ES2615156A1 - Lifting platform for aircraft engines (Machine-translation by Google Translate, not legally binding) - Google Patents

Abstract

Lifting platform for aircraft engines. The proposed lifting platform includes a frame (10) formed by at least two spars (11) and a crosspiece (12); at least four vertical displacement lifting devices (30) disposed on said two spars (11); at least four bed supports (40) attached to said lifting devices (30) and intended to be connected to a supporting bed of an aviation engine; a first sliding mechanism (41) guided in a direction parallel to a longitudinal axis (l) interposed between each bed support (40) and the frame (10), a second sliding mechanism (42) guided in a direction parallel to the transverse axis (t) interposed between each bench support (40) and the frame (10). (Machine-translation by Google Translate, not legally binding)

Description

ELEVATOR PLATFORM FOR AIRCRAFT ENGINES

Field of the technique 5 The present invention concerns the field of lifting platforms for aircraft engines, adapted to the lifting and handling of aircraft engines, typically jet engines that are suspended from the bottom of aircraft wings, allowing its coupling and decoupling of said wing for assembly, repair or replacement.

10 State of the art Aircraft engines typically hang from the bottom of the wing of an airplane, supported by screws or bolts. Frequently said engines must be removed for repair or overhaul, or replaced by others, so handling of such engines becomes necessary. The heavy weight of the engines, which can weigh several

15 tons, greatly complicates this operation. The usual technique consists of joining chains to anchors of the wing and also to the motor, tightening said chains to relieve the tension supported by the aforementioned screws or bolts, and proceeding to remove them. After that the chains are lengthened by a ratchet mechanism, lowering the engine to

20 deposit it on a support bench for aircraft engines where said engine is anchored and allows its safe transfer. Examples of such benches are described for example in GB2509230. Other documents raise benches with some improvements that allow the lifting and lowering of the fixed motor, for example document DE3427042, document DE19612626 or

25 document US2012110816, but the lifting capacities of these solutions are limited, allowing poor elevation, and precise positioning of the engine after its elevation also very complicated, although the aforementioned document US2012110816 proposes to raise the assembly on airbags offering certain freedom of movement of the assembly over said airbags. This solution also requires a

30 technically very sophisticated bench for each one of the engines to be manipulated, because after its manipulation the bench is occupied by an engine and cannot attend to other engines.

This same problem also affects other solutions such as the one stated in the document.

EP2165932, which uses a truck equipped with a lifting platform. To avoid this problem, lifting platforms are known that allow to support and lift one of said benches, so that after the elevation of the bench and its union with the engine, they can deposit said bench with the engine on the ground and proceed to repeat the operation with another bench on another motor, in this way the benches can be simple support structures and the same lifting platform can be used repeatedly. Examples of this solution are those described in US2005198797 and US6485247. However, none of the proposed solutions allow a precise adjustment of the position and inclination of the bench attached to the lifting platform, which is essential for the correct union and release of the engine with respect to the wing of the aircraft without causing damage to it or to the bolts or screws holding the motor to the wing.

BRIEF DESCRIPTION OF THE INVENTION The present invention concerns a lifting platform for aircraft engines comprising:

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a frame defining longitudinal, transverse and vertical axes orthogonal to each other, said frame being at least two spaced apart and symmetrical with respect to said longitudinal axis, and by a crossbar that rigidly joins the stringers, said two stringers defining each other a empty cargo space suitable to house a support bench of an aviation engine;

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at least four lifting devices arranged facing two to two, symmetrical with respect to said longitudinal axis and supported on said two stringers, each lifting device having a vertical travel stroke parallel to the vertical axis ranging from a position of minimum elevation to a position of maximum elevation;

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at least four bed supports, each connected to one of said lifting devices, said bed supports being able to be connected to said support bed of an aviation engine;

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a first sliding mechanism, guided in a direction parallel to the longitudinal axis, said first sliding mechanism being interposed between each support and the frame, allowing a guided displacement of each of said supports in said direction parallel to the longitudinal axis.

Thus, said frame has a general U-shaped configuration, with a crossbar that connects and separates two symmetrical stringers that will preferably be parallel to each other. The space between the crossbars is sized to accommodate a bench of an aviation engine, whose shape, size and fixing points are sized to receive, support and sustain an aviation engine to allow transport, storage and maintenance. The rest of the platform elements will be supported on said frame.

