Aircraft engine replacing device

Abstract

The utility model discloses an aircraft engine replacing device, which comprises a chassis, the suspension arm assembly is movably connected with the chassis, and the chassis is used for driving the suspension arm assembly to move; the control mechanism is connected with the suspension arm assembly, and the control mechanism is used for controlling the suspension arm assembly to hoist an aircraft engine; and the driving mechanism is connected with the chassis and the suspension arm assembly, and the driving mechanism is used for driving the suspension arm assembly to translate and / or rotate relative to the chassis. According to the aircraft engine replacement device, high precision and high efficiency of aircraft engine replacement can be achieved, and meanwhile the requirement for the skill level of a user is low.

Description

TECHNICAL FIELD

[0001] The utility model relates to engine replacement technical field especially, it is a kind of aircraft engine replacement device. BACKGROUND

[0002] Aircraft engine replacement is an important technology in the field of aeronautical engineering and maintenance, involving complex engineering design, safety standards and operating procedures.

[0003] In related technologies, hydraulic truck crane is often used for hoisting during the replacement of domestic military aircraft engines. The engine is fixed by a special clamp and sling, and the angle and height of the lifting arm are adjusted by a hydraulic system to ensure the alignment of the engine and the aircraft pylon. Multiple workers are required to cooperate during operation, and the hoisting position is adjusted in real time to avoid collision with the fuselage structure.

[0004] However, in the prior art, the aircraft engine replacement precision is low and the efficiency is low, and the skill level of the user is required to be high. UTILITY MODEL CONTENTS

[0005] The utility model aims at at least one of the technical problems existing in the prior art. Therefore, one purpose of the utility model is to provide an aircraft engine replacement device. The device can achieve high precision and high efficiency in aircraft engine replacement, while the skill level of the user is required to be low.

[0006] According to the aircraft engine replacement device provided by the utility model, it comprises:

[0007] A chassis;

[0008] A lifting arm assembly, which is movably connected to the chassis, and the chassis is used to drive the lifting arm assembly to move;

[0009] A control mechanism, which is connected to the lifting arm assembly, and the control mechanism is used to control the lifting arm assembly to hoist the aircraft engine;

[0010] A driving mechanism, which is connected to the chassis and the lifting arm assembly respectively, and the driving mechanism is used to drive the lifting arm assembly to translate and / or rotate relative to the chassis.

[0011] According to the aircraft engine replacement device provided by the embodiment of the utility model, the bottom disc is arranged to provide stable support for the aircraft engine replacement device, and the overall structural stability of the aircraft engine replacement device is further enhanced; the hoist arm assembly is arranged to hoist the aircraft engine and transmit it to the corresponding installation position, so that the flexibility of the aircraft engine replacement device can be improved; the control mechanism is arranged to accurately control the movement of the hoist arm assembly, such as the pitch angle and height of the hoist arm assembly, so that the installation angle and height of the aircraft engine can be accurately controlled to realize high-precision positioning and attitude adjustment during the hoisting of the aircraft engine, and the requirement for the skill level of the user can be reduced, and the convenience and reliability during the replacement of the aircraft engine can be improved; the driving mechanism is arranged to drive the hoist arm assembly to translate or rotate relative to the bottom disc to adjust the position of the hoist arm assembly, so that the installation position of the aircraft engine can be adjusted, and the convenience of disassembly and maintenance of the aircraft engine can be improved. Through the cooperative work of the control mechanism and the driving mechanism, the aircraft engine replacement device can realize high-precision positioning and rapid replacement of the aircraft engine, so that the maintenance efficiency can be significantly improved.

[0012] In some examples of the utility model, the hoist arm assembly comprises:

[0013] The support arm and the lifting arm are hingedly connected to each other, one end of the support arm is connected to the driving mechanism, and one end of the lifting arm is provided with a lifting hook.

[0014] In some examples of the utility model, the control mechanism comprises:

[0015] The lifting assembly is connected to the support arm at one end and connected to the lifting arm at the other end, and is used for controlling the rotation of the lifting arm.

[0016] The telescopic assembly is arranged in the lifting arm and is used for controlling the telescoping of the lifting hook.

[0017] The winch assembly is connected to the support arm, the hinge of the winch assembly passes through the lifting arm and is connected to the lifting hook, and the winch assembly controls the hoisting of the lifting hook for the aircraft engine.

[0018] In some examples of the utility model, the driving mechanism comprises:

[0019] The mounting plate is arranged on the bottom disc and is used for fixing the driving mechanism.

[0020] The support arm is fixedly connected to the mounting plate through the rotation module, and the rotation module is used for driving the rotation of the support arm.

[0021] A horizontal module, the mounting plate is slidably connected with the chassis through the horizontal module, and the horizontal module drives the support arm to move through the mounting plate.

