• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a device for placing / removing an aircraft engine (20) in the form of a trolley (100) comprising, on the one hand, a chassis (110) mounted on idle wheels (111). , 112, 113, 114) and on the other hand, a cradle (150) for receiving said motor (20), said device being characterized in that it comprises pneumatic and / or hydraulic actuators (160) arranged in interface between the frame (110) and the cradle (150) and able on the one hand to allow lifting of the cradle relative to the frame and on the other hand, to dampen shocks and / or vibrations, said actuators to lift the cradle in a first lifting position necessary for the installation / removal of the engine, then to maintain it in a second rest position under load to damp vibrations and / or shocks to the entire cradle-motor relative to the chassis.
    公开号:FR3058406A1
    申请号:FR1660908
    申请日:2016-11-10
    公开日:2018-05-11
    发明作者:Thomas LAMADON
    申请人:Next Aero Concept；
    IPC主号:
    专利说明:

    © Publication no .: 3,058,406 (use only for reproduction orders)
    ©) National registration number: 16 60908 ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY
    COURBEVOIE © Int Cl 8 : B 66 F 7/16 (2017.01), B 64 F 5/00
    A1 PATENT APPLICATION
    ©) Date of filing: 10.11.16. © Applicant (s): NEXTAERO CONCEPT Company by (© Priority: simplified actions - FR. @ Inventor (s): LAMADON THOMAS. ©) Date of public availability of the request: 11.05.18 Bulletin 18/19. ©) List of documents cited in the report preliminary research: Refer to end of present booklet (© References to other national documents ® Holder (s): NEXT AERO CONCEPT Company by related: simplified actions. ©) Extension request (s): (© Agent (s): A.P.I CONSEIL Société anonyme.
    AIRCRAFT ENGINE INSTALLATION / REMOVAL DEVICE.
    FR 3 058 406 - A1 (h /) The invention relates to a device for placing / removing and transferring an engine (20) of an aircraft in the form of a carriage (100) comprising on the one hand, a chassis (110) mounted on idler wheels (111, 112, 113, 114) and on the other hand, a cradle (150) for receiving said motor (20), said device being characterized in that it comprises actuators ( 160) pneumatic and / or hydraulic, arranged at the interface between the chassis (110) and the cradle (150) and able on the one hand to allow the cradle to be lifted relative to the chassis and on the other hand to absorb shocks and / or vibrations, said actuators making it possible to raise the cradle in a first lifting position necessary for fitting / removing the motor, then to maintain it in a second rest position under load to absorb vibrations and / or shocks undergone by the cradle-engine assembly with respect to the chassis.
    154,118
    DEVICE FOR INSTALLING / DEPOSITING AND TRANSFERRING A DAERONEF ENGINE [Field of the inventionl [0001] The invention relates to a device for installing and removing, and for transferring aircraft engines. This device allows in particular the mounting of an engine on an aircraft and its disassembly for maintenance or change operations. Transfer operations involve moving the engine from one workshop to another as well as from one site to another, requiring road, sea or air transport. These installation / removal or transfer operations take place during assembly operations of an aircraft for example, or during maintenance operations.
    [Prior art!
    Handling such engines is long and tedious because, although bulky and heavy, these engines, when they are not in operation, have fragile components. The ball bearings of these motors, in particular, are very expensive and very fragile parts which can deteriorate easily during transfer or installation and removal operations, due to vibrations and / or shocks.
    [0003] During the removal operations, a system called "bootstrap kit" in the aeronautical field makes it possible to separate the engine from the wing of the aircraft and place it on a trolley. The cart includes a chassis mounted on idler wheels and a removable cradle to accommodate the engine. More particularly, the "bootstrap kit" removal system is in the form of a crane crane. It makes it possible to lift the cradle of the carriage by four points and to secure it to the engine at four points distributed on either side of its center of gravity, two attachment points being arranged towards the front of the engine and two others attachment points being arranged towards the rear of the engine. The removal system then makes it possible to rest the cradle-engine assembly on the chassis of the trolley, more particularly on shock absorbers made of flexible rubber-like material, known under the Anglo-Saxon name "silentbloc" and arranged between the chassis and the cradle. The cradle is then held securely to the chassis. However, if the silent blocks dampen vibrations during transport, they do not effectively absorb any shocks that may occur.
    It therefore becomes necessary to adapt the transport vehicles by adding an air cushion suspension system in order to absorb shocks during the transport of the engine. Thus, a truck and / or its trailer must for example be equipped with such an air cushion suspension system on each axle. In this case, the carriage, on which the engine is placed, is secured to the vehicle by its chassis, leaving the cradle free in order to maintain the effectiveness of the silentblocs in absorbing vibrations.
