CN218503382U

CN218503382U - Outer cylinder bushing clamp for main frame of undercarriage

Info

Publication number: CN218503382U
Application number: CN202221939127.6U
Authority: CN
Inventors: 谭兴昆; 李汝忠; 李金劲; 温志发; 刘志鹏; 黄灿荣; 梅霄; 胡骁
Original assignee: Guangzhou Aircraft Maintenance Engineering Co Ltd
Current assignee: Guangzhou Aircraft Maintenance Engineering Co Ltd
Priority date: 2022-07-26
Filing date: 2022-07-26
Publication date: 2023-02-21
Anticipated expiration: 2032-07-26

Abstract

The utility model discloses an aircraft undercarriage body frame urceolus bush anchor clamps, including chuck and a plurality of jack catchs of setting on the chuck, a plurality of jack catchs use the chuck central point to be outside radial evenly distributed as the center, equal fixed mounting has an install bin on each jack catch, establish the power in every install bin, all be provided with fixture on every install bin, through the bush body of the fixed bush of fixture centre gripping, still be provided with on every install bin that centre gripping bush body process is used for pressure identification in order to prevent the not enough first identification mechanism of centre gripping dynamics and in order to prevent the excessive second identification mechanism of centre gripping dynamics. The utility model discloses an anchor clamps have good centre gripping effect, carry out the fixed in-process of centre gripping to the bush body, can form the first recognition mechanism of extrusion force discernment in the bush body centre gripping course of working, avoid the dynamics of centre gripping to lead to the fact the line that shakes to take place on the process bush body of cutting inadequately, further improvement the processingquality of bush body.

Description

Outer cylinder bushing clamp for main frame of undercarriage

Technical Field

The utility model belongs to aircraft bush processing equipment specifically indicates an aircraft undercarriage body frame urceolus bush anchor clamps.

Background

In the process of machining the liner of the outer cylinder of the main frame of the aircraft landing gear, the liner needs to be clamped and fixed through a clamp. The general fixture comprises a chuck and a plurality of clamping jaws arranged on the chuck, and the bushing body of the bushing is clamped and fixed through the clamping jaws during bushing processing, so that the bushing is prevented from moving.

Because the bush belongs to a long thin-wall workpiece, when the bush is clamped by the chuck, the clamping force is Cheng Yi, so that the bush is stressed and deformed, the clamping force is not enough, the clamping is not easy to loosen, cutting vibration lines are generated, and the machining quality of the bush is reduced.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an aircraft undercarriage body frame urceolus bush anchor clamps, this anchor clamps have good centre gripping effect.

The above object of the present invention is achieved by the following technical solutions: the utility model provides an aircraft undercarriage body frame urceolus bush anchor clamps, includes chuck and a plurality of jack catchs of setting on the chuck, and a plurality of jack catchs use the chuck central point to be outside radial evenly distributed as the center, its characterized in that: the clamping device comprises clamping mechanisms, a bushing body, a first identification mechanism and a second identification mechanism, wherein the bushing body is clamped and fixed by the clamping mechanisms, the bushing body is used for pressure identification to prevent clamping force from being insufficient, and the second identification mechanism is used for preventing clamping force from being excessive.

Fixture includes the inside first fixed sleeve of fixed mounting at the install bin, the slip cover is equipped with first slip piston rod on the first fixed sleeve, the other end of first slip piston rod is fixed with the driving plate, the other end of driving plate runs through the install bin and stretches out, stretches out the end and is fixed with the arc gripper jaw that is used for centre gripping bush body, the cover is equipped with first spring on the outer wall of first fixed sleeve and first slip piston rod, the both ends of first spring are fixed mutually with install bin and driving plate respectively.

First recognition mechanism is including fixing the first mounting panel in driving plate one side, the inside of install bin is connected with first fixed plate through first coupling assembling, first current conducting plate and second current conducting plate are installed respectively to first mounting panel and first fixed plate relative on the surface, and first current conducting plate is just to setting up with the second current conducting plate, install first pilot lamp on the install bin, the electricity is connected between first current conducting plate, second current conducting plate, first pilot lamp and the power.

The first connecting assembly comprises a second fixing sleeve fixedly mounted inside the installation box, a second sliding piston rod is sleeved on the second fixing sleeve in a sliding mode, the other end of the second sliding piston rod is fixedly connected with the first fixing plate, a second spring is sleeved on the outer walls of the second fixing sleeve and the second sliding piston rod in a sleeved mode, and two ends of the second spring are fixed with the installation box and the first fixing plate respectively.