[0022] In some examples of the utility model, the rotating module comprises:

[0023] A rotary table, a fixed end of the rotary table is fixedly connected with the mounting plate, and a movable end of the rotary table is fixedly connected with the support arm;

[0024] A rotating motor, the rotating motor is fixedly connected with the mounting plate, and the rotating motor is in transmission connection with the movable end of the rotary table.

[0025] In some examples of the utility model, the horizontal module comprises:

[0026] A guide rail, the guide rail is fixedly connected with the chassis;

[0027] A sliding block, the sliding block is slidably connected with the guide rail, and the sliding block is fixedly connected with the mounting plate;

[0028] A sliding motor, the sliding motor is fixedly connected with the mounting plate, and the sliding motor is in transmission connection with the sliding block.

[0029] In some examples of the utility model, the winch assembly comprises:

[0030] A winch, the winch is rotatably connected with the support arm, one end of the hinge is arranged on the winch, and the other end of the hinge is connected with the lifting hook;

[0031] A rotating motor, the rotating motor is fixedly connected with the support arm, and the rotating motor is in transmission connection with the winch.

[0032] In some examples of the utility model, the aircraft engine replacing device further comprises:

[0033] A controller, the controller is fixedly connected with the mounting plate, and the controller is electrically connected with the control mechanism and the driving mechanism respectively.

[0034] In some examples of the utility model, the chassis comprises:

[0035] A rolling wheel, the rolling wheel is arranged at the bottom of the chassis;

[0036] A folding support leg, one end of the folding support leg is fixedly connected with the chassis, and the folding support leg is used for providing support for the chassis.

[0037] In some examples of the present application, the aircraft engine replacement device further comprises: a traction assembly, the traction assembly is arranged at one end of the chassis, and the traction assembly is used for towing the aircraft engine replacement device.

[0038] Additional aspects and advantages of the present application will be given in part in the following description, and will become apparent from the following description, or will be learned by practice of the present application. BRIEF DESCRIPTION OF DRAWINGS

[0039] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiment or prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0040] Figure 1 The structure schematic diagram of the aircraft engine replacement device in working state is provided according to the present application.

[0041] Figure 2 The structure schematic diagram of the aircraft engine replacement device in normal state is provided according to the present application.

[0042] Figure 3 The structure schematic diagram of the chassis is provided according to the present application.

[0043] Figure 4 The structure schematic diagram of the traction assembly is provided according to the present application.

[0044] Explanation of reference signs:

[0045] 10-aircraft engine replacement device;

[0046] 100-chassis; 110-roller; 120-folding leg; 121-threaded screw rod; 122-rocker; 123-supporting piece; 124-limiting pin; 130-containing cavity;

[0047] 200-hoisting arm assembly; 210-supporting arm; 220-lifting arm; 221-fixed section; 222-telescopic section; 230-lifting hook;

[0048] 300-control mechanism; 310-lifting assembly; 320-telescopic assembly; 330-winch assembly; 331-winch; 332-hinge; 333-rotation motor;

[0049] 400 - drive mechanism; 410 - mounting plate; 420 - rotation module; 421 - rotary table; 4211 - fixed end; 4212 - movable end; 422 - rotary motor; 430 - horizontal module; 431 - guide rail; 432 - sliding block; 433 - sliding motor;

[0050] 500 - controller;

[0051] 600 - traction assembly; 610 - traction rod; 620 - knuckle; 630 - steering pin; 640 - locking pin; 650 - steering link. DETAILED DESCRIPTION

[0052] In order to make the purpose, technical scheme and advantages of the embodiments of the present application more clear, the technical scheme in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without making creative efforts fall within the scope of protection of the present application.

[0053] In the description of the present application, it should be understood that the orientations or positional relationships indicated by the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the features defined as "first" and "second" can explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise specified, the meaning of "a plurality of" is two or more.

[0054] In the description of the present application, it should be noted that, unless otherwise explicitly specified and limited, the terms "mounting", "connection" and "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0055] The embodiments of the present application are described below in detail, examples of which are shown in the drawings, wherein the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by reference to the drawings are exemplary only, and are used to explain the present application, and cannot be understood as a limitation of the present application.

[0056] Figure 1 A structural schematic diagram of the aircraft engine replacement device according to the present application in a working state; Figure 2 A structural schematic diagram of the aircraft engine replacement device according to the present application in a normal state; Figure 3 A structural schematic diagram of the chassis according to the present application; Figure 4 A structural schematic diagram of the traction assembly according to the present application.

