Lifting device for assembling general aero-engine

Abstract

The utility model provides a lifting device for assembling a general aero-engine, and solves the technical problems that an existing lifting device for assembling the general aero-engine cannot synchronously rotate during lifting in the using process, and the direction is inconvenient to adjust. Comprising a lifting box provided with a first containing cavity, and the top of the lifting box is not closed; the supporting assembly comprises a supporting base and two oppositely-arranged supporting pieces, the supporting base is in threaded connection to the inner wall of the lifting box, the two supporting pieces are each provided with a sliding block, the supporting base is provided with a sliding groove extending in the radial direction of the supporting base, and the sliding blocks are slidably connected to the sliding grooves; the first driving piece drives the two supporting pieces to move in a reciprocating mode in the extending direction of the sliding groove so as to be close to or away from each other; the second driving piece drives the supporting base to rotate in the axial direction of the lifting box; and the third driving piece is connected to the second driving piece and drives the second driving piece to reciprocate in the axial direction of the lifting box, and high-efficiency adjustment is achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of lifting devices, in particular to a lifting device for assembling general aviation engines. Background Art

[0002] An aero-engine is a highly complex and sophisticated thermal machine. As the heart of an aircraft, it is not only the driving force for the aircraft to fly, but also an important driving force for the development of aviation. Every important change in human aviation history is closely related to the technological progress of aero-engines.

[0003] The assembly of aircraft engines requires the use of a lifting device. The lifting device in the prior art cannot rotate synchronously during lifting and lowering, and the azimuth adjustment is inconvenient. Utility Model Content

[0004] The utility model aims to provide a general aviation engine assembly lifting device to solve the technical problem that the general aviation engine assembly lifting device cannot be rotated synchronously during lifting and lowering and the orientation adjustment is inconvenient during use.

[0005] The embodiments of the present invention are implemented by the following technical solutions:

[0006] A general aviation engine assembly lifting device comprises a lifting box, a support assembly, a first driving member, a second driving member and a third driving member;

[0007] The lifting box is provided with a first accommodating cavity, and the top of the lifting box is not closed;

[0008] The support assembly comprises a support base and two support members arranged opposite to each other, the support base is threadedly connected to the inner wall of the lifting box, the two support members are both provided with a slider, the support base is provided with a slide groove extending along its radial direction, and the slider is slidably connected to the slide groove;

[0009] The first driving member drives the two supporting members to reciprocate along the extending direction of the slide slot so as to move closer to or away from each other;

[0010] The second driving member drives the supporting base to rotate along the axial direction of the lifting box;

[0011] The third driving member is connected to the second driving member, and drives the second driving member to reciprocate along the axial direction of the lifting box.

[0012] In some embodiments, the two support members are connected by a threaded rod, the two support members are provided with threaded holes with corresponding positions and opposite threads, the threaded rod is connected to a first driving member, and the first driving member is a first motor.

[0013] In some embodiments, a driving base is connected to the bottom of the second driving member, the driving base is connected to a third driving member, and the second driving member is a second motor.

[0014] In some embodiments, the third driving member is a telescopic member.

[0015] In some embodiments, the auxiliary lifting member is further included, which is connected to the lifting box. The auxiliary lifting member is connected to a fourth driving member, and the fourth driving member drives the auxiliary lifting member to reciprocate along the axial direction of the lifting box.

[0016] In some embodiments, the auxiliary lifting members correspond to the fourth driving members one by one, and multiple groups are provided and evenly arranged along the circumference of the lifting box.

[0017] In some embodiments, the lifting box is further provided with a box support rod, and the box support rod is a telescopic rod.

[0018] The technical solution of the embodiment of the utility model has at least the following advantages and beneficial effects:

[0019] (1) The utility model provides a support assembly to support an aircraft engine component. The two support members can be driven by a first drive member to reciprocate along the extension direction of the slide slot to move closer to or farther from each other, thereby adjusting the support orientation of the support assembly to the aircraft engine component.

[0020] (2) The utility model is provided with a second driving member to drive the support base to rotate along the axial direction of the lifting box. Since the support base is threadedly connected to the inner wall of the lifting box, it can rise or fall along the axial direction of the lifting box during rotation, thereby realizing synchronous adjustment of rotation and lifting, and increasing adjustment efficiency.