Second identification mechanism is including fixing the second mounting panel at the driving plate opposite side, the inside of install bin is connected with the second fixed plate through second coupling assembling, first fixed plate is located between driving plate and the second fixed plate, second mounting panel and second fixed plate are relative installs third current conducting plate and fourth current conducting plate respectively on the surface, and third current conducting plate is just to setting up with the fourth current conducting plate, interval between third current conducting plate and the fourth current conducting plate is greater than interval between first current conducting plate and the second current conducting plate, the externally mounted of install bin has the second pilot lamp, be connected electrically between third current conducting plate, fourth current conducting plate, second pilot lamp and the power.

The second coupling assembling includes the inside third fixed sleeve of fixed mounting at the install bin, the slip cover is equipped with third sliding piston pole on the third fixed sleeve, the other end of third sliding piston pole with the second fixed plate fixed connection, the cover is equipped with the third spring on third fixed sleeve and the outer wall of third fixed sleeve, the both ends of third spring are fixed mutually with install bin and second fixed plate respectively.

Compared with the prior art, the utility model discloses have as follows and show the effect:

the utility model discloses an undercarriage body frame urceolus bush anchor clamps carries out the fixed in-process of centre gripping to the bush body, can form the first recognition mechanism of extrusion force discernment in the bush body centre gripping course of working, avoids the dynamics of centre gripping to lead to the fact the line that shakes to take place on the process bush body of cutting inadequately, further improvement the processingquality of bush body. The requirements of the bushing on dimensional accuracy, form and position tolerance and roughness are ensured.

The utility model discloses an undercarriage body frame urceolus bush anchor clamps carries out the fixed in-process of centre gripping to the bush body, can form the second identification mechanism of extrusion force discernment in the bush body centre gripping course of working, avoids the centre gripping to excessively cause the atress of bush body to damage, the processing operation of the bush body of being convenient for.

Drawings

The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.

FIG. 1 is a schematic view of the overall structure of the outer cylinder lining clamp of the landing gear main frame of the aircraft of the present invention in use;

FIG. 2 is a schematic structural view of the outer cylinder bushing clamp of the landing gear main frame of the aircraft according to the present invention partially opened, showing the internal structures of the first recognition mechanism and the second recognition mechanism;

FIG. 3 is an enlarged view of portion A of FIG. 1;

fig. 4 is an enlarged view of a portion B of fig. 2.

In the figure: 1-a chuck; 2-clamping jaws; 3, installing a box; 401-a drive plate; 402-arc gripper jaws; 403-a first fixed sleeve; 404-a first sliding piston rod; 405-a first spring; 501-a first mounting plate; 502-a first fixation plate; 503 — a first conductive plate; 504-a second conductive plate; 505-a first indicator light; 601-a second fixed sleeve; 602-a second sliding piston rod; 603-a second spring; 701-a second mounting plate; 702-a second fixation plate; 703-a third conductive plate; 704-a fourth conductive plate; 705-a second indicator light; 801-a third fixed sleeve; 802-a third sliding piston rod; 803-third spring; 9-the liner body.

Detailed Description

As shown in fig. 1-4, an aircraft landing gear body frame urceolus bush anchor clamps, including chuck 1 and three jack catch 2 of setting on chuck 1, three jack catch 2 uses chuck 1 central point to be outside radial evenly distributed as the center, equal fixed mounting has an install bin 3 on each jack catch 2, establish the power in every install bin 3, all be provided with fixture on every install bin 3, bushing body 9 through fixture centre gripping fixed bush, still be provided with the first recognition mechanism that clamping bush body 9 processes are used for pressure identification in order to prevent that the clamping dynamics is not enough and in order to prevent the excessive second recognition mechanism of clamping dynamics on every install bin 3.

Fixture includes fixed mounting at the inside first fixed sleeve 403 of install bin 3, sliding sleeve is equipped with first sliding piston rod 404 on first fixed sleeve 403, the other end of first sliding piston rod 404 is fixed with driving plate 401, the other end of driving plate 401 runs through install bin 3 and stretches out, it is fixed with the arc gripper jaw 402 that is used for centre gripping bush body 9 to stretch out the end, the cover is equipped with first spring 405 on the outer wall of first fixed sleeve 403 and first sliding piston rod 404, the both ends of first spring 405 are fixed mutually with install bin 3 and driving plate 401 respectively.

First recognition mechanism is including fixing the first mounting panel 501 in driving plate 401 one side, the inside of install bin 3 is connected with first fixed plate 502 through first coupling assembling, install first conductive plate 503 and second conductive plate 504 on the relative surface of first mounting panel 501 and first fixed plate 502 respectively, first conductive plate 503 and second conductive plate 504 are just to setting up, install first pilot lamp 505 on the install bin 3, be connected electrically between first conductive plate 503, second conductive plate 504, first pilot lamp 505 and the power. The first recognition mechanism of extrusion force discernment in the 9 centre gripping course of working of bush that form avoids the dynamics of centre gripping to cause the emergence vibration line on the process bush body 9 of cutting inadequately, further improvement the processingquality of bush body 9.