    The installation / removal and transfer of an aircraft engine is therefore difficult to implement, long and expensive since it requires the use of means of transport with suitable suspensions and means of specific lifting that is difficult to handle and takes a long time to set up.
    Solutions have been envisaged to simplify the engine installation / removal operations with a trolley equipped with lifting means.
    For this, document US2012 / 0110816 describes an installation / removal and transfer system for an aircraft engine in the form of a carriage comprising a chassis and a cradle. Lifting means make it possible to lift the cradle to deposit an aircraft engine thereon when it is removed from its support. These lifting means are in the form of screw actuators connected to the cradle by means of seals. Each actuator operates independently of the others. During positioning, the chassis also rests on air shoes allowing the carriage to be moved with little effort in order to position it precisely under the engine. These pads are used only during this phase of positioning the carriage relative to the engine. The truck must then be loaded on a vehicle whose suspensions are adapted to be able to absorb shocks and vibrations during transport.
    This trolley always requires the use of a means of transport with suitable suspensions. Consequently, the engine is not effectively protected during the removal or installation phases, movement between a removal zone and a loading zone, and loading on a suitable vehicle.
    The plaintiff therefore sought a way to simplify the construction of such a carriage to reduce the cost of its manufacture and allow its transport on a standard vehicle requiring no adaptation of its suspensions, to simplify its use, to protect the engine during all phases of its life as soon as the latter leaves its aircraft wing position and finally to reduce the time required to perform the complete removal or installation procedure.
    [Technical problem [0010] The invention therefore aims to remedy at least one of the drawbacks of the prior art. The invention aims in particular to propose an alternative device for installing / removing and transferring an aircraft engine which is simple in construction, inexpensive, easy to use, and which can be loaded onto any type of means of transport without requiring to adapt its suspensions and to protect the engine as soon as it leaves its position under aircraft wing.
    [Brief Description of the Inventionl To this end, the invention relates to a device for placing / removing and transferring an aircraft engine in the form of a carriage comprising on the one hand, a chassis mounted on idler wheels and on the other hand, a cradle for receiving said motor, said device being characterized in that it comprises pneumatic and / or hydraulic actuators, arranged at the interface between the chassis and the cradle and capable of on the one hand to allow a lifting of the cradle with respect to the chassis and on the other hand, to absorb shocks and / or vibrations, said actuators making it possible to raise the cradle in a first lifting position necessary for fitting / removing the engine, then keep it in a second position of rest under load to absorb vibrations and / or shocks undergone by the cradle-engine assembly relative to the chassis.
    According to other optional characteristics of the device:
    - The cradle comprises at least two crosspieces resting on said actuators and at the ends of which shock absorbers are fixed, the chassis comprising support parts forming a housing for the actuators.
    - The support parts include two vertical lateral guide walls for the crosspieces during the lifting of the cradle, a horizontal wall supporting the actuators and a wall forming a stop for the shock absorbers.
    - the support parts are in the form of a seat, the seat of which corresponds to the horizontal wall and the back of which corresponds to the wall forming a stop. Advantageously, said support parts are arranged so as to have a seat turned towards the cradle, the back corresponding to the wall forming a stop that can be inclined relative to a vertical axis from 0 ° to -89 ° and preferably from -1 ° to - 20 °.
    - In another configuration, the seat-shaped support parts can be arranged in an inverted manner, the seat being turned towards the outside of the chassis, the backrest corresponding to the wall forming a stopper being able to be inclined relative to a vertical axis of 0 ° to + 89 ° and preferably a range of +1 ° to + 20 °.
    - when the actuators are pneumatic they are inflated with air or with an inert and stable gas, and when they are hydraulic they are filled with an incompressible liquid;
    - When the actuators are pneumatic, the pressure necessary to reach the first lifting position and to relieve the airfoil of the aircraft from the weight of the engine is between 1 bar and 10 bars, and preferably between 1 bar and 8 bars; and the pressure necessary to maintain the loaded cradle in the second loaded rest position is between 2 bars and 9 bars, and preferably between 4 bars and 8 bars;
    - when the actuators are pneumatic, they are actuators with flexible membrane with at least one wave and when they are hydraulic, they are actuators with rigid walls or with flexible membrane;
    - The device comprises at least two actuators arranged along a median longitudinal axis of the chassis.
    - The device comprises at least three actuators, at least two of which are arranged on either side of the median longitudinal axis of the chassis;
    - Advantageously, there are four actuators, each being arranged at the interface between the end of a cross member of the cradle and the chassis, and in that at least the actuators arranged under the same cross member of the cradle are identical two to of them ;
    - each actuator can operate independently of the others or can operate in parallel with one or more other actuators as required;
    - the cradle comprises on the upper ends of two vertical uprights a reception part, the upper surface of which has an opening with inclined walls in the shape of a "V", in order to facilitate the introduction of fastening parts fixed to the engine ;
    - The device further comprises one or two bars for holding the rear part of the engine.