[0057] Reference is made below Figures 1-4 The aircraft engine replacement device 10 according to the embodiments of the present application is described below, which comprises: a chassis 100; a boom assembly 200, the boom assembly 200 is movably connected with the chassis 100, the chassis 100 is used to drive the boom assembly 200 to move; a control mechanism 300, the control mechanism 300 is connected with the boom assembly 200, the control mechanism 300 is used to control the boom assembly 200 to hoist the aircraft engine; a driving mechanism 400, the driving mechanism 400 is connected with the chassis 100 and the boom assembly 200 respectively, the driving mechanism 400 is used to drive the boom assembly 200 to translate and / or rotate relative to the chassis 100.

[0058] Specifically, the chassis 100 can be configured as a rectangular structure with an accommodating cavity 130 inside, and the chassis 100 can be made of a metal material, which usually has high strength and rigidity and can withstand large loads and stresses, thereby greatly improving the load-carrying capacity of the chassis 100. The chassis 100 can provide stable support for the aircraft engine replacement device 10, further enhancing the overall structural stability of the aircraft engine replacement device 10.

[0059] Part of the components of the boom assembly 200 can be movably connected with the chassis 100, so that the boom assembly 200 can move relative to the chassis 100; another part of the components of the boom assembly 200 can be fixedly connected with the chassis 100, so that the chassis 100 can provide support for the boom assembly 200. The boom assembly 200 can be movably connected with the aircraft engine, so that the boom assembly 200 can hoist the aircraft engine and transmit it to the corresponding installation position, thereby improving the flexibility of the aircraft engine replacement device 10.

[0060] The control mechanism 300 can be connected with the boom assembly 200, and the control mechanism 300 can be arranged at one end of the chassis 100 in the length direction of the chassis 100, and the length direction of the chassis 100 is the direction indicated by X in the figure. Figure 1 The control mechanism 300 can accurately control the movement of the boom assembly 200, for example, the pitch angle and height of the boom assembly 200, so as to accurately control the installation angle and height of the aircraft engine, so as to realize high-precision positioning and attitude adjustment in the aircraft engine hoisting process. The control mechanism 300 can reduce the requirement for the skill level of the user, thereby improving the convenience and reliability of the aircraft engine replacement and maintenance.

[0061] The driving mechanism 400 can be fixedly connected with the chassis 100 and the boom assembly 200 through threaded connection. In this way, the driving mechanism 400 can drive the boom assembly 200 to translate relative to the chassis 100, and the driving mechanism 400 can also drive the boom assembly 200 to rotate relative to the chassis 100. In this way, the driving mechanism 400 can adjust the position of the boom assembly 200, so as to adjust the horizontal installation position and angle of the aircraft engine, thereby improving the convenience of disassembly and maintenance of the aircraft engine.

[0062] Through the cooperative work of the control mechanism 300 and the driving mechanism 400, the aircraft engine replacement device 10 can realize high-precision positioning and rapid replacement of the aircraft engine hoisting, thereby significantly improving the maintenance efficiency.

[0063] According to the aircraft engine replacement device 10 provided by the embodiment of the utility model, the chassis 100 can provide stable support for the aircraft engine replacement device 10, and further enhance the overall structural stability of the aircraft engine replacement device 10. The boom assembly 200 can hoist the aircraft engine and transmit it to the corresponding installation position, thereby improving the flexibility of the aircraft engine replacement device 10. The control mechanism 300 can accurately control the movement of the boom assembly 200, for example, the pitch angle and height of the boom assembly 200, so as to accurately control the installation angle and height of the aircraft engine, so as to realize high-precision positioning and attitude adjustment in the aircraft engine hoisting process. In this way, the requirement for the skill level of the user can be reduced, and the convenience and reliability of the aircraft engine replacement can be improved. The driving mechanism 400 can drive the boom assembly 200 to translate or rotate relative to the chassis 100, so as to adjust the position of the boom assembly 200, thereby adjusting the installation position of the aircraft engine, and further improving the convenience of disassembly and maintenance of the aircraft engine. Through the cooperative work of the control mechanism 300 and the driving mechanism 400, the aircraft engine replacement device 10 can realize high-precision positioning and rapid replacement of the aircraft engine hoisting, thereby significantly improving the maintenance efficiency.

[0064] Please continueFigure 1 and Figure 2 As shown in FIGS. 1 and 2, the lifting arm assembly 200 comprises a support arm 210 and a lifting arm 220 hingedly connected to each other, one end of the support arm 210 is connected with the driving mechanism 400, and one end of the lifting arm 220 is provided with a lifting hook 230.