The first connecting assembly includes a second fixing sleeve 601 fixedly installed inside the mounting box 3, a second sliding piston rod 602 is slidably sleeved on the second fixing sleeve 601, the other end of the second sliding piston rod 602 is fixedly connected with the first fixing plate 502, a second spring 603 is sleeved on the outer walls of the second fixing sleeve 601 and the second sliding piston rod 602, and two ends of the second spring 603 are fixed with the mounting box 3 and the first fixing plate 502 respectively. The reset movement of the first fixing plate 502 after being pressed is facilitated by the first connecting assembly.

The second identification mechanism comprises a second mounting plate 701 fixed on the other side of the transmission plate 401, the inside of the mounting box 3 is connected with a second fixing plate 702 through a second connecting assembly, the first fixing plate 502 is located between the transmission plate 401 and the second fixing plate 702, a third conductive plate 703 and a fourth conductive plate 704 are respectively mounted on the opposite surfaces of the second mounting plate 701 and the second fixing plate 702, the third conductive plate 703 and the fourth conductive plate 704 are arranged in a right-to-right mode, the distance between the third conductive plate 703 and the fourth conductive plate 704 is larger than the distance between the first conductive plate 503 and the second conductive plate 504, a second indicator lamp 705 is mounted outside the mounting box 3, and the third conductive plate 703, the fourth conductive plate 704, the second indicator lamp 705 and a power supply are electrically connected. The second recognition mechanism of extrusion force discernment in the centre gripping course of working of bush body 9 that forms avoids the centre gripping excessively to cause the atress of bush body 9 to damage, the processing operation of the bush body 9 of being convenient for.

The second connecting assembly includes a third fixing sleeve 801 fixedly installed inside the installation box 3, a third sliding piston rod 802 is slidably sleeved on the third fixing sleeve 801, the other end of the third sliding piston rod 802 is fixedly connected with the second fixing plate 702, a third spring 803 is sleeved on the outer walls of the third fixing sleeve 801 and the third fixing sleeve 801, and two ends of the third spring 803 are respectively fixed with the installation box 3 and the second fixing plate 702. The second connecting assembly facilitates the reset movement of the second fixing plate 702 after pressing.

The process of clamping and fixing the lining body 9 of the outer cylinder lining of the main frame of the aircraft landing gear by using the clamp is as follows:

firstly, the bushing body 9 is placed between the arc-shaped clamping jaws 402, the chuck 1 is started, the clamping jaws 2 and the installation boxes 3 on the clamping jaws 2 are driven to be stressed to move close to each other, and the arc-shaped clamping jaws 402 are abutted to the outer side wall of the bushing body 9 through the mutual close movement of the installation boxes 3, so that the bushing body 9 is clamped and fixed.

Then, in the clamping process, after the arc-shaped clamping claws 402 abut against the bushing body 9, the transmission plates 401 are driven to move inside the installation box 3, in the moving process of the transmission plates 401, the first sliding piston rods 404 are pushed to slide on the first fixing sleeves 403 and drive the first springs 405 to deform continuously under stress, the extrusion force of the arc-shaped clamping claws 402 at one ends of the transmission plates 401 on the bushing body 9 is improved through the continuous deformation of the first springs 405, and in the continuous moving process of the transmission plates 401, the first conductive plates 503 on the first installation plates 501 are driven to abut against the second conductive plates 504 on the first fixing plates 502, a circuit among the first conductive plates 503, the second conductive plates 504, the first indicator lamps 505 and a power supply is connected, so that the first indicator lamps 505 start to light up, the lighting of the first indicator lamps 505 indicates that the extrusion force of the arc-shaped clamping claws 402 on the bushing body 9 is pushed by the first springs 405 at the moment, a first recognition mechanism for recognizing the extrusion force in the clamping process of the bushing body 9 is formed, and the vibration lines on the bushing body in the clamping process are prevented from being up to the standard, and the quality of the bushing body 9 is further improved.