Typically, said benches have a chassis formed by a framework of tubular steel profiles to which frame supports are attached which include motor anchor points positioned in complementary positions with the positions of motor anchors provided in said motor motors. airplane, so that the connection of the motor anchors and the motor anchor points rigidly joins said engine to said aircraft engine bed. The said benches also include lifting points, typically sized to allow the attachment of a forklift.

On said frame at least four lifting devices are fixed, facing two to two arranged symmetrically on the two frame beams. Each lifting device is connected to the same aircraft engine support bed by means of a bed support anchored to said lifting device, so that the set of all the bed supports of all the lifting devices, all connected to the same bed of support, allow a vertical displacement of the aforementioned aircraft engine support bench from a position of minimum elevation to a position of maximum elevation, by means of the coordinated operation of all lifting devices.

Said bed support is an element intended to be connected to a support bed of an aviation engine, either directly or through an interposed element. In this way, the at least four lifting devices equipped with the corresponding at least four bed supports can, by means of the aforementioned connection of the bed supports with a bed, raise said bed to an engine hung on a wing of an airplane, or lift an engine attached to a bench to a wing of an airplane. You can also do reverse descent operations.

It is also contemplated the integration of at least four first sliding mechanisms arranged between each of said at least four bed supports and the platform frame, allowing a relative displacement of said bed supports with respect to the frame in a direction parallel to the longitudinal axis of the frame.

Additionally, and in a novel way, it is contemplated that the platform also includes:

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a second sliding mechanism, guided in a direction parallel to the transverse axis, is interposed between each bed support and the frame, allowing guided movement of each of said bed supports in said direction parallel to the transverse axis; and because

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the at least four lifting devices, and the corresponding first sliding mechanisms and second sliding mechanisms are actuated by means of actuating devices.

It will be understood that an actuator device is a mechanism that creates a displacement, either rotary or linear, driven by an external source of energy without human work intervention. Said energy source may be, by way of example, electrical energy, or a liquid or gaseous fluid supplied under pressure, for example from a compressor. Examples of actuator devices can be, without limitation, a rotary or linear electric motor, a hydraulic or pneumatic piston, a hydraulic or pneumatic motor, etc.

Thus, said second sliding mechanism allows a displacement of each of said bed supports relative to the frame in a direction parallel to the transverse axis.

Thus, the combination of the lifting devices, the first sliding mechanisms and the second sliding mechanisms allow, without displacing the platform from its position, to raise or lower a support bench for aircraft engines, to move it in the transverse direction and in the longitudinal direction , thus allowing an adjustment of the position of the bench with respect to an engine attached to a wing, or of the engine attached to the bench with respect to a wing, with three degrees of freedom of translation, thus simplifying assembly tasks and disassembly of aircraft engines for replacement or maintenance.

Additionally, according to an optional embodiment, it is proposed that said actuating devices of each lifting device, of each first sliding mechanism and of each second sliding mechanism have independent regulation systems that allow a differentiated adjustment of their drives.

It will be understood that the regulation systems are mechanisms or devices, whether mechanical, electrical or electronic, that allow controlling and modifying the actuation parameters of said actuator devices, allowing for example to regulate the actuation time, the path of their stroke, applied torque, speed

drive, the power used, etc. Such regulation systems can be, for example, levers, switches, stopcocks, valves, electric frequency inverters, programmable electronic devices such as a PLC (programmable logic controller), and can react to signals supplied by a user , and / or by a stored program, / or by data obtained through sensors.

This independent regulation not only allows to modify the existing separation between the different bed supports, thus adapting the platform to different formats and sizes of benches and engines, but also allows three degrees of freedom of rotation to be added to the position of the bench with respect to a engine attached to a wing, or engine attached to the bench relative to a wing. This independent regulation allows:

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tilt a bench attached to the supports around an axis parallel to the longitudinal axis, by means of a different elevation of the lifting devices of each stringer;

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tilt the bench attached to the supports around an axis parallel to the transverse axis, by means of a differentiated elevation of the lifting devices closest to the crossbar with respect to the lifting devices furthest from the crossbar;

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rotate the bench attached to the supports around an axis parallel to the vertical axis, by means of a differentiated displacement of the second sliding mechanisms supported on the same beam, in coordination with the second sliding mechanisms supported on the symmetrical beam.