[0021] (3) The utility model is provided with a fourth driving member, the auxiliary lifting member is connected to the fourth driving member, the fourth driving member drives the auxiliary lifting member to reciprocate along the axial direction of the lifting box, the auxiliary lifting member is connected to the lifting box, the lifting action of the auxiliary lifting member can drive the lifting box to move up and down, realize the fixation in the horizontal direction and the separate adjustment in the height direction, and the device has good applicability.

[0022] (4) The utility model has reasonable design, simple structure and good practicality. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0024] Figure 1 A schematic diagram of the structure of a general aviation engine assembly lifting device provided by an embodiment of the utility model;

[0025] Figure 2 A schematic diagram of the internal structure of a general aviation engine assembly lifting device provided by an embodiment of the utility model;

[0026] icon:

[0027] 100. Lifting box;

[0028] 210, support base; 220, support member; 230, threaded rod;

[0029] 300, a first driving member;

[0030] 400, second driving member;

[0031] 500, a third driving member;

[0032] 600, fourth driving member;

[0033] 700. Auxiliary lifting parts. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Generally, the components of the embodiments of the utility model described and shown in the drawings here can be arranged and designed in various different configurations.

[0035] Example

[0036] The embodiment of the present application provides a lifting device for assembling a general aviation engine to achieve high-efficiency adjustment;

[0037] See also Figure 1 as well as Figure 2 , the general aviation engine assembly lifting device provided in the embodiment of the present application includes a lifting box 100, a support assembly, a first driving member 300, a second driving member 400 and a third driving member 500;

[0038] The lifting box 100 is provided with a first accommodating cavity, and the top of the lifting box 100 is not closed to accommodate the aircraft engine components. In some embodiments, the lifting box 100 is cylindrical, and the inner wall is provided with threads;

[0039] The support assembly includes a support base 210 and two support members 220 arranged opposite to each other. The support base 210 is threadedly connected to the inner wall of the lifting box 100. Both support members 220 are provided with sliders. The support base 210 is provided with a slide groove extending along its radial direction. The slider is slidably connected to the slide groove. In some embodiments, the support member 220 is provided with a support groove. In some embodiments, the middle part of the support base 210 is provided with a slide groove. In some embodiments, the slide groove is located in the center of the support base 210.

[0040] The first driving member 300 drives the two supporting members 220 to reciprocate along the extending direction of the slide slot to move closer to or away from each other;

[0041] The second driving member 400 drives the supporting base 210 to rotate along the axial direction of the lifting box 100;

[0042] The third driving member 500 is connected to the second driving member 400 , and drives the second driving member 400 to reciprocate along the axial direction of the lifting box 100 .

[0043] In some embodiments, the two support members 220 are connected by a threaded rod 230, and the two support members 220 are provided with threaded holes with corresponding positions and opposite threads. The threaded rod 230 is connected to the first driving member 300, and the first driving member 300 is a first motor. In some embodiments, the threaded rod 230 is close to the bottom of the two support members 220 and parallel to the support base 210. In some embodiments, the threaded rod 230 extends radially along the support base 210.

[0044] In some embodiments, a driving base is connected to the bottom of the second driving member 400, and the driving base is connected to the third driving member 500. The second driving member 400 is a second motor. In some embodiments, the bottom of the support base 210 is connected to the second motor through a second motor shaft, so that the rotation of the second motor drives the support base 210 to rotate, thereby driving the support member 220 and the aircraft engine components located on the support member 220 to rotate and rise.

[0045] In some embodiments, the third driving member 500 is a telescopic member. In some embodiments, the third driving member 500 is a telescopic cylinder. In some embodiments, the third driving member 500 is a hydraulic cylinder.

[0046] In some embodiments, it also includes an auxiliary lifting member 700 connected to the lifting box 100, the auxiliary lifting member 700 is connected to the fourth driving member 600, the fourth driving member 600 drives the auxiliary lifting member 700 to reciprocate along the axial direction of the lifting box 100, in some embodiments, the auxiliary lifting member 700 is fixedly connected to the lifting box 100, the fourth driving member 600 is a telescopic member, in some embodiments, the fourth driving member 600 is a telescopic cylinder, which is arranged below the auxiliary lifting member 700 to drive the auxiliary lifting member 700 to rise and fall, and in some embodiments, the fourth driving member 600 is a hydraulic cylinder.

[0047] In some embodiments, the auxiliary lifting member 700 and the fourth driving member 600 correspond one to one, and there are multiple groups, which are evenly arranged along the circumference of the lifting box 100. In some embodiments, the auxiliary lifting member 700 and the fourth driving member 600 correspond one to one, and there are 2 groups, which are respectively arranged on both sides of the lifting box 100.

