Lifting device for assembling wing spar of aircraft

Abstract

The utility model discloses a hoisting device for assembling an aircraft spar, which comprises a hoisting bracket, a first electric push rod is arranged on the hoisting bracket, a first telescopic arm is arranged below the first electric push rod, the lower end of the first telescopic arm is respectively provided with a fixed rod, and the lower end surface of the fixed rod is provided with a plurality of groups of hoisting ropes. According to the lifting device for assembling the aircraft spar, a fixing frame and a lifting support form a vertical lifting structure through a second telescopic arm under the action of a second electric push rod, and a connecting rod and the fixing frame form a bidirectional limiting sliding structure through a bidirectional screw rod, a sliding rod and a movable block under the action of a first servo motor; the two ends of the spar are supported through the lifting bearing plate, then double assurance is conducted on the spar in the moving process, a protective cover of the device and the bearing plate form a rotating structure through a rotating shaft under the action of a second servo motor, and therefore the two ends of the spar are protected through the protective cover; and the two ends of the wing spar are limited through the protective cover.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft wing spar assembly, in particular to a lifting device for aircraft wing spar assembly. Background Art

[0002] The aircraft wing spar is one of the aircraft components. Its main function is to bear the bending moment and shear force of the wing and transfer it to other parts of the aircraft, such as the fuselage and landing gear. The wing spar is the longitudinal member in the wing surface that mainly bears the bending moment and shear force. It is composed of upper and lower edge strips and webs. The upper and lower edge strips bear the bending moment load in tension and compression, while the webs transfer the tangential load in shear. During the assembly of the aircraft, in order to move the wing spar assembly to the appropriate position for assembly, a lifting device is used to drive the wing spar to move.

[0003] During use, the lifting device places the wing spar on the lifting assembly through a hook, and moves it to a suitable position for assembly through the lifting assembly. However, during use, the existing lifting device cannot ensure the safety of the wing spar during movement through a single lifting assembly, and cannot guarantee the stability of the wing spar during movement. Therefore, a lifting device for assembling an aircraft wing spar is proposed to solve the above problems. Utility Model Content

[0004] The purpose of the utility model is to provide a lifting device for assembling an aircraft wing beam, so as to solve the problem that the existing lifting device proposed in the above-mentioned background technology cannot ensure the safety of the wing beam during movement through a single lifting component during use, and cannot ensure the stability of the wing beam during movement.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a lifting device for assembling an aircraft wing beam, comprising a lifting bracket, the lifting bracket is provided with a first electric push rod, and the first electric push rod is provided with a first telescopic arm below, the lower ends of the first telescopic arms are respectively provided with fixing rods, and the lower end surfaces of the fixing rods are provided with multiple sets of lifting ropes, the other ends of the lifting ropes are provided with hooks, and a wing beam is placed between the hooks, the first electric push rod is respectively provided with a second electric push rod at both ends, and the second electric push rod is respectively provided with a second telescopic arm, the other end of the second telescopic arm is connected to a fixing frame, and the fixing frame is provided with a first servo motor inside, one end of the output shaft of the first servo motor is connected to a bidirectional screw through a coupling, and the bidirectional screw is correspondingly provided with a sliding rod below, movable blocks are respectively inserted at both ends of the bidirectional screw and the sliding rod, and connecting rods are respectively provided on both sides of the movable block, and a supporting plate is provided at the other end of the connecting rod;

[0006] A second servo motor is provided at one end of the upper end surface of the support plate, and one end of the output shaft of the second servo motor is connected to the rotating shaft through a coupling, and a protective cover is provided on the outer wall of the rotating shaft;

[0007] The protective cover is provided with a third electric push rod on the upper end surface, and the third electric push rod is provided with a third telescopic arm, the other end of the third telescopic arm is provided with a limit plate, and the lower end surface of the limit plate is provided with a soft rubber pad.

[0008] Preferably, the fixing rod forms a vertical lifting structure through the first telescopic arm and the lifting bracket under the action of the first electric push rod, and the lifting rope forms a locking and limiting structure through the hook and the wing beam.

[0009] Preferably, the fixed frame forms a vertical lifting structure through the second telescopic arm and the lifting bracket under the action of the second electric push rod, and the connecting rod forms a bidirectional limited sliding structure with the fixed frame through the bidirectional screw, sliding rod, movable block under the action of the first servo motor.

[0010] Preferably, the protective cover forms a rotating structure with the supporting plate through the rotating shaft under the action of the second servo motor.

[0011] Preferably, the limit plate forms a vertical lifting structure through the third telescopic arm and the protective cover under the action of the third electric push rod.