[0065] Specifically, the support arm 210 can be configured as a linear irregular rectangular structure, and the material of the support arm 210 can be a metal material. The metal material (such as steel, aluminum alloy, titanium alloy, etc.) has excellent strength and rigidity, and can withstand the huge load and stress of the aircraft engine during hoisting, so as to ensure that the support arm 210 does not deform or break during hoisting, and the operation safety is ensured. One end of the support arm 210 can be fixedly connected with the driving mechanism 400 in a threaded connection manner. In this way, the driving mechanism 400 can drive the support arm 210 to rotate or translate relative to the chassis 100.

[0066] The lifting arm 220 can be configured as a telescopic mechanical arm, and the material of the lifting arm 220 can also be a metal material. The fixed section 221 of the lifting arm 220 can be movably connected with the other end of the support arm 210 in a hinged manner. In this way, the lifting arm 220 can rotate around the hinge hole (not shown in the figure) by a certain angle, so as to accurately adjust the installation angle of the aircraft engine. The telescopic section 222 of the lifting arm 220 can be slidably connected with the lifting hook 230 through a pulley (not labeled in the figure), so that the lifting hook 230 can move flexibly within the length range of the telescopic section 222, thereby adapting to the hoisting requirements of different positions and angles. The lifting hook 230, as a key component of the lifting arm assembly 200, is specially used for hoisting the aircraft engine. The high strength and accurate positioning capability of the lifting hook 230 can ensure the safety and stability of the aircraft engine during disassembly, installation and transportation. Through the guiding action of the pulley, the lifting hook 230 can smoothly lift and move the engine, reduce shaking and impact, and further improve the efficiency and reliability of the hoisting operation.

[0067] Please continue to refer to Figure 1 and Figure 2 As shown in FIGS. 1 and 2, according to an embodiment of the present application, the control mechanism 300 comprises: a hoisting assembly 310, one end of the hoisting assembly 310 is connected with the support arm 210, the other end of the hoisting assembly 310 is connected with the lifting arm 220, and the hoisting assembly 310 is used for controlling the rotation of the lifting arm 220; a telescopic assembly 320, the telescopic assembly 320 is arranged in the lifting arm 220, and the telescopic assembly 320 is used for controlling the telescopic movement of the lifting hook 230; and a winch assembly 330, the winch assembly 330 is connected with the support arm 210, the hinge 332 of the winch assembly 330 penetrates through the lifting arm 220 and is connected with the lifting hook 230, and the winch assembly 330 controls the lifting hook 230 to hoist the aircraft engine.

[0068] Specifically, the hoisting assembly 310 can be configured as a servo cylinder, which can achieve micron-level or even nanometer-level positioning accuracy, has fast response speed, and can quickly complete starting, stopping and direction switching, thereby accurately regulating the installation position of the aircraft engine and synchronously improving the installation and maintenance efficiency.

[0069] One end of the hoisting assembly 310 can be fixedly connected with the support arm 210 in a threaded connection manner, and the other end of the hoisting assembly 310 can be hingedly connected with the hoisting arm 220. In this way, the hoisting assembly 310 can control the hoisting arm 220 to rotate by a certain angle, so as to accurately adjust the pitch angle of the aircraft engine during installation.

[0070] Further, the telescopic assembly 320 can be configured as a telescopic servo motor, which has the advantages of high precision, high response speed, high rigidity, energy saving and environmental protection, etc. The telescopic assembly 320 can be arranged in the interior of the hoisting arm 220, one end of the telescopic assembly 320 can be fixedly connected with the interior telescopic section 222 of the hoisting arm 220, and the other end of the telescopic assembly 320 can be fixedly connected with the interior fixed section 221 of the hoisting arm 220. In this way, through the telescopic movement of the telescopic assembly 320, the length of the hoisting arm 220 can be driven to change, so as to drive the telescopic movement of the lifting hook 230, and then accurately adjust the installation position of the aircraft engine. In this way, the aircraft engine can be fine-tuned in the horizontal and vertical directions, and the docking accuracy with the aircraft fuselage can be ensured. Flexible control of the telescopic assembly 320 can not only improve the installation efficiency of the aircraft engine, but also reduce the difficulty and risk of manual operation, so as to be applicable to complex space and high-precision engine installation scenarios.

[0071] It should be noted that part of the components of the winch assembly 330 can be fixedly connected with the support arm 210 in a threaded connection manner, so that the support arm 210 can provide support for the winch assembly 330. The hinge 332 of the winch assembly 330 can penetrate through the hoisting arm 220 and be fixedly connected with the lifting hook 230 in a bolt connection manner. In this way, the winch assembly 330 can control the lifting movement of the lifting hook 230 by winding the hinge 332, so as to accurately adjust the height position of the aircraft engine during installation. Through the driving of the winch 331, the lifting hook 230 can stably lift or lower the aircraft engine, so as to ensure that the aircraft engine can be accurately aligned with the target position during installation. In this way, the flexibility and precision of the aircraft engine hoisting can be improved, and the stability and safety of the aircraft engine changing device 10 can also be improved.