[0048] In some embodiments, the lifting box 100 is further provided with a box support rod, which is a telescopic rod to support the lifting box 100 .

[0049] The lifting process of the general aviation engine assembly lifting device of the present application is described in detail below:

[0050] When in use, the two support members 220 are driven by the first driving member 300 to reciprocate along the extension direction of the slide slot to approach or move away from each other. The aircraft engine components are placed between the two support members 220, and the two support members 220 support the aircraft engine components. The second driving member 400 drives the support base 210 to rotate along the axial direction of the lifting box 100. Since the support base 210 is threadedly connected to the inner wall of the lifting box 100, it can rise or fall along the axial direction of the lifting box 100 during rotation, thereby realizing synchronous adjustment of rotation and lifting. With the telescopic effect of the third driving member 500, the second driving member 400 rises and falls with the support base 210. The auxiliary lifting member 700 can also be driven by the fourth driving member 600 to reciprocate along the axial direction of the lifting box 100. Since the auxiliary lifting member 700 is connected to the lifting box 100, the lifting effect of the auxiliary lifting member 700 can drive the lifting box 100 to rise and fall, thereby realizing fixed horizontal position and separate adjustment in height direction.

[0051] The general aviation engine assembly lifting device of the present application has at least the following advantages:

[0052] (1) The utility model provides a support assembly to support an aircraft engine component. The two support members can be driven by a first drive member to reciprocate along the extension direction of the slide slot to move closer to or farther from each other, thereby adjusting the support orientation of the support assembly to the aircraft engine component.

[0053] (2) The utility model is provided with a second driving member to drive the support base to rotate along the axial direction of the lifting box. Since the support base is threadedly connected to the inner wall of the lifting box, it can rise or fall along the axial direction of the lifting box during rotation, thereby realizing synchronous adjustment of rotation and lifting, and increasing adjustment efficiency.

[0054] (3) The utility model is provided with a fourth driving member, the auxiliary lifting member is connected to the fourth driving member, the fourth driving member drives the auxiliary lifting member to reciprocate along the axial direction of the lifting box, the auxiliary lifting member is connected to the lifting box, the lifting action of the auxiliary lifting member can drive the lifting box to move up and down, realize the fixation in the horizontal direction and the separate adjustment in the height direction, and the device has good applicability.

[0055] (4) The utility model has reasonable design, simple structure and good practicality.

[0056] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may be subject to various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A general aviation engine assembly lifting device, characterized in that: include: A lifting box is provided with a first accommodating cavity, and the top of the lifting box is not closed; A support assembly, comprising a support base and two oppositely arranged support members, wherein the support base is threadedly connected to the inner wall of the lifting box, the two support members are both provided with a slider, the support base is provided with a slide groove extending along its radial direction, and the slider is slidably connected to the slide groove; A first driving member drives the two supporting members to reciprocate along the extending direction of the slide slot to move closer to or farther from each other; A second driving member drives the support base to rotate along the axial direction of the lifting box; The third driving member is connected to the second driving member, and drives the second driving member to reciprocate along the axial direction of the lifting box.

2. The general aviation engine assembly lifting device according to claim 1, characterized in that: The two support members are connected by a threaded rod, and the two support members are provided with threaded holes with corresponding positions and opposite threads. The threaded rod is connected to a first driving member, and the first driving member is a first motor.

3. The general aviation engine assembly lifting device according to claim 1, characterized in that: The bottom of the second driving member is connected to a driving base, the driving base is connected to a third driving member, and the second driving member is a second motor.

4. The general aviation engine assembly lifting device according to any one of claims 1 to 3, characterized in that: The third driving member is a telescopic member.

5. The general aviation engine assembly lifting device according to any one of claims 1 to 3, characterized in that: It also includes an auxiliary lifting member connected to the lifting box, the auxiliary lifting member is connected to a fourth driving member, and the fourth driving member drives the auxiliary lifting member to reciprocate along the axial direction of the lifting box.

6. The general aviation engine assembly lifting device according to claim 5, characterized in that: The auxiliary lifting members correspond to the fourth driving members one by one, and multiple groups are provided and are evenly arranged along the circumference of the lifting box.

7. The general aviation engine assembly lifting device according to any one of claims 1 to 3, characterized in that: The lifting box is also provided with a box body support rod, and the box body support rod is a telescopic rod.

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