    The invention also relates to a method of removing / installing and transferring an aircraft engine, said method being characterized in that it is implemented by means of the device as described above and during removal, it includes the following steps:
    - A first step of positioning the carriage in line with the motor and inflating the actuators to position the cradle so that the fastening parts, previously fixed on the motor, fit into the reception parts arranged at the end of the vertical uprights of the cradle,
    a second load-shedding step, consisting in inflating the actuators to a load-shedding pressure, in order to unload the wing of the aircraft from the weight of the engine, and to separate the engine from the wing of the aircraft,
    a third release step, according to which the actuators are deflated to lower the cradle by a height allowing the carriage to move out of the area under the wing of the aircraft,
    a fourth damping step, consisting in inflating the actuators to a damping pressure of the engine-cradle assembly, said cradle then being in a rest position under load,
    - a fifth step consisting in moving the trolley towards a loading zone then in loading it on a means of transport and during the installation of the engine, the implemented steps are carried out in the reverse order of removal.
    [Presentation of Figures!
    Other features and advantages of the invention will appear on reading the following description given by way of illustrative and nonlimiting example, with reference to the appended figures which represent:
    • Figure 1, a schematic front perspective view of the device according to the invention loaded with an aircraft engine, the cradle being disposed in the rest position under load, • Figure 2, a schematic rear perspective view of the device of Figure 1, • Figure 3, a schematic front perspective view of the device according to the invention when the cradle is in the lifting position.
    [Detailed description of the invention] The device according to the invention described below, allows the installation or removal and the transfer of an aircraft engine. It is particularly suitable for civil and military aircraft equipped with under-wing engines.
    In the following description, the same references are used to designate the same elements.
    The term "longitudinal axis" means a direction parallel to the ground and along the length of the carriage.
    The term "cross" or "transverse direction" means a direction parallel to the ground and along the width of the carriage.
    By "vertical" is meant a direction along an axis perpendicular to the ground.
    The device 100 according to the invention, as shown schematically in front and rear perspective in Figures 1, 3 and 2, comprises a chassis 110 and a cradle 150 for receiving the engine 20. The same references are used in the Figures 1 to 3 to designate the same elements.
    The chassis 110 is mounted on four idler wheels 111, 112, 113, 114, capable of being locked in position and braked during the various installation / removal operations or during the loading operations on a vehicle to be transported. These wheels can also be folded away and thus be erased to allow the chassis 110 to be securely secured to the chassis of the transport vehicle.
    The cradle 150 more particularly comprises vertical uprights 152, 153 and transverse 154, 155 connected together. The transverse uprights 154, 155 of the cradle, also known as “sleepers” in the following description, rest on the chassis 110 and more particularly on actuators 160, pneumatic and / or hydraulic, which form an interface between the chassis 110 and the cradle 150.
    These actuators 160 allow, when inflated, to raise the cradle, then lower it as they deflate, in order to perform the delicate operations of installation and removal without the need to use the installation / removal system "bootstrap kit" used until now. The cradle 150 still has the original attachment points 158, 159 allowing the optional use of the "bootstrap kit". Another function of these actuators 160 is to absorb shocks and vibrations during delicate installation / removal, transport and handling operations, in particular avoiding the costly use of means of transport equipped with suspensions on air cushions, but also avoiding the replacement of engine parts, such as ball bearings, which could be damaged during improper handling or transport.
    To allow the lifting and damping of the cradle, the device comprises at least two actuators 160 placed opposite one another on the median longitudinal axis of the chassis. Preferably, the carriage comprises two actuators at the front, on either side of the median longitudinal axis of the frame 110, for lifting the fan 21 of the engine and an actuator at the rear, along the median longitudinal axis , to support the load of the rear part 22 of the engine. More preferably, it comprises four actuators 160, between the cradle 150 and the chassis 110, two actuators being arranged at the front opposite the fan 21 of the engine and two others at the rear. Such an arrangement of the actuators 160 makes it possible to maintain optimum stability of the cradle 150, to correctly absorb any vibrations and shocks, and to correctly lift the cradle.
    Preferably, the actuators 160 are of the pneumatic type and are in the form of flexible membrane actuators with one, two or three waves. This type of actuator can be inflated using compressed air or an inert and stable gas such as nitrogen gas, for example. In the aeronautical field, the use of nitrogen gas is preferred for inflating this type of actuator. When these actuators are hydraulic, they are preferably in the form of actuators with rigid walls or with flexible membranes and are filled with an incompressible liquid of the oil type.