Finally, when the clamping force needs to be continuously increased after the first indicator lamp 505 is lighted, the jaws 2 are continuously driven, so that each transmission plate 401 continuously slides in the installation box 3, and in the movement process of the transmission plates 401, when the third conductive plate 703 on the second installation plate 701 abuts against the fourth conductive plate 704 on the second fixing plate 702, a circuit among the third conductive plate 703, the fourth conductive plate 704, the second indicator lamp 705 and a power supply is connected, so that the second indicator lamp 705 starts to light, and the lighting of the second indicator lamp 705 indicates that the extrusion force of the arc-shaped clamping jaw 402 pushed by the first spring 405 to the bushing body 9 exceeds the standard at the moment, the clamping force needs to be reduced, a second identification mechanism for identifying the extrusion force in the clamping processing process of the bushing body 9 is formed, the stress damage of the bushing body 9 caused by excessive clamping is avoided, and the processing operation of the bushing body 9 is facilitated.

Claims

1. The utility model provides an aircraft undercarriage body frame urceolus bush anchor clamps, includes chuck (1) and sets up a plurality of jack catchs (2) on chuck (1), and a plurality of jack catchs (2) use chuck (1) central point to be outside radial evenly distributed as the center, its characterized in that: equal fixed mounting has an install bin (3) on each jack catch (2), establishes the power in every install bin (3), all is provided with fixture on every install bin (3), and through bushing body (9) of fixture centre gripping fixed bushing, still be provided with centre gripping bushing body (9) process on every install bin (3) and be used for pressure identification in order to prevent the not enough first recognition mechanism of centre gripping dynamics and in order to prevent the excessive second recognition mechanism of centre gripping dynamics.

2. An aircraft landing gear main frame outer cylinder liner clamp according to claim 1, wherein: fixture includes fixed mounting at inside first fixed sleeve (403) of install bin (3), the sliding sleeve is equipped with first sliding piston pole (404) on first fixed sleeve (403), the other end of first sliding piston pole (404) is fixed with driving plate (401), the other end of driving plate (401) runs through install bin (3) and stretches out, stretches out the end and is fixed with arc gripper jaw (402) that are used for centre gripping bush body (9), the cover is equipped with first spring (405) on the outer wall of first fixed sleeve (403) and first sliding piston pole (404), the both ends of first spring (405) are fixed mutually with install bin (3) and driving plate (401) respectively.

3. An aircraft landing gear main frame outer cylinder liner clamp according to claim 2, wherein: first recognition mechanism is including fixing first mounting panel (501) in driving plate (401) one side, the inside of install bin (3) is connected with first fixed plate (502) through first coupling assembling, first conductive plate (503) and second conductive plate (504) are installed respectively on the surface that first mounting panel (501) and first fixed plate (502) are relative, and first conductive plate (503) and second conductive plate (504) are just to setting up, install first pilot lamp (505) on install bin (3), be connected electrically between first conductive plate (503), second conductive plate (504), first pilot lamp (505) and the power.

4. An aircraft landing gear main frame outer barrel lining clamp according to claim 3, wherein: first connecting element includes fixed mounting at the inside second fixed sleeve (601) of install bin (3), sliding sleeve is equipped with second sliding piston pole (602) on second fixed sleeve (601), the other end of second sliding piston pole (602) with first fixed plate (502) fixed connection, the cover is equipped with second spring (603) on the outer wall of second fixed sleeve (601) and second sliding piston pole (602), the both ends of second spring (603) are fixed mutually with install bin (3) and first fixed plate (502) respectively.

5. An aircraft landing gear main frame outer barrel lining clamp according to claim 3 or 4, wherein: the second recognition mechanism comprises a second mounting plate (701) fixed on the other side of the transmission plate (401), a second fixing plate (702) is connected to the inside of the mounting box (3) through a second connecting assembly, the first fixing plate (502) is located between the transmission plate (401) and the second fixing plate (702), a third conductive plate (703) and a fourth conductive plate (704) are respectively installed on the surface opposite to the second mounting plate (701) and the second fixing plate (702), the third conductive plate (703) and the fourth conductive plate (704) are arranged right opposite to each other, the distance between the third conductive plate (703) and the fourth conductive plate (704) is larger than the distance between the first conductive plate (503) and the second conductive plate (504), a second indicator lamp (705) is installed outside the mounting box (3), and the third conductive plate (703), the fourth conductive plate (704), the second indicator lamp (705) and a power supply are electrically connected.

6. An aircraft landing gear main frame outer cylinder liner clamp according to claim 5, wherein: the second coupling assembling includes the inside third fixed sleeve of fixed mounting in install bin (3), the sliding sleeve is equipped with third sliding piston rod on the third fixed sleeve, third sliding piston rod's the other end with second fixed plate (702) fixed connection, the cover is equipped with the third spring on third fixed sleeve and the fixed telescopic outer wall of third, the both ends of third spring are fixed mutually with install bin (3) and second fixed plate (702) respectively.