EP1334947A2 - Selbstnivellierende Hubvorrichtung - Google Patents

Selbstnivellierende Hubvorrichtung Download PDF

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Publication number
EP1334947A2
EP1334947A2 EP02425657A EP02425657A EP1334947A2 EP 1334947 A2 EP1334947 A2 EP 1334947A2 EP 02425657 A EP02425657 A EP 02425657A EP 02425657 A EP02425657 A EP 02425657A EP 1334947 A2 EP1334947 A2 EP 1334947A2
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EP
European Patent Office
Prior art keywords
lifting
leveling
self
cell
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.)
Granted
Application number
EP02425657A
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English (en)
French (fr)
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EP1334947B1 (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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    • 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 leveling purpose, for self-leveling 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 leveling, 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.
  • This Self-Leveling Integrated Lifting device brings the following improvements:
  • this lifting group works everyone autonomous or in synchronous speed to have a self-leveling operation to reference to a leveling cell (Fig. 05).
  • This Self Leveling 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 leveling 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 attitutude obtained upon the aircraft, besides accidental lowering
  • an absolutely new feature is representated 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 leveling measurement, this latter being possibly obtained acoustically as well.
  • Self-leveling 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-leveling 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-leveling Integrated Lifting device also allows to reduce time losses and overwork 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 to perform 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 perfecly 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 aflter 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.
  • These lifting and lowering operations can be performed by a single operation outside the aircraft, who uses a palmar remote control in perfect safety, rapidly and with little energy, thanks to the easy handling of the device (Fig. 10, particulars 6 and 4).
  • the CENTRAL GENERAL CONTROL (Fig. 12) is composed of a remote control for self-leveling and manual operations (Fig. 12, particular 4) plus a system with electrical command card for self-leveling, linked with the lifting groups (Fig. 12, particular 1) by means of wires or radio control.
  • the central general control (Fig. 12) is aimed at receiving and processing signals coming from the leveling cell (Fig. 05) through wires linked with the IN-connector of the level (Fig. 12, part. 2). As soon as received, the signals are co-ordinated by the electrical command card.
  • a series of accumulators (Fig. 01, part.
  • this card supplies the energy necessary for the lifters to start and drives them to their self-leveling 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. 2) placed on a suitable, highly sensitive, wedge pin (Fig. 05, sect. B, part. 1) enclosed in an airtight methacrylate cell (Fig. 5, sect. B, part. 2), submerged in antifreeze fluid for antishock effect.
  • the leveling cell is enclosed in a suitable container (Fig. 06) together with the following components: external reading sensors (Fig. 05, sect. B, part. 4 - 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 leveling calibration.
  • the leveling 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 leveling cell (Fig. 05) whose container (Fig.
  • goniometric support (Figs. 08 and 09) is part of the Self-leveling 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.
  • a knob (Fig. 08, part. 05; Fig. 09, part. 1) placed at the basis of the graduated goniometre to perform manual simulation maneuvers.
  • the leveling 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. 2) 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.
  • Figure 01 shows a top-view design of the whole lifting group apparatus without its upper cover. It includes 11 particulars: 1) lifting jack sectors; 2) reduction units; 3) motor; 4) wheels; 5) run-out switch; 6) bearing base and supports; 7) battery-charger; 8) adhesion sensor; 9) accumulators; 10) electronic command system; 11) steering rod.
  • Figure 02 shows the front-view design of a lifting group with upper cover, including the keyboard , movement wheel and stering rod. It includes 11 particulars; 1) voltage LED; 2) manual/automatic switch; 3) signal entry; 4) up/down knob; 5) ON/OFF key; 6) lifting jack head; 7) battery disconnecter; 8) battery indicator; 9) steering rod; 10) movement wheel; 11) wheels.
  • Figure 03 shows te rear-view design of a lifting group with upper cover including support bases, plus lateral view with upper cover. It includes 5 particulars: 1) lifting jack head; 2) cover; 3) supports; 4) wheels; 5) steeing rod and movement wheel.
  • Figure 04 shows the top-view of a lifting group with its upper cover. It includes 6 particulars: 1) guidance knob and movement wheel ; 2) keyboard; 3) cover; 4) lifting jack head; 5) wheels; 6) supports.
  • Figure 04-1(a shows the lifting group assembly.
  • Figure 05 shows the level cell. It includes: Section A : 1) cover. Section B : 1) wedge pin; 2) antishock case of the methacrylate cell; 3) projection of the cell antishock case; 4) sensors. Section C : 1) wedge pin slot (sect. B, part. 1); 2) mechanical pendulum; 3) projection of the swaying bell.
  • Figure 06 shows the leveling cell container. It includes 3 particulars, i.e. LED, signal entry, tightening.
  • Figure 07 shows the support telescopic pole. It includes 3 particulars: 1) plumb.line reference thrust rod; 2) approach knob; 3) lifting/lowering regulation cursor.
  • Figure 08 shows model "A" of the goniometric shift system. It includes 5 particulars: 1) clutch of the leveling cell container; 2) threaded internal screw; 3) reference push rod; 4) positioning push rods; 5) regulation knob.
  • Figure 09 shows model "B" of the goniometric shift system. It includes 3 particulars: 1) regulation knob; 2) clutch of the leveling cell container; 3) reference index of degree shifting.
  • Figure 10 shows the lifting group with tripod base for large-dimension aircraft. It includes 6 particulars: 1) anti-vibrant supports of the tripod base; 2) fifth wheels with balls; 3) self-adhesion automatic sensor; 4) wheels ; 5) lifter housing; 6) motor sterring rod.
  • Figure 11 shows self-centring floating head. It includes 5 particulars: 1) aircraft link point; 2) pin and springs for centring; 3) fifth-wheel with balls; 4) sensors; 5) centring reference pin.
  • Figure 12 shows the central general control front panel, including 4 particulars: 1) IN-connector for signals from lifters; 2) IN-connector of the level; 3) IN-connector of palmar control; 4) manual control.

