig. 05, sect. B, part. 25) enclosed in an airtight methacrylate cell (Fig. 5, sect. B,
  • the levelling cell is enclosed in a suitable container (Fig. 06) together with the following components: external reading sensors (Fig. 05, sect. B, part. 45 - description of mortise positioning of the sensor inside the container Fig. 06), with infrared, photoelectric, or similar power of interception of the mechanical pendulum shifts (Fig. 05), LED for sensor interception and sensitivity regulators for levelling calibration.
  • the levelling cell is equipped with supports appropriate for every kind of means to be lifted and self-levelled.
  • Fig. 07 shows a sustaining telescopic pole with a spherical sector that operates in reference to the levelling cell (Fig. 05) whose container (Fig.
  • goniometric support is part of the Self-levelling Integrated Lifting device and acts by means of an electronic control device for triangulation, which makes easier the shifting of the longitudinal axis for targeting purposes or aircraft attitude simulation. This goniometric support (Figs.
  • the levelling cell (Fig. 05) is placed inside the aircraft by means of its support telescopic pole (Fig. 07) and connected through multipolar electric wire to either the electronic command apparatus including an electronic card (Fig. 01, part. 10) placed inside each lifting group (Fig. 01) for autonomous function, or the IN-connector of the level in the central general control (Fig. 12, part. 22) also provided with electric command card for function in synchronism of the various lifting groups.
  • Every shift of the mechanical pendulum in the level cell is translated by the external reading sensors into electrical impulses, which in turn are sent to the electronic command system or central general control (Fig. 01, part. 10) through wires and therefore translated into shifts by the electronic card for signal control that interprets them as lifting and/or lowering and moves the lifters.

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  • Life Sciences & Earth Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Geology (AREA)
  • Mechanical Engineering (AREA)
  • Structural Engineering (AREA)
  • Handcart (AREA)
  • Soil Working Implements (AREA)
  • Vehicle Body Suspensions (AREA)
  • Motorcycle And Bicycle Frame (AREA)
  • Vehicle Cleaning, Maintenance, Repair, Refitting, And Outriggers (AREA)
  • Road Paving Machines (AREA)
  • Devices For Checking Fares Or Tickets At Control Points (AREA)
  • Road Repair (AREA)
  • Wind Motors (AREA)
  • Mechanical Treatment Of Semiconductor (AREA)

Claims (11)

  1. Selbstnivellierende integrierte Hubvorrichtung, umfassend:
    a) mindestens drei Hubgruppen der elektromechanischen "Schraube-Mutter"-Art (Figur 01, Figur 10);
    b) eine zentrale, allgemeine Steuerung (Figur 12);
    c) eine Nivellierzelle (Figur 05);
    d) eine Untersetzungseinheit (2 - Figur 1);
    e) einen Motor (3 - Figur 1);
    f) ein automatisches Wiegesystem; und
    g) eine Steuertafel (Figur 12); wobei
    jede der Hubgruppen mit einem selbst-zentrierenden, fliegenden Magnetkopf (Figur 11) versehen ist.
  2. Vorrichtung nach Anspruch 1, umfassend mindestens vier der Gruppen a), wobei jede Gruppe einen Adhäsions-Sensor zur automatischen Steuerung der Gruppe hinsichtlich der Funktion des selbstnivellierenden Mechanismus in Bezug auf die Nivellierzelle c) aufweist.
  3. Vorrichtung nach einem der Ansprüche 1 oder 2, weiter mindestens eine der folgenden Komponenten umfassend: zwei Akkumulatoren, ein Ladegerät, eine elektronische Steuerung für den Motor e).
  4. Vorrichtung nach einem der Ansprüche 1, 2 oder 3, wobei die Hubgruppen jeweils autonom arbeiten.
  5. Vorrichtung nach Anspruch 2, wobei die Hubgruppen mit synchroner Geschwindigkeit in Bezug auf eine Nivellierzelle arbeiten.
  6. Vorrichtung nach Anspruch 1, wobei eine Anzeige von Teil- und Gesamtgewichten und/oder einer Nivellierungsmessung vorgesehen sind.
  7. Vorrichtung nach einem der Ansprüche 1 bis 6, weiter eine Anzeige einer Nivellierungsmessung umfassend.
  8. Vorrichtung nach Anspruch 7, wobei die Anzeige der Nivellierungsmessung akustisch ist.
  9. Verwendung der Vorrichtung nach einem der Ansprüche 1 bis 8 für Hebe- und Absenkvorgänge.
  10. Verwendung nach Anspruch 9, bei der die Vorgänge aus der Gruppe ausgewählt werden, die Nivellieren, Selbstnivellieren, Wartung und Wiegen umfasst.
  11. Verwendung nach Anspruch 9 oder 10, bei der der Vorgang an einem Gegenstand durchgeführt wird, der aus der Gruppe ausgewählt wird, die Fluggeräte wie Flugzeuge, Hubschrauber, zivile und militärische Flugzeuge, Wasserfahrzeuge, Camping-Fahrzeuge und ähnliches, Kraftfahrzeuge und Züge, Brücken und Radars umfasst.
EP02425657A 2001-11-02 2002-10-30 Selbstnivellierende Hubvorrichtung Expired - Lifetime EP1334947B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
ITRM20010646 2001-11-02
IT2001RM000646A ITRM20010646A1 (it) 2001-11-02 2001-11-02 Dispositivo di sollevamento integrato auto livellante.
CA2427405A CA2427405C (en) 2001-11-02 2003-05-01 Leveling instrument, an electromechanical lifter and a self leveling integrated lifting system using both of them