Thus, the proposed platform allows to position an engine in any position, within the operating margins of the different mechanisms and devices of the platform, having six degrees of freedom of movement of said engine with respect to the platform, allowing precise regulation of the position of the aircraft engine without the need to move the platform assembly.

According to another embodiment, the lifting devices include walkable platforms that rise together with the lifting device. This feature allows operators to comfortably access both the engine and the wing of the aircraft to which the engine is attached, facilitating repair and assembly and disassembly.

Optionally the walkable platforms of mutually adjacent lifting devices supported on the same beam are connected to each other by articulated walkable bridges that allow a differentiated movement of the

connected passable platforms. This allows an operator to transit between two adjacent walkable platforms, while allowing a differentiated displacement of said platforms.

Additionally, it is proposed that said second sliding mechanism be positioned between each passable platform and its corresponding lifting device, so that said second sliding mechanism moves the passable platform with respect to the lifting device. In this case, the corresponding bench support will be connected to said passable platform and will move along with it.

According to another additional embodiment, the first sliding mechanism is located between each bed support and the corresponding passable platform. In the case of being the support attached to the passable platform, said first sliding mechanism is located between the bed support and the passable platform, preferably the end of the passable platform closest to the loading space located between the two stringers.

In another preferred embodiment, the lifting devices described above are scissor lifting devices, formed by a structure of articulated bars in the form of scissors or pantographs that allow, being in a position of minimum elevation, to occupy a very small vertical space, and allowing to place said scissor mechanism under the passable platform, if any, although other lifting mechanisms are also contemplated such as vertical pistons, pulley systems, rack and cogwheel systems, etc. In spite of that, the preferred embodiment is that of a scissor lift device, since it does not require vertical guide elements along the vertical travel stroke of the lift device, which could hinder the positioning operations of the lift platform with respect to A plane engine.

Due to the high weight that said scissor mechanism must lift, when it is loading an airplane engine and its corresponding support bench, it is proposed that at least a portion of the lifting stroke of the scissor lift devices be driven at least by a pusher arranged in a direction parallel to the vertical axis or in a direction with an inclination of ± 30 ° with respect to said direction parallel to the vertical axis.

Said scissor mechanisms can be operated by a horizontal thrust of an actuator, such as the rotation of a spindle, or by a vertical thrust.

or almost vertical of an actuator device such as a piston. In the case of the horizontal actuator, at the start of the vertical stroke the bars that make up the scissors are almost aligned, so that the force required for its elevation in much greater than

in later stages of elevation when the bars form an angle to each other. Since the weight to be lifted by said lifting device can be very large, it is contemplated that, at least during said initial part of the vertical travel of the lifting device, an actuator device produces a vertical thrust to produce the initial lift without producing the aforementioned effect caused by the low angle between the scissor arms. Once this initial stage is over, the rest of the elevation can be produced by the same vertical actuator device, or by means of a horizontal actuator device that allows a greater elevation to be achieved without taking up vertical space in a position of minimum elevation.

Preferably in the position of minimum elevation of the passable platform, said supports are less than 40cm from the ground on which the motor lifting platform sits. This means that the supports can be anchored to the bench below the height of the aircraft engine, thus allowing an operator located on the walkable platforms to access said engine laterally, and also allowing the side covers that typically surround the engines Aircraft can be opened without interfering with the aforementioned passable platforms, the engine being supported by the mentioned supports.

Said supports are, according to a preferred embodiment, freely articulated with respect to the rest of the platform with at least three degrees of freedom, and preferably with six degrees of freedom. This allows the angle formed by the support with the rest of the lift platform for aircraft engines to be adapted according to the position taken by said engine or engine support bench with respect to said lift platform.

The lifting platform is also proposed to be supported on wheels, allowing its displacement, also contemplating the possibility that at least a part of said wheels are motorized for autonomous propulsion of the lifting platform. As an example, it is proposed that the lifting platform consist of at least four self-steering wheels located at four ends of the lifting platform. Additionally, another additional wheel can be included in each spar, is motorized and not self-oriented, so that the independent regulation of each of said motorized wheels in combination with the self-orientating wheels, allows to move and maneuver the lifting platform. Said motorized wheels can be lifted or uncoupled from the engine to allow the drag of the lifting platform.

Additionally, the possibility of the lifting platform having lifting struts provided with a vertical travel parallel to the axis is contemplated.

vertical, said vertical race being protuberant on the face of the platform facing the ground, allowing an elevation of the platform as a whole from the ground by means of the controlled extension of said lifting struts by said face facing the ground.