[0012] Compared with the prior art, the beneficial effects of the utility model are as follows: the fixed frame of the lifting device for assembling the aircraft wing beam forms a vertical lifting structure through the second telescopic arm and the lifting bracket under the action of the second electric push rod, and the connecting rod forms a two-way limited sliding structure with the fixed frame through the two-way screw, the sliding rod, the movable block under the action of the first servo motor, so that the two ends of the wing beam are supported by the lifting support plate, thereby doubly ensuring the wing beam during the moving process, and the protective cover of the device forms a rotating structure through the rotating shaft and the supporting plate under the action of the second servo motor, so that the two ends of the wing beam are protected by the protective cover, and the two ends of the wing beam are limited by the protective cover, and the limit plate of the device forms a vertical lifting joint through the third telescopic arm and the protective cover under the action of the third electric push rod, thereby increasing the stability of the wing beam during the moving process through the lifting limit plate. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a side structural schematic diagram of a lifting rope assembly of a lifting device for assembling an aircraft wing spar according to the utility model;

[0014] Figure 2 This is a side structural schematic diagram of a support plate moving assembly of a lifting device for assembling an aircraft wing spar according to the utility model;

[0015] Figure 3 This is a schematic diagram of the structure of a supporting plate moving assembly of a lifting device for assembling an aircraft wing beam according to the utility model;

[0016] Figure 4This is a schematic diagram of the structure of a lifting rope assembly of a lifting device for assembling an aircraft wing spar according to the utility model;

[0017] Figure 5 The utility model is a schematic structural diagram of a protective cover assembly of a lifting device for assembling an aircraft wing beam.

[0018] In the figure: 1. lifting bracket, 2. first electric push rod, 3. first telescopic arm, 4. fixing rod, 5. lifting rope, 6. wing beam, 7. second electric push rod, 8. second telescopic arm, 9. fixing frame, 10. first servo motor, 11. bidirectional screw, 12. sliding rod, 13. movable block, 14. connecting rod, 15. supporting plate, 16. second servo motor, 17. rotating shaft, 18. protective cover, 19. third electric push rod, 20. third telescopic arm, 21. limiting plate. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0020] See also Figure 1-5 The utility model provides a technical solution: a lifting device for assembling an aircraft wing beam, comprising a lifting bracket 1, a first electric push rod 2 is provided on the lifting bracket 1, and a first telescopic arm 3 is provided below the first electric push rod 2, a fixing rod 4 is provided at the lower end of the first telescopic arm 3, and a plurality of lifting ropes 5 are provided on the lower end surface of the fixing rod 4, a hook is provided at the other end of the lifting rope 5, and a wing beam 6 is placed between the hooks.

[0021] Furthermore, under the action of the first electric push rod 2, the fixed rod 4 forms a vertical lifting structure with the lifting bracket 1 through the first telescopic arm 3, and the lifting rope 5 forms a locking limit structure with the wing beam 6 through the hook, so that the wing beam 6 is lifted by the lifting lifting rope 5 and drives the wing beam 6 to move.

[0022] The first electric push rod 2 is provided with a second electric push rod 7 at both ends, and the second electric push rod 7 is provided with a second telescopic arm 8, the other end of the second telescopic arm 8 is connected to a fixing frame 9, and the fixing frame 9 is provided with a first servo motor 10 inside, one end of the output shaft of the first servo motor 10 is connected to a bidirectional screw 11 through a coupling, and the bidirectional screw 11 is provided with a sliding rod 12 at the bottom, and the bidirectional screw 11 and the sliding rod 12 are respectively inserted with movable blocks 13 at both ends, and the movable block 13 is provided with connecting rods 14 on both sides, and the other end of the connecting rod 14 is provided with a supporting plate 15.

[0023] Furthermore, the fixed frame 9, under the action of the second electric push rod 7, forms a vertical lifting structure with the lifting bracket 1 through the second telescopic arm 8, and the connecting rod 14, under the action of the first servo motor 10, forms a two-way limited sliding structure with the fixed frame 9 through the two-way screw 11, the slide rod 12, the movable block 13, so that the supporting plate 15 is moved to the bottom of the wing beam 6 through the connecting rod 14 with two-way limited movement, so that the two ends of the wing beam 6 can be supported by the supporting plate 15, thereby providing doubly protection for the wing beam 6 during the lifting process.

[0024] A second servo motor 16 is disposed at one end of the upper end surface of the supporting plate 15 , and one end of the output shaft of the second servo motor 16 is connected to a rotating shaft 17 via a coupling. A protective cover 18 is disposed on the outer wall of the rotating shaft 17 .

[0025] Furthermore, under the action of the second servo motor 16 , the protective cover 18 forms a rotating structure with the supporting plate 15 through the rotating shaft 17 , so that the rotating protective cover 18 protects both ends of the wing beam 6 while limiting the position of the wing beam 6 .

[0026] The protective cover 18 is provided with a third electric push rod 19 on the upper end surface, and a third telescopic arm 20 is provided on the third electric push rod 19 . A limit plate 21 is provided at the other end of the third telescopic arm 20 , and a soft rubber pad is provided on the lower end surface of the limit plate 21 .