Publications (3)

Publication Number Publication Date
EP1334947A2 EP1334947A2 (de) 2003-08-13
EP1334947A3 EP1334947A3 (de) 2004-11-24
EP1334947B1 true EP1334947B1 (de) 2006-09-27

Family

ID=34064004

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02425657A Expired - Lifetime EP1334947B1 (de) 2001-11-02 2002-10-30 Selbstnivellierende Hubvorrichtung

Country Status (8)

Country Link
EP (1) EP1334947B1 (de)
AT (1) ATE340759T1 (de)
CA (1) CA2427405C (de)
CY (1) CY1106277T1 (de)
DE (2) DE60214966T4 (de)
DK (1) DK1334947T3 (de)
ES (1) ES2273990T3 (de)
IT (1) ITRM20010646A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103874650B (zh) * 2011-08-29 2016-10-12 托马斯·塞弗林 用于飞机的提升设备

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10361807A1 (de) * 2003-12-30 2005-07-28 Herbert Kallenberger Hubsystem zum Anheben und Absenken und/oder Verschieben grosser Lasten
ITRM20060180A1 (it) 2006-03-31 2007-10-01 Cristian Isopo Dispositivo di sollevamento elettromeccanico
CN102880100B (zh) * 2012-10-26 2014-08-20 黑龙江大学 秋千式电控摆
CN106395702B (zh) * 2016-10-13 2018-07-27 上海理工大学 一种自重平衡器
CN109443641A (zh) * 2018-12-29 2019-03-08 中航电测仪器股份有限公司 一种快速调校飞机水平的系统及方法
DE202019101761U1 (de) * 2019-03-28 2019-04-29 Udo Idler Rotationsschwerlastfahrwerk

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0538208A1 (de) * 1991-10-18 1993-04-21 Enzo Maggiori Elektrischer teleskopischer Hebebock
IT1286320B1 (it) * 1996-09-19 1998-07-08 Roberto Maggiori Sistema di sollevamento autolivellante per aeromobili e veicoli

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2491048A1 (fr) * 1980-09-30 1982-04-02 Sovam Installation de levage d'une charge de grande dimension a l'aide de plusieurs dispositifs de levage independants agissant en plusieurs points de charge, notamment destinee au levage d'un avion en vue de sa reparation
DE3537640A1 (de) * 1985-10-23 1987-04-23 Zippo Gmbh Hebeanlage fuer flugzeuge
DE3713007A1 (de) * 1987-04-16 1988-10-27 Hydro Geraetebau Gmbh & Co Kg Einrichtung zum hochbocken von flugzeugen
JPH03200457A (ja) * 1989-12-28 1991-09-02 Mitsubishi Heavy Ind Ltd 航空機の自動昇降装置
DE4131326C2 (de) * 1991-09-20 1994-03-24 Hydro Geraetebau Gmbh & Co Kg Heber, insbesondere Dreibockheber für Flugzeuge

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0538208A1 (de) * 1991-10-18 1993-04-21 Enzo Maggiori Elektrischer teleskopischer Hebebock
IT1286320B1 (it) * 1996-09-19 1998-07-08 Roberto Maggiori Sistema di sollevamento autolivellante per aeromobili e veicoli

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103874650B (zh) * 2011-08-29 2016-10-12 托马斯·塞弗林 用于飞机的提升设备

Also Published As

Publication number Publication date
DE60214966T4 (de) 2010-02-18
ES2273990T3 (es) 2007-05-16
EP1334947A2 (de) 2003-08-13
DK1334947T3 (da) 2007-02-05
CY1106277T1 (el) 2011-10-12
CA2427405A1 (en) 2004-11-01
ITRM20010646A0 (it) 2001-11-02
CA2427405C (en) 2013-12-10
ITRM20010646A1 (it) 2003-05-02
ATE340759T1 (de) 2006-10-15
EP1334947A3 (de) 2004-11-24
DE60214966D1 (de) 2006-11-09
DE60214966T2 (de) 2007-03-29

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