CN219790530U - Aircraft ventral fin assembly type frame - Google Patents

Abstract

The utility model discloses an aircraft ventral fin assembly type frame, which belongs to the technical field of aircraft components and comprises a bottom plate, wherein the top of the bottom plate is fixedly connected with a support frame, and a double-shaft motor is arranged in the support frame.

Description

Aircraft ventral fin assembly type frame

Technical Field

The utility model relates to the technical field of aircraft parts, in particular to an aircraft ventral fin assembly type frame.

Background

The aircraft ventral fin is the sword form fin that sets up along the air current direction under the aircraft fuselage tail, and the ventral fin also is called the sagging tail, is located the fuselage afterbody, and the position that corresponds of sagging tail below is very important structure, in order to ensure the assembly effect of aircraft ventral fin, consequently needs an auxiliary frame.

However, most of the conventional auxiliary frames cannot be adjusted according to the length of the ventral fin of the aircraft, and meanwhile, the problem of poor assembly stability and flexibility exists.

Disclosure of Invention

First, the technical problem to be solved

Aiming at the defects in the prior art, the utility model aims to provide the aircraft ventral fin assembly type frame which has the characteristics of being capable of being adjusted according to the length of the aircraft ventral fin and guaranteeing the assembly stability and flexibility.

(II) technical scheme

In order to achieve the above purpose, the utility model provides an aircraft ventral fin assembly type frame, which comprises a bottom plate, wherein the top of the bottom plate is fixedly connected with a support frame, a double-shaft motor is arranged in the support frame, two output shafts of the double-shaft motor are fixedly connected with threaded rods, one end of each threaded rod is fixedly connected with a first rotating shaft, the first rotating shafts are sleeved on the inner side of the support frame through bearings A, the surface of each threaded rod is in threaded connection with a first threaded sleeve, the top of each first threaded sleeve is fixedly connected with an adjusting block, an electric push rod is arranged in each adjusting block, the top of each electric push rod is provided with a mounting frame, the inner side of each mounting frame is fixedly connected with a second threaded sleeve, the inner threads of each second threaded sleeve are connected with bolts, one end of each bolt is fixedly connected with a second rotating shaft, the top of each support frame is provided with a placing plate through a limiting plate in a sleeved mode through bearings B, the bottom of each bottom plate is fixedly connected with four universal wheels.

When using an aircraft ventral fin assembly type frame of this technical scheme, work through biax motor, can drive the threaded rod and rotate, thereby drive first thread bush, adjusting block and mounting bracket and remove, can adjust the position of device according to aircraft ventral fin length, conveniently overlap joint restriction to aircraft ventral fin, work respectively through two electric putter, can drive mounting bracket and aircraft ventral fin and go up and down, thereby realize adjusting aircraft ventral fin's height and angle, make things convenient for follow-up assembly treatment, through the rotation bolt, with the help of second thread bush, can drive the bolt, second pivot and limiting plate remove, can carry out the centre gripping to aircraft ventral fin and fix, the stability of aircraft ventral fin when guaranteeing the assembly, through setting up the universal wheel, the convenience is adjusted the position of device, can operate aircraft ventral fin, the convenience is assembled the aircraft ventral fin simultaneously.

Further, a first sliding groove is formed in the support frame, a first sliding block is connected to the first sliding groove in a sliding mode, and the first sliding block is fixedly connected to the bottom of the first thread bush.

Further, a supporting sleeve is arranged inside the supporting frame, and the output shaft of the double-shaft motor is sleeved inside the supporting sleeve.

Further, the second spout has been seted up to the inside second spout that has seted up of adjusting block, sliding connection has the second slider in the second spout, second slider top fixedly connected with head rod, head rod top fixedly connected with is in the mounting bracket bottom, the inboard fixedly connected with first adapter sleeve of adjusting block, the head rod cup joints inside first adapter sleeve.

Further, the inside fixedly connected with second adapter sleeve of mounting bracket, the second connecting rod has been cup jointed in the second adapter sleeve, second connecting rod one end fixed connection is in limiting plate one side.

Further, a control panel is arranged on one side of the support frame, and the control panel is electrically connected with the double-shaft motor and the electric push rod through wires.

(III) beneficial effects

In summary, the utility model has the following beneficial effects:

1. through biax motor work, can drive the threaded rod and rotate, thereby drive first thread bush, adjusting block and mounting bracket and remove, can adjust the position of device according to aircraft ventral fin length, conveniently overlap joint restriction to aircraft ventral fin, work respectively through two electric putter, can drive mounting bracket and aircraft ventral fin and go up and down, thereby realize adjusting aircraft ventral fin's height and angle, make things convenient for follow-up assembly processing, through the rotation bolt, with the help of the second thread bush, can drive the bolt, second pivot and limiting plate remove, can carry out the centre gripping fixed to aircraft ventral fin, stability to aircraft ventral fin when guaranteeing the assembly, through setting up the universal wheel, conveniently adjust the position of device, can operate aircraft ventral fin, the while is convenient to assemble processing to aircraft ventral fin;

2. the stability of the first thread sleeve in moving can be ensured by arranging the first sliding groove and the first sliding block, and the output shaft of the double-shaft motor can be limited by arranging the supporting sleeve, so that the stability of the double-shaft motor in use is ensured;

3. through setting up second spout and second slider, can ensure the stability of head rod and mounting bracket when the lift removes, through setting up head rod and first adapter sleeve, can further ensure the stability of mounting bracket when the lift removes, through setting up second adapter sleeve and second connecting rod, can ensure the stability of stopper when removing, with the help of setting up control panel, can control the electrical components of device to the convenience is controlled the device.