[0072] Please continue to see Figure 1 and Figure 2As shown, according to another embodiment of the present application, the driving mechanism 400 comprises: a mounting plate 410; a rotating module 420, the support arm 210 is fixedly connected with the mounting plate 410 through the rotating module 420, and the rotating module 420 is used for driving the support arm 210 to rotate; a horizontal module 430, the mounting plate 410 is slidingly connected with the chassis 100 through the horizontal module 430, and the horizontal module 430 drives the support arm 210 to move through the mounting plate 410.

[0073] Specifically, the mounting plate 410 can be configured as a rectangle or a circle, and can also be configured as other irregular shapes, and the present application does not make specific limitations on this. The mounting plate 410 can be movably arranged at one end of the chassis 100 along the length direction of the chassis 100, and the structural material of the mounting plate 410 can be consistent with that of the chassis 100, for example, can be a metal material. In this way, the strength and rigidity of the driving mechanism 400 can be significantly improved.

[0074] The rotating module 420 can be fixedly connected with the mounting plate 410 through a threaded connection, and the rotating module 420 can be fixedly connected with one end of the support arm 210 through a threaded connection or a welding connection. In this way, the rotating module 420 can drive the support arm 210 to rotate relative to the chassis 100, so as to drive the synchronous rotation of the lifting arm 220, and further adjust the rotation angle of the lifting hook 230. In this way, the lifting hook 230 can be flexibly adjusted at multiple angles in the horizontal plane, so as to accurately control the rotation angle of the aircraft engine during installation. Through the precise driving of the rotating module 420, the installation efficiency of the aircraft engine can be greatly improved, and the difficulty of manual operation can be simultaneously reduced.

[0075] The horizontal module 430 can be fixedly installed in the accommodating cavity 130 of the chassis 100, and the extension direction of the horizontal module 430 can be parallel to the length direction of the chassis 100. The horizontal module 430 can reciprocate along the length direction of the chassis 100. In this way, the horizontal module 430 can drive the mounting plate 410 to reciprocate along the length direction of the chassis 100, so as to drive the support arm 210 to reciprocate along the length direction of the chassis 100, and further adjust the horizontal position of the aircraft engine during installation.

[0076] Please continue to see Figure 1 and Figure 2 As shown, according to another embodiment of the present application, the rotating module 420 comprises: a turntable 421, a fixed end 4211 of the turntable 421 is fixedly connected with the mounting plate 410, and a movable end 4212 of the turntable 421 is fixedly connected with the support arm 210; a rotating motor 422, the rotating motor 422 is fixedly connected with the mounting plate 410, and the rotating motor 422 is in transmission connection with the movable end 4212 of the turntable 421.

[0077] Specifically, the rotary table 421 can be configured as a cylinder, the fixed end 4211 of the rotary table 421 can be fixedly connected with the mounting plate 410 in a threaded connection manner, and the movable end 4212 of the rotary table 421 can be fixedly connected with the support arm 210 in a threaded connection manner. In this way, the rotation of the movable end 4212 of the rotary table 421 relative to the fixed end 4211 can drive the rotation of the support arm 210, so that the installation angle of the aircraft engine can be adjusted.

[0078] The rotary motor 422 can be configured as a servo motor, which has the advantages of high control accuracy, high system efficiency, and use in extreme temperature environments, and has better environmental adaptability and reliability. The rotary motor 422 can be fixedly connected with the mounting plate 410 in a threaded connection manner, so that the mounting plate 410 can provide support for the rotary motor 422. The rotary motor 422 can be drivingly connected with the movable end 4212 of the rotary table 421 in a worm gear (not shown in the figure) connection manner, in this way, the rotary motor 422 can drive the rotary table 421 to rotate, so that the rotation angle of the aircraft engine can be adjusted by the rotary motor 422, and the installation and maintenance efficiency of the aircraft engine can be improved.

[0079] Please continue to see Figures 1-3 As shown, according to the optional embodiment of the utility model, the horizontal module 430 comprises: a guide rail 431 fixedly connected with the chassis 100; a sliding block 432 slidingly connected with the guide rail 431, and the sliding block 432 is fixedly connected with the mounting plate 410; and a sliding motor 433 fixedly connected with the mounting plate 410, and the sliding motor 433 is drivingly connected with the sliding block 432.

[0080] Specifically, the guide rail 431 can be configured as a heavy-load linear guide rail 431, which has the advantages of high load capacity, high precision and high stability, so as to improve the stability and safety of the horizontal module 430. The number of guide rails 431 can be two, and the two guide rails 431 can be fixedly installed on the inner bottom of the chassis 100 in parallel and at intervals in a threaded connection or welding connection manner, and the extension direction of the two guide rails 431 can be consistent with the length direction of the chassis 100. In this way, it can be avoided that the horizontal module 430 collides with other parts during movement and is damaged, so as to further improve the structural stability of the horizontal module 430.

