CN221088949U - Frock is used in aircraft maintenance - Google Patents

Abstract

The application relates to the technical field of aircraft overhaul, in particular to an aircraft overhaul tooling, which comprises an operation table, wherein the upper surface of the operation table is fixedly connected with a first motor, the output end of the first motor is fixedly connected with a square frame, the left end and the right end of the square frame are both rotationally connected with rotating shafts, one end of the square frame is provided with a second motor, and the opposite ends of the two rotating shafts penetrate through the square frame and are provided with clamping assemblies.

Description

Frock is used in aircraft maintenance

Technical Field

The application relates to the technical field of aircraft overhaul, in particular to a tool for aircraft overhaul.

Background

The aircraft is required to be overhauled before and after being used so as to avoid faults in the use process, and the aircraft is required to be fixed during overhauling, so that the overhauling of people is convenient.

The utility model patent of bulletin number CN216464455U proposes an aircraft maintenance device with protect function, including the maintenance table, the bilateral symmetry of maintenance table has fixture through the support concreties, fixture is located the top of maintenance table, be equipped with the interior cavity on the maintenance table, slide in the interior cavity and be equipped with the bearing cup, connect through the spring between bearing cup and the interior cavity diapire, there is water conservancy diversion hole one in the central lower of bearing cup, the bottom of maintenance table is equipped with water conservancy diversion hole two, water conservancy diversion hole two is located water conservancy diversion hole one under and is close to water conservancy diversion hole one, the bottom of maintenance table can be dismantled and be equipped with the collection box.

The aircraft maintenance device with the protection function cannot conduct angle adjustment when the aircraft is clamped on the clamping mechanism, is inconvenient to overhaul different angles, and causes the problem of reduced working efficiency.

Disclosure of utility model

The utility model aims to solve or at least relieve the problems that the existing aircraft maintenance device with the protection function cannot adjust angles when an aircraft is clamped on a clamping mechanism, and is inconvenient to overhaul at different angles, so that the working efficiency is reduced.

In order to achieve the above purpose, the present utility model adopts the following technical scheme:

The utility model provides an aircraft overhauls uses frock, includes the operation panel, fixed surface is connected with first motor on the operation panel, first motor output fixedly connected with square frame, both ends all rotate about square frame and be connected with the axis of rotation, square frame one of them end is equipped with the second motor, second motor output with one axis of rotation fixed connection, another the axis of rotation is kept away from the one end fixedly connected with rotary valve of second motor, two the opposite one end of axis of rotation all runs through square frame and is equipped with clamping assembly, both ends lateral wall all threaded connection has fixing bolt about square frame, fixing bolt one end all runs through square frame and with axis of rotation looks butt.

Through adopting above technical scheme, during the use, through fixing the aircraft in the clamping assembly, afterwards make square frame drive the aircraft through starting first motor and carry out the horizontal direction rotation, the rethread starts the second motor and makes the axis of rotation drive clamping assembly rotate, carries out the rotation of vertical direction with the aircraft, afterwards can finely adjust the angle of aircraft through manual rotation rotary valve, and the rethread rotates fixing bolt and fixes the axis of rotation, prevents to appear rocking at maintenance in-process aircraft.

Optionally, the clamping assembly includes two connecting plates, the connecting plate all with axis of rotation fixed connection, the relative one end of connecting plate all is equipped with splint, splint with all be equipped with a plurality of springs between the connecting plate, the spring both ends respectively in splint with connecting plate fixed connection.

Through adopting above technical scheme, during the use, separate two splint, put into the aircraft between two splint, rebound through the spring makes two splint be close to each other, carries out the centre gripping with the aircraft of equidimension not fixed.

Optionally, a sliding rod is arranged in the spring, one end of the sliding rod is fixedly connected with the clamping plate, and the other end of the sliding rod penetrates through the connecting plate and forms sliding connection.

Through adopting above technical scheme, can prevent through the slide bar that the spring from receiving gravity influence in the use, lead to the spring to appear crooked unable use.

Optionally, a collecting groove is formed around the first motor on the upper surface of the operating platform.

Through adopting above technical scheme, can collect the part that dismantles in the maintenance in-process through the collecting vat, concentrate and deposit, direct take when facilitating the use.

Optionally, the operation panel upper surface is located the collecting vat outside has seted up annular spout, square frame bottom both sides fixedly connected with support column, support column bottom fixedly connected with universal wheel, the universal wheel is located in the annular spout and form sliding connection.

Through adopting above technical scheme, can support square frame through the support column, avoid the gravity of square frame to concentrate on first motor, can make things convenient for square frame to carry out the horizontal direction rotation through the universal wheel simultaneously.

Optionally, rubber pads are fixedly connected with one side of the two clamping plates opposite to each other and the bottom wall of the collecting tank.