Said lifting struts can be regulated independently to keep the platform perfectly horizontal in an elevated position with respect to the ground, even if said ground is not perfectly horizontal.

These struts allow to lift the whole of the lifting platform, and complement the elevation produced by the lifting devices so that, together, an elevation of several meters can occur, thus achieving the position of the engines located under the wings of aircraft of big size. According to an example without limitation, the lifting struts allow an elevation of between 1 and 2 meters such as 1.3 meters, and the lifting devices allow an elevation of between 1 and 2 meters such as 1.5 meters. In this way, the lifting platform could, according to this described example, produce an elevation of between 2 and 4 meters such as an elevation of 2.8 meters.

It is also proposed that the lifting platform includes sensors that detect the relative position of a wing of an aircraft, or of an engine detached from said lifting platform, with respect to said lifting platform. This feature allows the lifting platform to be automatically guided, without human intervention, to a position close to the engine position or wing position, allowing a user to make final adjustments.

Another proposed additional feature is that each bed support integrates an independent weight sensor. In this way you can determine the distribution of forces between the different elements of the lifting platform and also know the total weight supported. Similarly, precise control of the force exerted by a motor attached to the lifting platform on a wing to which said motor is coupled from below is allowed. This data is decisive to avoid damage to the motor, the wing, or the connectors between both elements, and they allow to easily release said connectors between both elements by removing the load supported by said connectors by lifting the lifting platform.

It will be understood that references to geometric position, such as parallel, perpendicular, tangent, etc. they admit deviations of up to ± 5º with respect to the theoretical position defined by said nomenclature.

Other features of the invention will appear in the following detailed description of a embodiment example.

Brief description of the figures The above and other advantages and features will be more fully understood from of the following detailed description of an exemplary embodiment with reference to the attached drawings, which should be taken for illustrative and non-limiting purposes, in which:

Fig. 1 shows a perspective view of a lift platform for aircraft engines,

said lifting platform being in a position of minimum elevation; Fig. 2 shows a perspective view of a lift platform for aircraft engines as shown in Fig. 1, said lifting platform being in maximum position elevation, with extended lifting struts and four lifting devices also elevated to its maximum height;

Fig. 3 shows an enlarged detail of one of the stringers shown in Fig. 2, and of

the two lifting devices attached to said stringer; Fig. 4 shows a perspective view of a scissor lift device isolated from the rest of the lifting platform and devoid of the passable platform, showing the first and the second sliding mechanisms;

Fig. 5 shows a view of the proposed lifting platform arranged under a wing of an airplane being the engine of the plane attached to a support bench, and said bench of support attached to the lifting platform;

Fig. 6 shows a side elevation of the platform shown in Fig. 1 in the position of

minimum elevation; Fig. 7 shows a side elevation of the platform shown in Fig. 2 in the position of maximum elevation;

Fig. 8 shows a plan view of the lifting platform shown in Fig. 1.

Detailed description of an exemplary embodiment Fig. 1 shows, in an illustrative non-limiting manner, an embodiment of the lifting platform 1 for proposed aircraft engines. Said lifting platform 1 is composed of a U-shaped frame 10 that surrounds a central empty cargo space 20 intended to accommodate a support bed for aircraft engines. Said frame 10 is formed by two parallel and spaced members 11 connected by a crossbar

12. Said frame 10 is passable on its upper face for operators, and supports

all the components that make up the lifting platform 1. Said lifting platform 1 extends parallel to a floor, and defines a longitudinal axis L, horizontal and centered between both stringers 11, a transverse axis T, perpendicular to the axis longitudinal L and also horizontal, and a vertical axis V orthogonal with the other two axes.

Said frame 10 is supported on a floor on six sets of wheels 60, four of said sets of wheels 60 being located in the four extreme corners of the lifting platform 1 and being sets of 60 self-orientating wheels. The rest two sets of wheels 60 are each located in the central region of each of the two stringers 11, being sets of 60 motorized wheels and not self-orientable. This 60 wheel configuration allows the lifting platform 1 to be self-driven and addressed by the regulated drive of said wheel assemblies 60 motorized It is also proposed that motorized wheel assemblies 60 can be retracted, or disconnected from the engine, allowing the lifting platform 1 to be dragged For this purpose, a coupling, preferably in the center of the crossbar 12, for the coupling of a tractor vehicle.