[0081] The sliding block 432 can be slidingly installed on the guide rail 431, and the sliding block 432 can slide relative to the guide rail 431 along the extension direction of the guide rail 431. The sliding block 432 can be fixedly connected with the mounting plate 410 in a threaded connection manner, in this way, the mounting plate 410 can be driven by the sliding block 432 to move along the extension direction of the guide rail 431, so that the reciprocating movement of the boom assembly 200 in the horizontal direction can be realized.

[0082] The sliding motor 433 can be fixedly connected with the mounting plate 410 in a threaded manner. The sliding motor 433 can be a servo motor, which can realize rapid movement of the driving sliding block 432. The mounting plate 410 can be fixedly connected with the driving sliding block 432 in a bolted manner. A gear (not shown in the figure) can be fixedly installed with the output end (not shown in the figure) of the sliding motor 433 in a coaxial manner. A rack (not shown in the figure) can be fixedly installed with the bottom of the chassis 100 in a bolted or welded manner. In this way, through the meshing of the gear and the rack, the rotary motion of the sliding motor 433 can be converted into the linear motion of the driving sliding block 432, thereby realizing the rapid movement of the driving sliding block 432. By driving the servo motor, the lifting arm assembly 200 can move horizontally along the length direction of the chassis 100, facilitating the user to quickly complete the butt joint of the aircraft engine and the aircraft engine pylon and to improve the horizontal displacement accuracy during installation of the aircraft engine.

[0083] Please continue to refer to Figure 1 and Figure 2 According to further embodiments of the present application, the winch assembly 330 includes: a winch 331, the winch 331 being rotatably connected with the support arm 210, one end of a hinge 332 being wound around the winch 331, the other end of the hinge 332 being connected with the lifting hook 230; and a winding motor 333, the winding motor 333 being fixedly connected with the support arm 210 and being in transmission connection with the winch 331.

[0084] Specifically, the winch 331 can be rotatably connected with the support arm 210 in a bearing (not shown in the figure). In this way, the winch 331 can rotate relative to the support arm 210 through the bearing. One end of the hinge 332 can be wound around the surface of the winch 331 in a threaded manner. The other end of the hinge 332 can pass through the inside of the lifting arm 220 and be fixedly connected with the lifting hook 230. In this way, the lifting hook 230 can be lifted and lowered through the winding of the hinge 332 on the winch 331.

[0085] The winding motor 333 can be fixedly installed on one side of the support arm 210 in a threaded manner. The driving rod (not shown in the figure) of the winding motor 333 can be fixedly connected with the drum (not shown in the figure) of the winch 331 in a welding or coaxial connection manner. In this way, the winding motor 333 can drive the winch 331 to rotate to wind the hinge 332, thereby controlling the lifting and lowering of the lifting hook 230.

[0086] Please continue to refer to Figure 1 and Figure 2As shown, in an optional mode of the utility model, the aircraft engine replacement device 10 further comprises: a controller 500, the controller 500 is fixedly connected with the mounting plate 410, and the controller 500 is electrically connected with the control mechanism 300 and the driving mechanism 400 respectively.

[0087] Specifically, the controller 500 can be configured as an electric control box, and the controller 500 can be fixedly connected with the mounting plate 410 in a threaded connection mode, so that the mounting plate 410 can provide support for the controller 500. The controller 500 is electrically connected with the control mechanism 300 and the driving mechanism 400 respectively in a wired connection or wireless connection mode, so that the user can directly adjust the control mechanism 300 and the driving mechanism 400 through the controller 500, thereby realizing high efficiency of aircraft engine replacement and maintenance and reducing the workload of the user.

[0088] The controller 500 can be externally connected with a handheld remote controller (not marked in the figure), and the handheld remote controller can be electrically connected with the controller 500 in a wired connection or wireless connection mode. The user can remotely control the system through the handheld remote controller to monitor and adjust the boom assembly 200 in real time, thereby reducing the dependence on the skill level of the user and simultaneously improving the working efficiency of the user.

[0089] Please continue to see Figures 1-3 As shown, in some examples of the utility model, the chassis 100 comprises: a roller 110, the roller 110 is arranged at the bottom of the chassis 100; and a folding support leg 120, one end of the folding support leg 120 is fixedly connected with the chassis 100, and the folding support leg 120 is used for providing support for the chassis 100.