    All the actuators can be identical, or identical two by two. In the latter case, the two actuators arranged at the front and intended to support the load of the fan 21 are identical to each other, but differ from the two actuators placed at the rear and intended to support the load of the rear part 22 of the engine.
    In a particular example, the carriage comprises four identical pneumatic actuators, with flexible membrane with two waves. In this case, each of the actuators allows, when inflated to a maximum pressure of 8 bars for example, to lift the cradle 150 to a maximum elevation height of 30 cm and to support a maximum load of 42 kN per actuator at this maximum height.
    When the cradle 150 is positioned in the loaded rest position, these actuators 160 are preferably inflated to a pressure between 2 and 9 bars, and more preferably, the inflation pressure is between 4 bars and 8 bars depending on the type of engine, in order to be able to support the engine load and absorb shock and vibration. For this, a user can refer to charts indicating the inflation pressure of each actuator according to the type of engine to be supported. Such a pressure ensures a damping between 7 Hz and 10 Hz of the cradle-engine assembly relative to the chassis.
    Optionally, the carriage further comprises shock absorbers "silentbloc >> 140 arranged near the actuators 160. These shock absorbers 140 allow to provide an emergency function, in the event that there is a leakage of the filling fluid of the actuators 160. In such a case, even if the actuators 160 deflate due to a leak of fluid, the cradle-engine assembly finds itself resting on the silentblocs 140, as in the existing configurations on the chassis of the trolleys on the market.
    For this, the chassis comprises, under the end of each cross member 154, 155 of the cradle, a support piece 116 providing the support functions for the actuators 160, the stop for the shock absorbers 140 and guide for the sleepers 154, 155. More particularly, each piece 116 has two vertical walls 118 for lateral guide for the sleepers 154, 155 during the lifting of the cradle 150, a horizontal wall 117 and parallel to the ground, support for the actuators and a wall 120 forming a stop for shock absorbers 140.
    Thus, the support parts 116 have two vertical walls 118 for lateral guide for the sleepers during the lifting of the cradle, a horizontal wall 117 supporting the actuators and a wall forming a stop 120 for the shock absorbers.
    Advantageously, said support parts 116 are in the form of a seat whose seat corresponds to the horizontal wall 117 and whose back corresponds to the wall forming a stop 120. In the embodiment, the support parts 116 are arranged so as to have a seat facing the cradle 150, the backrest corresponds to the wall forming a stop 120 and can be inclined relative to a vertical axis from 0 ° to -89 ° and preferably from -1 ° to -20 °.
    In another configuration not shown, the support pieces 116 in the form of a seat can be arranged in an inverted manner, the horizontal wall forming the seat 117 facing the outside of the chassis, the back 120 corresponding to the wall forming stop can be tilted with respect to a vertical axis from 0 ° to + 89 ° and preferably from +1 ° to + 20 °.
    Each piece 116 thus forms a housing for an actuator 160 and, along its stop wall 120, a second housing for a shock absorber 140. As described above, the wall 120 forming a stop is preferably slightly inclined relative to the perpendicular to the horizontal wall 117, the ends of the crosspieces being of a shape adapted to come into abutment during the movements of the cradle.
    The cradle 150 comprises at least two cross members 154, 155 disposed against the actuators 160. Preferably, the silentblocs 140 are advantageously fixed to the ends of each cross member 154, 155, and when the cradle 150 is driven in translation towards its lifting position due to the inflation of the actuators 160, the silentblocs 140 are driven with the cross members 154, 155 and come off slightly from the wall 120 of each piece 116 support. The vertical side walls 118 of each piece 116 serve as a lateral guide for the crosspieces during the ascent and descent phase of the cradle 150. FIG. 3 illustrates the installation / removal device according to the invention, the actuators 160 of which are inflated and the cradle 150 of which is in the lifting position.
    The cradle 150 comprises on the upper ends of the vertical uprights 152, 153 a reception piece 156 intended to receive fastening parts 24 fixed on the motor 20. The reception piece 156 has an opening on its upper face, with inclined walls in the shape of a "V", in order to facilitate the introduction of the fastening parts 24 fixed on the motor 20. The fastening parts 24 are advantageously fixed on a transverse axis of the motor, prior to installing or removing the engine. This system makes it possible to precisely position the chassis-cradle assembly relative to the engine.
    When the actuators 160 are completely deflated, that is to say when the cradle is in an empty rest position, the reception pieces 156 at the ends of the vertical uprights 152, 153 of the cradle 150 are located at a distance of the order of 10 cm below the fastening parts 24 of the motor 20.