Drawings

In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings required for the description of the embodiments or the prior art will be briefly described, and it is apparent that the drawings in the following description are only one embodiment of the present utility model, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic cross-sectional elevation view of the present utility model;

FIG. 2 is a schematic elevational view of the present utility model;

fig. 3 is a schematic top view of the present utility model.

The marks in the drawings are:

1. a universal wheel; 2. a bottom plate; 3. a first chute; 4. a first slider; 5. a first rotating shaft; 6. a threaded rod; 7. a first threaded sleeve; 8. a second chute; 9. a second slider; 10. a first connecting rod; 11. an electric push rod; 12. a first connection sleeve; 13. a mounting frame; 14. a limiting plate; 15. placing a plate; 16. a support sleeve; 17. a biaxial motor; 18. a control panel; 19. a support frame; 20. adjusting the block; 21. a bolt; 22. a second threaded sleeve; 23. a second rotating shaft; 24. a second connecting sleeve; 25. and a second connecting rod.

Detailed Description

In order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the present utility model easy to understand, the technical solutions in the embodiments of the present utility model are clearly and completely described below to further illustrate the present utility model, and it is obvious that the described embodiments are only some embodiments of the present utility model, not all versions.

Examples:

the utility model is described in further detail below with reference to fig. 1-3.

Referring to fig. 1-3, the present utility model provides a technical solution: the utility model provides an aircraft ventral fin assembly type frame, including bottom plate 2, bottom plate 2 top fixedly connected with support frame 19, the inside biax motor 17 that is provided with of support frame 19, work through biax motor 17, can drive threaded rod 6 and rotate, thereby drive first thread bush 7, adjusting block 20 and mounting bracket 13 remove, can adjust the position of device according to aircraft ventral fin length, conveniently overlap joint restriction to aircraft ventral fin, biax motor 17 two output shaft fixedly connected with threaded rod 6, threaded rod 6 one end fixedly connected with first pivot 5, first pivot 5 cup joints in support frame 19 inboard through bearing A, threaded rod 6 surface threaded connection has first thread bush 7, first thread bush 7 top fixedly connected with adjusting block 20, adjusting block 20 inside is provided with electric putter 11, work respectively through two electric putter 11, can drive mounting bracket 13 and aircraft ventral fin and go up and down, thereby realizing the adjustment of the height and angle of the aircraft ventral fin, the subsequent assembly treatment is convenient, the top end of the electric push rod 11 is provided with the mounting frame 13, the inner side of the mounting frame 13 is fixedly connected with the second thread bush 22, the inner thread of the second thread bush 22 is connected with the bolt 21, the second rotating shaft 23 and the limiting plate 14 can be driven to move by rotating the bolt 21 through the second thread bush 22, the aircraft ventral fin can be clamped and fixed, the stability of the aircraft ventral fin during the assembly is ensured, one end of the bolt 21 is fixedly connected with the second rotating shaft 23, the limiting plate 14 is sleeved on the second rotating shaft 23 through the bearing B, the top of the supporting frame 19 is provided with the placing plate 15, the bottom of the bottom plate 2 is fixedly connected with the universal wheel 1, the position of the device is conveniently adjusted through the universal wheel 1, the operation of the aircraft ventral fin can be conveniently carried out, the assembly treatment is conveniently carried out on the aircraft ventral fin at the same time, the number of universal wheels 1 is four.

Specifically, the first chute 3 is arranged in the support frame 19, the first slide block 4 is connected in the first chute 3 in a sliding way, the first slide block 4 is fixedly connected to the bottom of the first thread bush 7, the support sleeve 16 is arranged in the support frame 19, and the output shaft of the double-shaft motor 17 is sleeved in the support sleeve 16.

Through adopting above-mentioned technical scheme, through setting up first spout 3 and first slider 4, can ensure the stability of first thread bush 7 when removing, through setting up support sleeve 16, can restrict biax motor 17 output shaft, ensure the stability of biax motor 17 when using.