[0090] Specifically, the roller 110 can be installed at the bottom of the chassis 100 along the height direction of the chassis 100, and the height direction of the chassis 100 can be the direction indicated by Z in the figure. The number of the roller 110 can be four, which are evenly arranged around the bottom of the chassis 100, thereby supporting the entire aircraft engine replacement device 10. Figure 1 The structural material of the roller 110 is rubber, and the rubber material has excellent elasticity, which can effectively absorb impact and vibration and reduce damage to the aircraft engine replacement device 10, thereby improving the stability and safety of the aircraft engine replacement device 10.

[0091] The folding support leg 120 can be configured as a telescopic structure, and along the height direction of the chassis 100, the folding support leg 120 can be movably installed at the bottom of the chassis 100 through a connecting pin (not shown in the figure), which facilitates the quick use of the folding support leg 120. The number of the folding support leg 120 can be four, which are evenly arranged on the opposite sides of the chassis 100 along the width direction of the aircraft engine replacement device 10, and the width direction of the aircraft engine replacement device 10 can be the direction indicated by X in the figure. Figure 1The folding legs 120 are arranged in the direction indicated by Y. In this way, when the aircraft engine replacement device 10 is hoisted, the user can unfold the folding legs 120 to make the folding legs 120 rigidly contact the ground, thereby improving the structural stability of the aircraft engine replacement device 10.

[0092] The folding leg 120 comprises a threaded screw rod 121 and a rocker 122. The threaded screw rod 121 is movably connected to one end of the folding leg 120 by sleeving, and the rocker 122 is fixedly connected to one end of the threaded screw rod 121 by welding or integral forming. In this way, the user can adjust the distance between the threaded screw rod 121 and the ground by rotating the rocker 122, so that the folding leg 120 rigidly contacts the ground, thereby improving the stability of the folding leg 120.

[0093] The folding leg 120 further comprises a support 123 and a limiting pin 124. The support 123 can be configured as a disc structure, a rectangular sheet structure, or other irregular sheet structures, which are not limited in the embodiments of the present application. The support 123 is fixedly connected to the other end of the threaded screw rod 121 by screwing, welding or integral forming. In this way, the support 123 can increase the support surface of the aircraft engine replacement device 10, thereby ensuring the stability and safety of the aircraft engine replacement device 10 during hoisting.

[0094] In the normal state, the folding legs 120 can be folded and placed on both sides of the bottom of the chassis 100, and the limiting pin 124 can limit the rotation of the folding leg 120, thereby saving the space of the aircraft engine replacement device 10 and optimizing the overall structure layout. When the aircraft engine replacement device 10 reaches the specified position, the limiting pin 124 is removed, and the folding leg 120 is rotated to the corresponding position. The user can adjust the rotation position of the folding leg 120 according to the actual application scenario. After determining the position, the limiting pin 124 is reset, and the limiting pin 124 can limit the swinging of the folding leg 120 during work. The user can adjust the threaded screw rod 121 by rotating the rocker 122, so that the support 123 rigidly contacts the ground. Through the four unfolded folding legs 120, the overall center of gravity of the aircraft engine replacement device 10 can be ensured to be always located within the quadrilateral surrounded by the folding legs 120, thereby enhancing the stability of the aircraft engine replacement device 10 during hoisting operation and ensuring the hoisting safety of the aircraft engine.

[0095] Please continue to see Figure 1 and Figure 4 As shown in the drawings, in some examples of the utility model, the aircraft engine replacement device 10 further comprises a traction assembly 600, the traction assembly 600 is arranged at one end of the chassis 100, and the traction assembly 600 is used for towing the aircraft engine replacement device 10.

[0096] The traction assembly 600 is fixedly connected with the chassis 100, and is arranged at an end away from the jib assembly 200 along the length direction of the chassis 100. The traction assembly 600 can comprise a traction rod 610, a steering knuckle 620, a steering pin 630, a steering connecting rod 650 and a locking pin 640.

[0097] The traction rod 610 can be configured as a triangular frame structure, and the traction rod 610 can also be configured as a rectangular frame structure, and the utility model embodiment does not make specific limitation on this. One end of the traction rod 610 can be movably connected with the steering connecting rod 650 through the steering pin 630, and in this way, the traction rod 610 can rotate around the pin shaft, so that the user can mechanically tow the aircraft engine replacement device 10 through the traction rod 610.

[0098] One end of the steering knuckle 620 can be fixedly connected with the chassis 100 in a threaded connection or welding manner, and one side of the steering knuckle 620 can be fixedly connected with the roller 110 in a coaxial connection manner, and the number of the steering knuckles 620 can be multiple, so that the roller 110 can realize steering through the steering knuckles 620.