    The example described below makes it possible to understand the procedure implemented for the removal of an engine for its maintenance.
    Removal phase.
    The aircraft is positioned on flat ground and chocks are positioned under the wheels to avoid any movement of the aircraft during the engine removal operation.
    20. The usual procedures prior to removal of the engine 20, such as opening the covers, disconnecting the energies and fluids, etc. are carried out. The two fasteners 24, allowing the weight of the motor 20 to be taken up on the carriage 100, are installed and fixed directly on the motor 20, on a transverse axis. The carriage, composed of a chassis 110 and a cradle 150, is then moved under the motor 20 by means of two traction bars 119 hooked on one side of the chassis via dedicated attachment points 121 and on the other to a non-schematic handling tractor. The cradle 150 is then in the low idle rest position, that is to say that the actuators 160 are empty and the "silentblocs" 140 are in contact with both the cross members 154, 155 of the cradle 150 and the wall 120 of each part 116 of the chassis. The carriage is positioned under the wing of the aircraft, facing the engine 20, so that the fastening pieces 24 previously fixed on the engine 20 are found as close as possible to the reception pieces 156 in " V >> of the upper end of the vertical uprights 152, 153 of the cradle 150.
    The front and rear actuators 160 then begin to be pressurized in order to inflate them and to lift the cradle 150 relative to the chassis 110 and thus, to allow the fastener parts 24 to come to lodge perfectly in the location of the reception rooms 156 provided for this purpose on the upper end of the vertical uprights 152, 153 of the cradle, thanks to the “V” openings. The entire carriage 100 is therefore positioned relative to the motor 20 during this first positioning step. Such a carriage whose cradle 150 is in the raised position due to the inflation of the actuators 160 is shown diagrammatically in FIG. 3.
    As soon as the fastening pieces 24 are positioned in the reception pieces 156, the rise of the cradle 150 is momentarily interrupted. The four idler wheels 111, 112, 113, 114 are blocked and braked. The operator or operators can then install and fix one or two holding bars 130 of the rear part 22 of the engine. This (these) bar (s) is (are) advantageously fixed (s) at one end 131 on the lower part of the cradle, the other end being fixed on the rear part 22 of the engine 20. The operator or operators fix at in addition to transverse axes 157 making it possible to hold the fastening parts 24 in their housings 156. The actuators 160 are then again filled until a pressure corresponding to the lifting height necessary to support the motor is obtained. This pressure is advantageously between 1 bar and 10 bars, and preferably between 1 bar and 8 bars depending on the type of engine. It can be determined from a removal chart corresponding to the type of engine to be removed. The pressure indicated for each actuator 160, or each pair of actuator, then corresponds to the pressure necessary to relieve the airfoil of the aircraft from the weight of the engine 20 in order to allow the operators to unscrew the engine attachment bolts when these these are unconstrained. The weight of the motor 20 is then entirely supported by the actuators 160.
    As soon as the engine attachment bolts are removed, the actuators 160 begin to be emptied in order to reduce the pressure and gently lower the cradle - engine assembly until all the silentblocs 140 are in their housing in contact with the abutment wall 120 of the chassis 110. The carriage 100, loaded with its motor 20, is then moved a few meters using the traction bars 119 and the handling tractor to exit the under-wing area. The actuators are not necessarily completely emptied, there may be a little pressure for the actuators to play their role of shock absorbers, but the cradle must be low enough to allow the motor to be released from the underwater area, avoiding shocks. This step is called the "release step".
    Transport phase:
    Once the engine 20 is safe outside the wing area, a damping step consists of refilling the actuators 160 simultaneously until a pressure corresponding to the height of the rest position under load, intended to effectively absorb shock and vibration. For this, this pressure can be determined from damping diagrams corresponding to the type of engine to be transported. Typically, it is advantageously between 2 and 9 bars, and more preferably between 4 bars and 8 bars depending on the type of engine to be transported. Such a pressure makes it possible in particular to ensure damping of between 7 Hz and 10 Hz of the cradle-engine assembly relative to the chassis. The trolley, in this configuration, can then be moved to a loading area, then loaded, once the idle wheels are braked and / or folded, on a means of transport to be transported safely.