Landscapes

  • 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 Repair (AREA)
  • Mechanical Treatment Of Semiconductor (AREA)
  • Devices For Checking Fares Or Tickets At Control Points (AREA)
  • Wind Motors (AREA)
  • Road Paving Machines (AREA)
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 true EP1334947A2 (de) 2003-08-13
EP1334947A3 EP1334947A3 (de) 2004-11-24
EP1334947B1 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 (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005066062A1 (de) * 2003-12-30 2005-07-21 Herbert Kallenberger Hubsystem zum anheben und absenken und/oder verschieben grosser lasten
WO2007113891A2 (en) 2006-03-31 2007-10-11 Sandro Venturini Electro-mechanical lifting device
CN102880100A (zh) * 2012-10-26 2013-01-16 黑龙江大学 秋千式电控摆
WO2013029591A1 (de) * 2011-08-29 2013-03-07 Thomas Sefrin Hebevorrichtung für ein flugzeug
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
EP3718950A1 (de) * 2019-03-28 2020-10-07 Udo Idler Rotationsschwerlastfahrwerk

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106395702B (zh) * 2016-10-13 2018-07-27 上海理工大学 一种自重平衡器

Citations (7)

* 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
EP0287044A1 (de) * 1987-04-16 1988-10-19 Hydro-Gerätebau GmbH & Co. KG Hebezeuge 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
EP0532970A1 (de) * 1991-09-20 1993-03-24 Hydro-Gerätebau GmbH & Co. KG Hebezeuge Heber, insbesondere Dreibockheber für Flugzeuge
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

Patent Citations (7)

* 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
EP0287044A1 (de) * 1987-04-16 1988-10-19 Hydro-Gerätebau GmbH & Co. KG Hebezeuge 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
EP0532970A1 (de) * 1991-09-20 1993-03-24 Hydro-Gerätebau GmbH & Co. KG Hebezeuge Heber, insbesondere Dreibockheber für Flugzeuge
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 0154, no. 68 (M-1184), 27 November 1991 (1991-11-27) & JP 3 200457 A (MITSUBISHI HEAVY IND LTD), 2 September 1991 (1991-09-02) *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005066062A1 (de) * 2003-12-30 2005-07-21 Herbert Kallenberger Hubsystem zum anheben und absenken und/oder verschieben grosser lasten
WO2007113891A2 (en) 2006-03-31 2007-10-11 Sandro Venturini Electro-mechanical lifting device
WO2007113891A3 (en) * 2006-03-31 2008-03-20 Sandro Venturini Electro-mechanical lifting device
US8567762B2 (en) 2006-03-31 2013-10-29 Sandro Venturini Electro-mechanical lifting device
WO2013029591A1 (de) * 2011-08-29 2013-03-07 Thomas Sefrin Hebevorrichtung für ein flugzeug
CN103874650A (zh) * 2011-08-29 2014-06-18 托马斯·塞弗林 用于飞机的提升设备
CN102880100A (zh) * 2012-10-26 2013-01-16 黑龙江大学 秋千式电控摆
CN102880100B (zh) * 2012-10-26 2014-08-20 黑龙江大学 秋千式电控摆
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
EP3718950A1 (de) * 2019-03-28 2020-10-07 Udo Idler Rotationsschwerlastfahrwerk

Also Published As

Publication number Publication date
EP1334947B1 (de) 2006-09-27
DE60214966D1 (de) 2006-11-09
CY1106277T1 (el) 2011-10-12
ATE340759T1 (de) 2006-10-15
CA2427405C (en) 2013-12-10
ITRM20010646A1 (it) 2003-05-02
DE60214966T2 (de) 2007-03-29
ITRM20010646A0 (it) 2001-11-02
EP1334947A3 (de) 2004-11-24
DK1334947T3 (da) 2007-02-05
DE60214966T4 (de) 2010-02-18
CA2427405A1 (en) 2004-11-01
ES2273990T3 (es) 2007-05-16

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