Through adopting above technical scheme, can prevent through having elastic rubber pad that damage and part drop into the collecting vat to the aircraft when two splint are close to each other and appear breaking the problem.

Optionally, an empty slot is formed in the side wall of one side of the operating platform, and the storage box is connected in a sliding manner in the empty slot.

Through adopting above technical scheme, can deposit the instrument that needs when overhauling through the receiver, convenient direct use of taking avoids random mess to put simultaneously, leads to the instrument to lose.

In summary, the beneficial effects of the application are as follows:

1. According to the application, through the cooperation arrangement among the structures such as the first motor, the second motor, the rotating shaft and the like, when the aircraft is used, the aircraft is fixed in the clamping assembly, the first motor and the second motor are started to enable the aircraft to rotate in the horizontal direction and the vertical direction, so that the problems that when the aircraft is clamped on the clamping mechanism, the angle cannot be adjusted, the aircraft is inconvenient to overhaul at different angles, and the working efficiency is reduced are avoided as much as possible;

2. Can deposit the instrument that needs when overhauling through the receiver, convenient direct use of taking avoids random mess to put simultaneously, leads to the instrument to lose.

Drawings

FIG. 1 is a schematic diagram of the overall structure of the present utility model;

FIG. 2 is a schematic view of a clamping assembly according to the present utility model;

fig. 3 is an enlarged view of the area a in fig. 1 according to the present utility model.

Reference numerals illustrate: 1. an operation table; 2. a first motor; 3. a square frame; 4. a rotating shaft; 5. a second motor; 6. a rotary valve; 7. a fixing bolt; 8. a connecting plate; 9. a clamping plate; 10. a spring; 11. a slide bar; 12. a collection tank; 13. an annular chute; 14. a support column; 15. a universal wheel; 16. a rubber pad; 17. a hollow groove; 18. and a storage box.

Detailed Description

The application is described in further detail below with reference to fig. 1-3.

Referring to fig. 1-3, an aircraft overhauling tool comprises an operation table 1, wherein a first motor 2 for providing power is fixedly connected to the upper surface of the operation table 1, the output end of the first motor 2 is fixedly connected with a square frame 3, the left end and the right end of the square frame 3 are respectively connected with a rotating shaft 4 in a rotating mode, one end of the square frame 3 is provided with a second motor 5 for providing power, the output end of the second motor 5 is fixedly connected with one rotating shaft 4, one end of the other rotating shaft 4, far away from the second motor 5, is fixedly connected with a rotating valve 6 for manually controlling the rotating shaft 4 to rotate, opposite ends of the two rotating shafts 4 respectively penetrate through the square frame 3 and are provided with clamping assemblies for clamping and fixing an aircraft, side walls of the left end and the right end of the square frame 3 are respectively connected with fixing bolts 7 in a threaded mode, one end of each fixing bolt 7 respectively penetrates through the square frame 3 and is abutted against the rotating shaft 4, and the rotating shaft 4 are used for fixing the rotating shaft 4 and the square frame 3, and preventing the rotating shaft 4 from rotating.

During the use, through fixing the aircraft in clamping assembly, afterwards, make square frame 3 drive the aircraft through start first motor 2 and carry out the horizontal direction and rotate, rethread starts second motor 5 and makes axis of rotation 4 drive clamping assembly and rotate, carry out the rotation of vertical direction with the aircraft, afterwards, can finely adjust the angle of aircraft through manual rotation rotary valve 6, rethread rotates fixing bolt 7 and fixes axis of rotation 4, prevent to appear rocking at maintenance in-process aircraft, avoided as far as possible, when centre gripping the aircraft on clamping mechanism, can't carry out angle adjustment, inconvenient maintenance to different angles, the problem that has led to reducing work efficiency.

Referring to fig. 2, the clamping assembly includes two connecting plates 8, connecting plate 8 all with axis of rotation 4 fixed connection, the relative one end of connecting plate 8 all is equipped with splint 9, all is equipped with a plurality of springs 10 between splint 9 and the connecting plate 8, and spring 10 both ends are respectively in splint 9 and connecting plate 8 fixed connection, and during the use, separate two splint 9, put into the aircraft between two splint 9, rebound through spring 10 makes two splint 9 be close to each other, carries out the centre gripping with the aircraft of equidimension not fixed.

Referring to fig. 2, the springs 10 are provided with slide bars 11, one ends of the slide bars 11 are fixedly connected with the clamping plates 9, the other ends of the slide bars 11 penetrate through the connecting plates 8 and form sliding connection, and the springs 10 can be prevented from being affected by gravity in the use process through the slide bars 11, so that the springs 10 are bent and cannot be used.