[0027] Furthermore, under the action of the third electric push rod 19, the limit plate 21 forms a vertical lifting structure through the third telescopic arm 20 and the protective cover 18, so that under the action of the third electric push rod 19, the wing beam 6 is squeezed and limited by the limit plate 21, thereby increasing the stability of the wing beam 6 during the movement.

[0028] Working principle: When using the lifting device for assembling the aircraft wing beam, first drive the lifting rope 5 to descend through the first electric push rod 2, so that the hook is installed on the wing beam 6. When the hook is installed, the first electric push rod 2 can drive the wing beam 6 to rise. When the wing beam 6 rises a distance, the second electric push rod 7 can be started. The second electric push rod 7 drives the fixing frame 9 to descend through the second telescopic arm 8, so that the support plate 15 is located at both ends of the wing beam 6. Then the first servo motor 10 can be started. The output shaft of the first servo motor 10 drives the bidirectional screw 11 to rotate through the coupling, and drives the support plate 15 to slide in a bidirectional limited manner through the slide bar 12, the movable block 13, and the connecting rod 14, so as to pass the support plate 15 on the wing beam 6. The two ends of the wing beam 6 are supported, so that the lifting process of the wing beam 6 is doubly protected by the supporting plate 15; when the supporting plate 15 is moved, the second servo motor 16 can be started, and the output shaft of the second servo motor 16 drives the rotating shaft 17 to rotate through the coupling, thereby driving the protective cover 18 to rotate, so that the two ends of the wing beam 6 can be protected by the protective cover 18, and the wing beam 6 can be limited by the protective cover 18 at the same time; then the third electric push rod 19 can be started, so as to drive the limiting plate 21 to descend through the third telescopic arm 20, so that the wing beam 6 can be squeezed and limited by the soft rubber pad on the limiting plate 21, thereby ensuring the stability of the wing beam 6 during the lifting and moving process. This is the use process of the lifting device for assembling the aircraft wing beam.

[0029] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art may still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

Claims

1. A lifting device for assembling an aircraft wing spar, comprising a lifting bracket (1), characterized in that: The lifting bracket (1) is provided with a first electric push rod (2), and the first electric push rod (2) is provided with a first telescopic arm (3) at the bottom, the lower ends of the first telescopic arms (3) are respectively provided with fixing rods (4), and the lower end surfaces of the fixing rods (4) are provided with a plurality of lifting ropes (5), the other ends of the lifting ropes (5) are provided with hooks, and wing beams (6) are placed between the hooks, the first electric push rod (2) is respectively provided with second electric push rods (7) at both ends, and the second electric push rods (7) are respectively provided with second telescopic arms (8), and the second The other end of the telescopic arm (8) is connected to a fixed frame (9), and a first servo motor (10) is provided inside the fixed frame (9), one end of an output shaft of the first servo motor (10) is connected to a bidirectional screw rod (11) via a coupling, and a sliding rod (12) is provided below the bidirectional screw rod (11), respectively, movable blocks (13) are inserted at both ends of the bidirectional screw rod (11) and the sliding rod (12), and connecting rods (14) are provided on both sides of the movable block (13), and a supporting plate (15) is provided at the other end of the connecting rod (14); A second servo motor (16) is provided at one end of the upper end surface of the support plate (15), and one end of the output shaft of the second servo motor (16) is connected to a rotating shaft (17) via a coupling, and a protective cover (18) is provided on the outer wall of the rotating shaft (17); The protective cover (18) is provided with a third electric push rod (19) on the upper end surface, and the third electric push rod (19) is provided with a third telescopic arm (20), the other end of the third telescopic arm (20) is provided with a limit plate (21), and the lower end surface of the limit plate (21) is provided with a soft rubber pad.

2. A lifting device for assembling an aircraft wing spar according to claim 1, characterized in that: The fixing rod (4) forms a vertical lifting structure with the lifting bracket (1) through the first telescopic arm (3) under the action of the first electric push rod (2), and the lifting rope (5) forms a locking limit structure with the wing beam (6) through the hook.

3. The lifting device for assembling an aircraft wing spar according to claim 1, characterized in that: The fixed frame (9) forms a vertical lifting structure through the second telescopic arm (8) and the lifting bracket (1) under the action of the second electric push rod (7), and the connecting rod (14) forms a bidirectional limited sliding structure through the bidirectional screw rod (11), the sliding rod (12), the movable block (13) and the fixed frame (9) under the action of the first servo motor (10).

4. The lifting device for assembling an aircraft wing spar according to claim 1, characterized in that: The protective cover (18) forms a rotating structure with the supporting plate (15) through the rotating shaft (17) under the action of the second servo motor (16).

5. The lifting device for assembling an aircraft wing spar according to claim 1, characterized in that: The limiting plate (21) forms a vertical lifting structure through the third telescopic arm (20) and the protective cover (18) under the action of the third electric push rod (19).

Images