    Installation phase:
    The installation phase is similar to the removal phase, but with the reverse steps. Thus, initially, the carriage 100 loaded with its motor 20 is moved into the under-wing area. In this first step, the actuators 160 are not necessarily completely emptied, there may be a little pressure for the actuators to play their role of shock absorbers, but the cradle must be low enough to allow positioning of the motor in the under sail area avoiding impact. The carriage 100 is positioned under the wing of the aircraft, in line with an attachment mark for the engine 20. The four idle wheels 111, 112, 113, 114 are locked and braked. The actuators 160 are then filled again until a pressure corresponding to the lifting height necessary to fix the engine to the wing is obtained. This pressure is advantageously between 1 bar and 10 bars, and preferably between 1 bar and 8 bars depending on the type of engine. This pressure supports the weight of the engine and lifts it to a height necessary to allow operators to fix it to the wing and to screw the engine attachment bolts without being forced. The weight of the motor 20 is then fully supported by the actuators 160. Once the motor is fixed to the airfoil, the actuators 160 are slightly deflated to gradually support the weight of the motor by the airfoil. This deflation is interrupted to allow the operator to detach the retaining bar or bars 130 from the rear part 22 of the engine as well as the transverse axes 157 making it possible to maintain the fastening parts 24 in their housings 156, so as to release the fastening parts 24 of the motor 20 of the reception parts 156 of the cradle 150. The carriage is then completely detached from the motor and no longer supports the weight of the motor. The actuators 160 can be completely deflated in order to lower the cradle to an idle rest position.
    Such a trolley thus configured can be installed on a standard vehicle, such as a truck or a trailer, without having to go through a transporter equipped with equipment specially designed to damp the frequencies between 7Hz and 10Hz recommended by the main engine manufacturers. In addition, thanks to the configuration of this carriage, the motor is amortized from its removal phase, unlike existing carriages which run a significant risk of shock during the engine lowering phases, transport between the removal area and the loading area, and loading on a means of transport equipped with suitable suspensions.
    The carriage which has just been described makes it possible not only to reduce the risk associated with shocks which may occur on fragile parts of the engine when it is not in operation, but also to reduce the installation / removal time. It makes it possible to carry out on its own all the stages of installation or removal, without requiring the use of the system of installation / removal "kit bootstrap" used until now to place and remove the engine and place it on the cradle of the carriage. Furthermore, the risk associated with the installation of a “bootstrap kit” above an engine is eliminated when using the cart described.
    权利要求:
    Claims (13)
    [1]
    Claims:
    1. Device for installing / removing and transferring an aircraft engine (20) in the form of a carriage (100) comprising, on the one hand, a chassis (110) mounted on idle wheels (111, 112, 113 , 114) and on the other hand, a cradle (150) for receiving said motor (20), said device being characterized in that it comprises pneumatic and / or hydraulic actuators (160), arranged at the interface between the chassis (110) and the cradle (150) and able on the one hand to allow a lifting of the cradle relative to the chassis and on the other hand, to absorb shocks and / or vibrations, said actuators making it possible to lift the cradle in a first lifting position necessary for fitting / removing the engine, then maintaining it in a second resting position under load to absorb vibrations and / or shocks undergone by the engine cradle assembly relative to the chassis.
    [2]
    2. Device according to claim 1, characterized in that the cradle (150) comprises at least two crosspieces (154, 155) resting on said actuators (160) and at the ends of which shock absorbers (140) are fixed, and in that the frame (110) comprises parts (116) forming a housing for the actuators (160).
    [3]
    3. Device according to claim 2, characterized in that the support parts (116) comprise two vertical walls (118) for lateral guide for the crosspieces (154, 155) during the lifting of the cradle (150), a horizontal wall (117 ) actuator support and a wall (120) forming a stop for the shock absorbers (140).
    [4]
    4. Device according to claim 2 or 3, characterized in that the support parts (116) are in the form of a seat whose seat corresponding to the horizontal wall (117) and whose back corresponding to the wall forming a stop (120).
    [5]
    5. Device according to claim 4, characterized in that said support parts (116) are arranged so as to have a seat facing the cradle, the back corresponding to the wall forming a stop being able to be inclined relative to a vertical axis of 0 ° to -89 ° and preferably from -1 <to -20 °.
    [6]
    6. Device according to at least one of the preceding claims, characterized in that when the actuators are pneumatic they are inflated with air or with an inert and stable gas, and when they are hydraulic they are filled with an incompressible liquid .
    Ί. Device according to at least one of the preceding claims, characterized in that when the actuators are pneumatic, the pressure necessary to reach the first lifting position and to relieve the airfoil of the aircraft from the weight of the engine is between 1 bar and 10 bars, and preferably between 1 bar and 8 bars; and the pressure necessary to maintain the loaded cradle in the second loaded rest position is between 2 bars and 9 bars, and preferably between 4 bars and 8 bars.
    [7]
    8. Device according to one of the preceding claims, characterized in that when the actuators (160) are pneumatic, they are actuators with flexible membrane with at least one wave, and when they are hydraulic, they are wall actuators rigid or flexible membrane.