In order to produce the retraction of the motorized wheels 60 it is contemplated to join them to the rest of the

lifting platform by means of a mechanism that allows to regulate its vertical position. It is also proposed that each of the wheels 60 be connected to the rest of the lifting platform by means of a shock absorber, allowing to absorb small irregularities of the terrain through which it circulates and overcome small obstacles of low height.

The proposed lifting platform 1 further includes four lifting struts 70 located surrounding said empty cargo space 20 confined between the stringers 11. Each of said lifting struts 70 consists of a hydraulic piston located parallel to the vertical axis V, and is connected to the frame 10 so that, when driven, a piston protrudes from the face of the frame 10 facing the ground, applying a force against said floor and thereby producing the lifting of the lifting platform 1 and its load. The four lifting struts 70 are coordinated to maintain the horizontality of the frame 10 at all times even if the floor is not completely horizontal. This is achieved by sensors, for example tilt sensors, and laser sensors measuring distance between the ground and the frame 10 connected to a regulation system responsible for regulating the drive parameters of each of said lifting struts 70.

Preferably said lifting struts 70 are fed with hydraulic fluid

from a compressor located on the frame 10, for example on the crossbar 12. Additionally it is proposed that at least the lifting struts 70 further away from the crossbar 12 can be knocked down by means of an articulation when they are folded to avoid interference with an aircraft engine during the approach and positioning maneuvers of the lifting platform under said engine attached to an aircraft wing.

Each of the stringers 11 also integrates two lifting devices 30 adjacent to the central loading space 20 of the lifting platform 1, said central loading space 20 being surrounded by two stringers 11 and four lifting devices 30.

Each lifting device 30 integrates a horizontal walkable platform 31 through which a user can travel, preferably at least partially surrounded by safety rails.

Under said passable platform 31 a scissor or pantograph mechanism is located, formed by rigid bars articulated with each other, connected to a horizontal spindle 33 parallel to the transverse direction T, actuated by means of an actuator device 50 which preferably will be an electric motor or hydraulic

The rotation of the spindle 33 driven by the motor will cause a displacement of one end of at least one of the rigid bars of the scissor or pantograph mechanism, which is proposed to have guide elements such as those shown in Fig. 4, producing an elevation of the walkable platform 31 with respect to the frame 10. This type of scissor mechanisms actuated by means of spindle 33 allows an elevation in the direction of the vertical axis V and to perform said elevation with great precision, especially if the actuator device 50 is regulated by means of regulation systems that allow precise control of the angle and / or speed of rotation of said motor drive.

Due to the different distribution of the forces depending on the angle formed by the articulated rigid bars that make up the lifting device 30 described, the lifting device 30 being in a position of minimum elevation, shown in Fig. 4, in which the walkable platform 31 can no longer descend with respect to the frame 10, the vertical component of the effort applied on the lifting device 30 by the spindle 33 is only a very small fraction of the total effort introduced, because the articulated bars form an angle obtuse only slightly lower than 180º. To avoid this effect, without sacrificing the precise control of the elevation provided by the spindle mechanism 33, it is also proposed to include a starter piston 34 that provides a

vertical thrust to the lifting device 30 during the initial part of its stroke, providing an additional vertical component effort to the lifting device 30 in its initial section of the upward stroke. Once the angle formed by the rigid bars of the lifting device 30 with each other has exceeded a certain threshold, the action of said starting piston 34 is irrelevant, and therefore its stroke stops without preventing the lifting platform 30 from continuing its vertical stroke. driven by a spindle mechanism 33. With this construction the cited starter piston 34 can be of short length and be integrated in the thickness of the frame 10 without hindering the passage of the operators, or the manipulation of the aircraft engines, as the mechanism of scissors or pantograph, in a position of minimum elevation, it is very compact and can be housed below the walkable platform 31.

The walkable platforms 31 may also have extendable ladders for

facilitate the access of the operators from the frame 10 or from the ground. Said walkable platform 31 is connected to the corresponding lifting device 30 by means of a second sliding mechanism 42 which allows the movement of said walkable platform 31 in a direction parallel to the transverse axis T with respect to the corresponding lifting device 30.