Referring to fig. 1, a collecting groove 12 is formed around the first motor 2 on the upper surface of the operation table 1, and parts detached in the overhaul process can be collected and stored in a concentrated mode through the collecting groove 12, so that the operation table is convenient to use and take directly.

Referring to fig. 1 and 3, annular chute 13 has been seted up to operation panel 1 upper surface in the collecting vat 12 outside, square frame 3 bottom both sides fixedly connected with support column 14, support column 14 bottom fixedly connected with universal wheel 15, universal wheel 15 is located annular chute 13 and forms sliding connection, can support square frame 3 through support column 14, avoid the gravity of square frame 3 to concentrate on first motor 2, can make things convenient for square frame 3 to carry out the horizontal direction rotation through universal wheel 15 simultaneously.

Referring to fig. 1 and 2, rubber pads 16 are fixedly connected to opposite sides of the two clamping plates 9 and the bottom wall of the collecting tank 12, and damage to the aircraft and damage to parts falling into the collecting tank 12 caused by the two clamping plates 9 approaching each other can be prevented by the elastic rubber pads 16.

Referring to fig. 1, an empty slot 17 is formed in a side wall of one side of the operation platform 1, a storage box 18 is slidably connected in the empty slot 17, tools required during maintenance can be stored through the storage box 18, the tools can be conveniently and directly taken and used, and meanwhile, the tools are prevented from being randomly placed, so that the tools are lost.

The implementation principle of the application is as follows: during the use, through fixing the aircraft in clamping assembly, afterwards, make square frame 3 drive the aircraft through start first motor 2 and carry out the horizontal direction and rotate, rethread starts second motor 5 and makes axis of rotation 4 drive clamping assembly and rotate, carry out the rotation of vertical direction with the aircraft, afterwards, can finely adjust the angle of aircraft through manual rotation rotary valve 6, rethread rotates fixing bolt 7 and fixes axis of rotation 4, prevent to appear rocking at maintenance in-process aircraft, avoided as far as possible, when centre gripping the aircraft on clamping mechanism, can't carry out angle adjustment, inconvenient maintenance to different angles, the problem that has led to reducing work efficiency.

The foregoing description is only a preferred embodiment of the present utility model, and the present utility model is not limited thereto, but it is to be understood that modifications and equivalents of some of the technical features described in the foregoing embodiments may be made by those skilled in the art, although the present utility model has been described in detail with reference to the foregoing embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.

Claims (7)

1. Aircraft overhauls uses frock, including operation panel (1), its characterized in that: the utility model discloses a control cabinet, including square frame (3), control cabinet (1) upper surface fixedly connected with first motor (2), first motor (2) output fixedly connected with square frame (3), both ends all rotate and are connected with axis of rotation (4) about square frame (3), square frame (3) one end is equipped with second motor (5), second motor (5) output with one axis of rotation (4) fixed connection, another axis of rotation (4) are kept away from one end fixedly connected with rotary valve (6) of second motor (5), two the opposite one end of axis of rotation (4) all runs through square frame (3) and is equipped with clamping assembly, both ends lateral wall all threaded connection has fixing bolt (7) about square frame (3), fixing bolt (7) one end all run through square frame (3) and with axis of rotation (4) looks butt.

2. The tooling for overhauling an aircraft according to claim 1, wherein: the clamping assembly comprises two connecting plates (8), wherein the connecting plates (8) are fixedly connected with the rotating shaft (4), clamping plates (9) are arranged at opposite ends of the connecting plates (8), a plurality of springs (10) are arranged between the clamping plates (9) and the connecting plates (8), and two ends of each spring (10) are fixedly connected with the corresponding clamping plate (9) and the corresponding connecting plate (8).

3. The tooling for overhauling an aircraft according to claim 2, wherein: the spring (10) is internally provided with a sliding rod (11), one end of the sliding rod (11) is fixedly connected with the clamping plate (9), and the other end of the sliding rod (11) penetrates through the connecting plate (8) and forms sliding connection.

4. A tooling for aircraft service according to claim 3, wherein: the upper surface of the operating platform (1) is positioned around the first motor (2) and is provided with a collecting groove (12).

5. The tooling for overhauling an aircraft of claim 4, wherein: the operation panel (1) upper surface is located annular spout (13) have been seted up in collecting vat (12) outside, square frame (3) bottom both sides fixedly connected with support column (14), support column (14) bottom fixedly connected with universal wheel (15), universal wheel (15) are located annular spout (13) are interior and form sliding connection.

6. The tooling for overhauling an aircraft of claim 5, wherein: rubber pads (16) are fixedly connected to the opposite sides of the two clamping plates (9) and the bottom wall of the collecting tank (12).

7. The tooling for overhauling an aircraft according to claim 1, wherein: an empty groove (17) is formed in one side wall of the operating platform (1), and a storage box (18) is connected in the empty groove (17) in a sliding mode.