Specifically, the second spout 8 has been seted up to the inside of adjusting block 20, sliding connection has second slider 9 in second spout 8, second slider 9 top fixedly connected with head rod 10, head rod 10 top fixed connection is in mounting bracket 13 bottom, the inboard fixedly connected with first adapter sleeve 12 of adjusting block 20, head rod 10 cup joints inside first adapter sleeve 12, the inside fixedly connected with second adapter sleeve 24 of mounting bracket 13, second connecting rod 25 has been cup jointed in the second adapter sleeve 24, second connecting rod 25 one end fixed connection is in limiting plate 14 one side.

Through adopting above-mentioned technical scheme, through setting up second spout 8 and second slider 9, can ensure the stability of head rod 10 and mounting bracket 13 when the lift removes, through setting up head rod 10 and first adapter sleeve 12, can further ensure the stability of mounting bracket 13 when the lift removes, through setting up second adapter sleeve 24 and second connecting rod 25, can ensure the stability of stopper when removing.

Specifically, a control panel 18 is disposed on one side of the support frame 19, and the control panel 18 is electrically connected with the biaxial motor 17 and the electric push rod 11 through wires.

By adopting the above technical scheme, by means of the control panel 18, the electrical components of the device can be controlled, thereby facilitating the control of the device.

The working principle of the utility model is as follows:

when the aircraft ventral fin is assembled, the double-shaft motor 17 can be controlled to work according to the length of the aircraft ventral fin, the threaded rod 6 is driven to rotate, the first threaded sleeve 7, the adjusting block 20 and the mounting frame 13 are driven to move, the distance between the two mounting frames 13 is adjusted and controlled, after the position of the two mounting frames 13 is controlled, the aircraft ventral fin is placed inside the mounting frames 13, the electric push rod 11 is controlled to work according to the assembly height and the angle, the mounting frames 13 and the aircraft ventral fin are driven to be adjusted and controlled, and finally the aircraft ventral fin and the device are pushed to move to the assembly position, so that the aircraft ventral fin is assembled.

The present embodiment is only for explanation of the present utility model and is not to be construed as limiting the present utility model, and modifications to the present embodiment, which may not creatively contribute to the present utility model as required by those skilled in the art after reading the present specification, are all protected by patent laws within the scope of claims of the present utility model.

Claims (6)

1. Aircraft ventral fin assembly jig, including bottom plate (2), its characterized in that: the novel double-shaft motor is characterized in that a support frame (19) is fixedly connected to the top of the bottom plate (2), a double-shaft motor (17) is arranged inside the support frame (19), a threaded rod (6) is fixedly connected to two output shafts of the double-shaft motor (17), a first rotating shaft (5) is fixedly connected to one end of the threaded rod (6), the first rotating shaft (5) is sleeved on the inner side of the support frame (19) through a bearing A, a first thread bush (7) is connected to the surface of the threaded rod (6) in a threaded manner, and an adjusting block (20) is fixedly connected to the top of the first thread bush (7);

the utility model discloses a motor-assisted bicycle is characterized in that an adjusting block (20) is internally provided with an electric push rod (11), an installing frame (13) is arranged at the top end of the electric push rod (11), a second thread bush (22) is fixedly connected to the inner side of the installing frame (13), a bolt (21) is connected to the inner thread of the second thread bush (22), a second rotating shaft (23) is fixedly connected to one end of the bolt (21), a limiting plate (14) is sleeved on the second rotating shaft (23) through a bearing B, a placing plate (15) is arranged at the top of the supporting frame (19), universal wheels (1) are fixedly connected to the bottom of the bottom plate (2), and the number of the universal wheels (1) is four.

2. An aircraft ventral fin mounting bracket according to claim 1, wherein: the support frame (19) is internally provided with a first sliding groove (3), a first sliding block (4) is connected in the first sliding groove (3) in a sliding mode, and the first sliding block (4) is fixedly connected to the bottom of the first thread bush (7).

3. An aircraft ventral fin mounting bracket according to claim 1, wherein: the support frame (19) is internally provided with a support sleeve (16), and the output shaft of the double-shaft motor (17) is sleeved in the support sleeve (16).

4. An aircraft ventral fin mounting bracket according to claim 1, wherein: the adjusting block (20) is internally provided with a second sliding groove (8), a second sliding block (9) is connected in the second sliding groove (8) in a sliding mode, a first connecting rod (10) is fixedly connected to the top of the second sliding block (9), the top of the first connecting rod (10) is fixedly connected to the bottom of the mounting frame (13), a first connecting sleeve (12) is fixedly connected to the inner side of the adjusting block (20), and the first connecting rod (10) is sleeved inside the first connecting sleeve (12).

5. An aircraft ventral fin mounting bracket according to claim 1, wherein: the mounting frame (13) is internally fixedly connected with a second connecting sleeve (24), a second connecting rod (25) is sleeved in the second connecting sleeve (24), and one end of the second connecting rod (25) is fixedly connected to one side of the limiting plate (14).

6. An aircraft ventral fin mounting bracket according to claim 1, wherein: one side of the supporting frame (19) is provided with an operation panel (18), and the operation panel (18) is electrically connected with the double-shaft motor (17) and the electric push rod (11) through wires.