In this exemplary embodiment, said second sliding mechanism 42 is composed of guides on which the walkable platform 31 can be guided in the direction of the transverse axis T, and of a mechanism composed of a spindle 43 connected to said platform drive 31 driven by an actuator 50 which in this case consists of an electric or hydraulic motor that allows a controlled rotation of the spindle 43, thanks to a regulation system, thus allowing a precise adjustment of the position of the walkable platform 31 with respect to the lifting device 30.

At the end of said walkable platform 31, a bench support 40 is fixed by a first sliding mechanism 41 which allows said bench support 40 to move in a direction parallel to the longitudinal axis L with respect to the corresponding walkable platform 31.

Said bed support 40 is an element intended to be connected to an airplane engine support bed which is located in the cargo space 20 located between the beams 11, in the manner shown in Fig. 5. In the present example of embodiment said bed support 40 is articulated with respect to a carriage that slides along some

guides parallel to the longitudinal axis L, driven by a spindle driven by

actuator devices 50, such as an electric or hydraulic motor. The fact that the bed support 40 is articulated, for example by means of a ball joint, With respect to the car, it prevents unwanted efforts caused by the loading of the bench and of an airplane engine are transmitted to the platform elements lift 1, loads such as bending moments or torso efforts.

The first sliding mechanism 41 allows a precise adjustment of the position of the support of

bench 40 with respect to the corresponding passable platform 31. Adjacent walkable platforms 31 mounted on the same crossbar 11 are preferably connected to each other by an articulated walkable bridge 32, allowing a user to safely move from one passable platform 31 to the other.

The regulation systems allow independent and differentiated regulation of each lifting device 30, of each first sliding mechanism 41 and of each second sliding mechanism 42, allowing precise regulation of spatial position and angle of a load formed by a bench and / or an engine, which are attached to the lifting platform 1 through the mentioned bench supports 40:

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the uniform operation of the lifting devices 30 allows the ascent and descent of the load;

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the uniform actuation of the first sliding mechanisms 41 allows the displacement of the load in the direction of the longitudinal axis L;

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the uniform actuation of the second sliding mechanisms 42 allows the displacement of the load in the direction of the transverse axis T;

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the differentiated actuation of the lifting devices 30 close to the crossbar 12 with respect to the lifting devices 30 far away from the crossbar 12 allows the rotation of the load around an axis parallel to the transverse axis T;

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the differentiated actuation of the lifting devices 30 held on a beam 11 with respect to the lifting devices 30 held on the other beam 11 allows the rotation of the load around an axis parallel to the longitudinal axis L;

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the differentiated drive of the second sliding mechanisms 42 of adjacent walkable platforms 31 supported on the same crossbar 11 relative to each other and in coordination with the drive of the second

sliding mechanisms 42 of the facing lifting devices 30 allows the

rotation of the load around an axis parallel to the vertical axis V. This allows six degrees of freedom to be offered to the handling of the load, which provides a precise adjustment of its position.

5 All these drives can be controlled manually, either from a fixed or wireless center console, or from different fixed or wireless partial consoles,

or automatically following instructions of a regulation system formed by a programmable logic controller equipped with programmed routines, and which can optionally receive sensor information and produce adjustments depending on the readings of said

10 sensors, for example moving the entire lifting platform 1 to a position suitable for handling the load, or operating the different mechanisms to place a bench attached to the lifting platform 1 in a position close to the position required for placement or removal of an engine with respect to a wing.

Examples of the sensors that could equip the said lifting platform 1 are

15 load sensors connected to each bed support 40, position detecting sensors that allow to detect the position of a bed, an engine or a wing of an airplane, with respect to the mobile platform 1, presence detectors to stop the operation in case if there is a risk for an operator, tilt detectors to know the position of both the lifting platform 1 and the load, etc.

20 The independent regulation of the different mechanism of the lifting platform 1 not only allows the position of a load to be modified, but also allows the lifting platform 1 to be adapted for handling different models of benches and different models of aircraft engines.

Additionally, it is proposed to include tools intended to be inserted into

25 openings of a bed, and provided with complementary couplings with the bed supports 40 of the lifting platform 1. Optionally said tools can include regulation means to modify some of their dimensional parameters thus allowing a better coupling of said bed supports 40 to any type of bench.