    [8]
    9. Device according to one of the preceding claims, characterized in that it comprises at least two actuators arranged along a median longitudinal axis of the chassis.
    [9]
    10. Device according to one of claims 1 to 7, characterized in that it comprises at least three actuators, at least two of which are disposed at the front on either side of the median longitudinal axis of the chassis.
    [10]
    11. Device according to one of the preceding claims, characterized in that the actuators (160) are four in number, each being arranged at the interface between the end of a cross member (154, 155) of the cradle (150) and the chassis (110), and in that at least the actuators arranged under the same crosspiece (154, 155) of the cradle (150) are identical two by two.
    [11]
    12. Device according to any one of the preceding claims, characterized in that the cradle comprises on the upper ends of two vertical uprights (152, 153) a reception part (156) whose upper surface has an opening with walls inclined in the shape of a "V", in order to facilitate the introduction of fasteners (24) fixed on the motor (20).
    [12]
    13. Device according to any one of the preceding claims, characterized in that it further comprises one or two holding bars (130) of the rear part (22) of the motor (20).
    [13]
    14. A method of removing / installing and transferring an aircraft engine (20), said method being characterized in that it is implemented by means of the device (100) according to one of the preceding claims, in that during of removal, it includes the following steps:
    - A first step of positioning the carriage (100) in line with the motor (20) and inflating the actuators (160) to position the cradle (150) so that the fastening parts (24), previously fixed on the motor (20), are inserted in the reception parts (156) arranged at the end of the vertical uprights (152, 153) of the cradle (150);
    - a second load-shedding step, consisting in inflating the actuators (160) to a load-shedding pressure, to unload the wing of the aircraft from the weight of the engine, and to separate the engine from the wing of the aircraft,
    a third release step, according to which the actuators are deflated to lower the cradle by a height allowing the carriage to move out of the area under the wing of the aircraft,
    - a fourth damping step, consisting in inflating the actuators (160) to a damping pressure of the engine-cradle assembly, said cradle then being in a rest position under load,
    - a fifth step consisting in moving the cart to a loading area and then loading it onto a means of transport;
    - and in that, during the installation of the engine, the steps implemented are carried out in the reverse order of removal.
    1/3
    154,118
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3058406A1|2018-05-11|AIRCRAFT ENGINE INSTALLATION / REMOVAL AND TRANSFER DEVICE.
    FR2867766A1|2005-09-23|INSTALLATION FOR LOAD TRANSFER BETWEEN A TRANSFER PLATFORM AND A TRANSPORT VEHICLE
    FR2919545A1|2009-02-06|MODULAR VEHICLE FOR HEAVY TRANSPORT, IN PARTICULAR A PORT
    FR2904817A1|2008-02-15|SYSTEM AND METHOD FOR TRANSPORTING AN OBJECT IN MULTIPLE DIRECTIONS.
    FR3058987A1|2018-05-25|ORGAN AND TROLLEY FOR THE REMOVAL, TRANSPORT, AND MAINTENANCE OF A TURBOMACHINE
    EP2576312A1|2013-04-10|Transport wagon having an interface for compensating height relative to the ground, mainly according to the weight of the load to be transported
    EP2548764B1|2015-06-24|Loading aid device
    FR2967118A1|2012-05-11|PROTECTIVE DEVICE FOR BATTERY EXCHANGE STATION
    EP0112778B1|1987-04-29|Loading platform for carrying a truck or a goods container with adapting means for road, rail and oversea transport
    EP3049279B1|2018-10-17|Mobile logistics base, transport bed to be loaded with a vehicle and light vehicle for providing such a base
    FR3068325A1|2019-01-04|DEPOSITABLE ASSEMBLY FOR LOADING / UNLOADING A SEMI-TRAILER ON A RAIL STRUCTURE OF WAGON-POCHE
    FR3055010A1|2018-02-16|DEVICE FOR TRANSPORTING THE SLING OF A PNEUMATIC BOAT IN OPERATIONAL CONFIGURATION UNDER HELICOPTER
    FR3099453A1|2021-02-05|Handling support, handling system and method implementing such a support
    EP3024694B1|2019-08-07|Wheeled vehicle for transferring heavy loads, having a plurality of low-height articulated modules
    WO2019207224A1|2019-10-31|Device and method for adjusting the height of a vehicle on a loading platform
    FR2877891A1|2006-05-19|Boat launching device for boat carrying trailer, has cross-ties fixed on tubular structures of fair-leads and supporting rollers that are transversally moved for aligning cross-ties on origin rollers on trailer to slide hull towards rear
    FR2878794A1|2006-06-09|SUPPORT AND TRANSFER TRAVERSE FOR LOADING AND UNLOADING A LOAD, ON A TRAILER FROM A TRUCK EQUIPPED WITH A LOAD HANDLING ARM.