[0099] The steering connecting rod 650 can be configured as an irregular strip structure, and the steering connecting rod 650 can be movably connected with the steering knuckle 620 through a connecting pin, and the traction rod 610 can be connected with the steering connecting rod 650 through the steering pin 630. In this way, when the traction rod 610 is steered left and right, the traction rod 610 can rotate around the steering pin 630, so as to drive the roller 110 to rotate around the respective steering knuckles 620, and then the steering of the aircraft engine replacement device 10 can be realized. It should be noted that the maximum steering angle of the traction assembly 600 can be ± 50°. The locking pin 640 can be arranged at intervals with the steering pin 630, and when the aircraft engine replacement device 10 needs to be moved, the user can pull out the locking pin 640, at this time, the traction assembly 600 can be steered left and right; after the locking pin 640 is inserted, the locking pin 640 can limit the left and right steering of the traction assembly 600, so as to conveniently park the aircraft engine replacement device 10.

[0100] Other constitutions of the aircraft engine replacement device 10 according to the utility model embodiment, such as welding, threaded connection and the like, and operation are known to those skilled in the art, and will not be described in detail here.

[0101] In the description of the present specification, the description of the terms "one embodiment", "some embodiments", "exemplary embodiment", "example", "specific example" or "some examples" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the exemplary description of the above terms does not necessarily mean the same embodiment or example. Furthermore, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0102] Although the embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the claims and their equivalents.

Claims

1. An aircraft engine replacement device, characterized in that, The utility model provides a kind of aircraft engine replacement device, including: Chassis; Jib assembly, the jib assembly is movably connected with the chassis, the chassis is used to drive the jib assembly to move; Control mechanism, the control mechanism is connected with the jib assembly, the control mechanism is used to control the jib assembly to hoist aircraft engine; Driving mechanism, the driving mechanism is connected with the chassis and the jib assembly respectively, the driving mechanism is used to drive the jib assembly to translate and / or rotate relative to the chassis.

2. An aircraft engine replacement device according to claim 1, wherein, The jib assembly includes: Interconnected support arm and lifting arm, one end of the support arm is connected with the driving mechanism, one end of the lifting arm is provided with a lifting hook.

3. An aircraft engine replacement device according to claim 2, wherein, The control mechanism includes: Hoisting assembly, one end of the hoisting assembly is connected with the support arm, the other end of the hoisting assembly is connected with the lifting arm, the hoisting assembly is used to control the lifting arm to rotate; Telescopic assembly, the telescopic assembly is arranged in the lifting arm, the telescopic assembly is used to control the lifting hook to extend and retract; Winch assembly, the winch assembly is connected with the support arm, the hinge of the winch assembly passes through the lifting arm and is connected with the lifting hook, the winch assembly controls the lifting hook to hoist aircraft engine.

4. An aircraft engine replacement device according to claim 3, wherein, The driving mechanism includes: Mounting plate; Rotary module, the support arm is fixedly connected with the mounting plate through the rotary module, the rotary module is used to drive the support arm to rotate; Horizontal module, the mounting plate is slidingly connected with the chassis through the horizontal module, the horizontal module drives the support arm to move through the mounting plate.

5. An aircraft engine replacement device according to claim 4, wherein, The rotary module includes: Rotary table, the fixed end of the rotary table is fixedly connected with the mounting plate, the movable end of the rotary table is fixedly connected with the support arm; Rotary motor, the rotary motor is fixedly connected with the mounting plate, and the rotary motor is in transmission connection with the movable end of the rotary table.

6. An aircraft engine replacement device according to claim 4, wherein, The horizontal module includes: Guide rail, the guide rail is fixedly connected with the chassis; Sliding block, the sliding block is slidingly connected with the guide rail, and the sliding block is fixedly connected with the mounting plate; Sliding motor, the sliding motor is fixedly connected with the mounting plate, and the sliding motor is in transmission connection with the sliding block.

7. An aircraft engine replacement device according to claim 3, wherein, The winch assembly includes: Winch, the winch is in rotary connection with the support arm, one end of the hinge is arranged on the winch, and the other end of the hinge is connected with the lifting hook; Rotary motor, the rotary motor is fixedly connected with the support arm, and the rotary motor is in transmission connection with the winch.

8. An aircraft engine replacement device according to claim 4, wherein, Further including: Controller, the controller is fixedly connected with the mounting plate, and the controller is electrically connected with the control mechanism and the driving mechanism respectively.

9. An aircraft engine replacement device according to any one of claims 1-8, characterized in that, The chassis includes: Roller, the roller is arranged at the bottom of the chassis; Foldable leg, one end of the foldable leg is fixedly connected with the chassis, and the foldable leg is used to provide support for the chassis.

10. The aircraft engine replacement device of claim 1, wherein, Further including traction assembly, the traction assembly is arranged at one end of the chassis, and the traction assembly is used to tow the aircraft engine replacement device.

Images