Claims (10)

1.-Lift platform for aircraft engines comprising:

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a frame (10) defining longitudinal (L), transverse (T) and vertical (V) axes orthogonal to each other, said frame (10) being formed by at least two stringers

(11) distanced and symmetrical with respect to said longitudinal axis (L), and by a crossbar (12) that rigidly joins the stringers (11), said two stringers (11) defining an empty loading space (20) suitable for to house a support bench of an aviation engine;

•

at least four lifting devices (30) arranged facing two to two, symmetrical with respect to said longitudinal axis (L) and supported on said two stringers (11), each lifting device (30) having a vertical travel stroke parallel to the vertical axis (V) ranging from a position of minimum elevation to a position of maximum elevation;

•

at least four bed supports (40), each connected to one of said lifting devices (30), said bed supports (40) being able to be connected to a support bed of an aviation engine;

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a first sliding mechanism (41), guided in a direction parallel to the longitudinal axis (L), said first sliding mechanism (41) interposed between each bed support (40) and the frame (10), allowing a guided displacement of each one of said bed supports (40) in said direction parallel to the longitudinal axis (L);

 characterized by that

•

a second sliding mechanism (42), guided in a direction parallel to the transverse axis (T), is interposed between each bed support (40) and the frame (10), allowing guided movement of each of said bed supports ( 40) in said direction parallel to the transverse axis (T); and because

•

the at least four lifting devices (30), and the corresponding first sliding mechanisms (41) and second sliding mechanisms (42) are actuated by actuator devices (50).

2.-Lifting platform according to claim 1 characterized in that said actuator devices (50) of each lifting device (30), of each first mechanism Sliding (41) and each second sliding mechanism (42) have systems of independent regulation that allows a differentiated adjustment of its drives. 3.-Lifting platform according to claim 1 or 2 characterized in that the lifting devices (30) include transitable platforms (31) that rise together with the lifting device (30). 4. Lifting platform according to claim 3 characterized in that the transitable platforms (31) of adjacent lifting devices (30) supported on the same beam (11) are connected to each other by articulated transitable bridges (32) that allow a differentiated movement of the passable platforms (31) connected. 5.-Lifting platform according to claim 3 or 4 characterized in that said second sliding mechanism (42) is located between each passable platform (31) and its corresponding lifting device (30), and because the corresponding bed support (40) is linked to said passable platform (31). 6.-Lifting platform according to claim 3, 4 or 5 characterized in that the first sliding mechanism (41) is located between each bed support (40) and the corresponding passable platform (31). 7.-Lifting platform according to any one of the preceding claims, characterized in that the lifting devices (30) are scissor. 8.-Lifting platform according to claim 7 characterized in that at least a portion of the lifting stroke of the scissor lift devices (30) is driven by less by a pusher arranged in a direction parallel to the vertical axis (V) or in a direction with an inclination of ± 30 ° with respect to said direction parallel to the vertical axis (V). 9.-Lifting platform according to any one of the preceding claims, characterized in that in the position of minimum elevation of the lifting platform (1), the cited bench supports (40) are less than 40cm from the ground on which it sits said lifting platform (1). 10.-Lifting platform according to any one of the preceding claims, characterized in that said bed supports (40) are freely articulated with respect to the rest of the lifting platform (1) with at least three degrees of freedom, and preferably with six degrees of freedom. 11. Lifting platform according to any one of the preceding claims, characterized in that said lifting platform (1) is supported on wheels (60). 12. Lifting platform according to claim 11 characterized in that at least a part of said wheels (60) are motorized for autonomous propulsion of the lifting platform (1). 13.-Lifting platform according to any one of the preceding claims, 5 characterized in that it has lifting struts (70) equipped with a vertical displacement run parallel to the vertical axis (V), which protrude from the face of the lifting platform (1) facing the ground, allowing an elevation of the lifting platform (1) with respect to the ground. 14.-Lift platform according to claim 13 characterized in that the lifting struts 10 (70) are regulated independently to maintain the lifting platform (1) perfectly horizontal in an elevated position with respect to the ground. 15.-Lifting platform according to any one of the preceding claims, characterized in that it includes one or more of the following sensors: • sensors that detect the relative position of a wing of an airplane, or of an engine 15 detached from said lifting platform, with respect to said lifting platform;

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weight sensors on each of the bench supports;

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tilt sensors of the lifting platform;

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user presence sensors;

20 • distance sensors between the lifting platform and the ground;

•

position sensors of the different mobile elements of the lifting platform;

•

hydraulic fluid pressure sensors.

DRAWINGS