    FR2987794A1|2013-09-13|Vehicle i.e. road trailer, for transporting motorcycle, has axle comprising elongate body and support for mounting on frame, and support mounted relative to frame, where end of rod of jack is articulated to support
    EP3219541B1|2020-04-08|Set of two vehicles for distributing objects
    FR2926758A1|2009-07-31|Loading arrangement for e.g. trailer in military application, has sliding unit distinct from maintaining unit that maintains base and subframe to be inseparable during their sliding, where maintaining unit is distinct from locking unit
    FR2654054A1|1991-05-10|PROVISION FOR TRANSPORT BY RAIL AND FOR LOADING AND UNLOADING OF ROAD VEHICLES, SUCH AS TRUCKS AND SIMILAR VEHICLES, AS WELL AS MOBILE CASES, OF RAILWAY CARS THAT CARRY THEM.
    EP1209027A1|2002-05-29|Light utility vehicle with a removable container
    WO2009019328A1|2009-02-12|Handling vehicle, particularly for use in ports
    BE1011735A3|1999-12-07|Portable device for fitting and removing a wheel
    FR3112020A1|2021-12-31|RADIOACTIVE MATERIAL TRANSPORT PACKAGING SUPPORT SYSTEM, CONFIGURED TO ALLOW ITS TILTING FROM A HORIZONTAL TRANSPORT POSITION TO A VERTICAL OPERATING POSITION
    同族专利:
    公开号 | 公开日
    US20190322391A1|2019-10-24|
    FR3058406B1|2020-11-06|
    WO2018087492A1|2018-05-17|
    EP3538474A1|2019-09-18|
    CA3065656A1|2018-05-17|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4461455A|1981-09-30|1984-07-24|The Boeing Company|Aircraft engine lifting and positioning apparatus|
    US6485247B1|2000-09-28|2002-11-26|The Boeing Company|Engine uplift loader|
    EP2165932A2|2008-09-17|2010-03-24|CLAAS Fertigungstechnik GmbH|Transport and fitting vehicle for a component module|
    WO2015185811A1|2014-06-06|2015-12-10|Aircelle|Assembly for handling an aircraft engine|CN111203830A|2020-03-10|2020-05-29|中烜航空科技有限公司|Equipment with universal adjusting function for assembling airplane parts|US2825477A|1953-09-04|1958-03-04|Henry M Ross|Engine work stand and method of using the same|
    KR200271162Y1|1999-05-11|2002-04-10|이원해|coupler for excavator|
    GB2462405B|2008-05-29|2010-09-08|Rolls Royce Plc|A cradle arrangement|
    US20120110816A1|2010-11-08|2012-05-10|The Boeing Company|Engine Loading System|CN110561327A|2019-08-27|2019-12-13|中国民航大学|Three-degree-of-freedom aero-engine installation posture adjustment simulation system|
    CN112498708B|2020-06-01|2022-02-08|重庆宗申航空发动机制造有限公司|Aviation unmanned aerial vehicle and aeroengine installing support|
    CN111824451B|2020-06-23|2021-09-07|成都飞机工业（集团）有限责任公司|Aircraft part transports guarantor type device|
    CN111747053A|2020-07-17|2020-10-09|中国十九冶集团有限公司|Installation device of large ball mill in limited space|
    CN113414582A|2021-06-21|2021-09-21|佛山新成洪鼎机械技术有限公司|Six-degree-of-freedom numerical control centering installation device|
    法律状态:
    2017-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-05-11| PLSC| Publication of the preliminary search report|Effective date: 20180511 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-28| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1660908|2016-11-10|
    FR1660908A|FR3058406B1|2016-11-10|2016-11-10|AIRCRAFT ENGINE INSTALLATION / REMOVAL AND TRANSFER DEVICE.|FR1660908A| FR3058406B1|2016-11-10|2016-11-10|AIRCRAFT ENGINE INSTALLATION / REMOVAL AND TRANSFER DEVICE.|
    CA3065656A| CA3065656A1|2016-11-10|2017-11-10|Aircraft engine installation/removal and transfer device|
    US16/348,757| US20190322391A1|2016-11-10|2017-11-10|Aircraft engine installation/removal and transfer device|
    PCT/FR2017/053076| WO2018087492A1|2016-11-10|2017-11-10|Aircraft engine installation/removal and transfer device|
    EP17804626.4A| EP3538474A1|2016-11-10|2017-11-10|Aircraft engine installation/removal and transfer device|
    [返回顶部]