CN113716072A

CN113716072A - Aircraft spare part detects uses clamping device

Info

Publication number: CN113716072A
Application number: CN202111096758.6A
Authority: CN
Inventors: 常丽敏; 郝庆波; 战晔; 李浩然; 姜旭东
Original assignee: PLA AIR FORCE AVIATION UNIVERSITY
Current assignee: PLA AIR FORCE AVIATION UNIVERSITY
Priority date: 2021-09-17
Filing date: 2021-09-17
Publication date: 2021-11-30
Anticipated expiration: 2041-09-17
Also published as: CN113716072B

Abstract

The invention discloses a clamping device for detecting aircraft parts, which comprises a base, wherein a supporting mechanism is arranged on the upper surface of the base, a transmission mechanism is rotatably connected between the supporting mechanism and the base through a bearing, and four clamping mechanisms are arranged on the upper surface of the supporting mechanism in a surrounding decoration manner relative to the transmission mechanism. When the clamping mechanism is used, one of the clamping mechanisms is driven to be fixed with the transmission gear through the conveying mechanism, the first bevel gear can not rotate, the placing plate can rotate clockwise to drive the second bevel gear to rotate, the second bevel gear drives the first screw rod to rotate through matching with the first bevel gear, the first screw rod drives the clamping rod to move towards the center of the placing plate through matching with the first screw rod nut, and then different parts can be clamped.

Description

Aircraft spare part detects uses clamping device

Technical Field

The invention relates to a clamping device for detecting parts, in particular to a clamping device for detecting parts of an aircraft, and belongs to the technical field of detection of parts of aircraft.

Background

The spare part of aircraft need detect it after production is accomplished, and its model of spare part of aircraft is diversified usually, and its size of spare part of different specifications is also different, and then it is fixed to carry out the centre gripping through anchor clamps when making the detection, and current clamping device is when using, need start horizontal vertical two-way clamping device and carry out the centre gripping to it, can be comparatively loaded down with trivial details when the operation, and the gyration phenomenon appears easily in the motor after stopping, causes the centre gripping not hard up, to this it is necessary to provide an aircraft spare part detects and uses clamping device.

Disclosure of Invention

The invention aims to solve the defects in the prior art and provides a clamping device for detecting an aircraft part.

In order to achieve the purpose, the invention adopts the following technical scheme:

the utility model provides an aircraft spare part detects and uses clamping device, includes a base, the upper surface of base is provided with a supporting mechanism, it is connected with a drive mechanism to rotate through the bearing jointly between supporting mechanism and the base, supporting mechanism's upper surface is around decorating being provided with four fixture about drive mechanism, be provided with a conveying mechanism in the inside of base on supporting mechanism and drive mechanism's position, conveying mechanism corresponds and all is provided with a latch mechanism, one of them on supporting mechanism and drive mechanism's the position latch mechanism's inside is provided with one and extends the mechanism.

Preferably, the supporting mechanism includes a ring channel, the upper surface at the base is seted up to the ring channel, the ring channel internal rotation is connected with an annular piece, the upper end of annular piece runs through the notch of ring channel and upwards extends and fixedly connected with one places the board, the even equidistance of lower surface that the annular piece is located the ring channel has seted up a plurality of ball groove, a plurality of equal roll connection has a ball, a plurality of in the ball groove the lower terminal surface of ball all runs through the notch that corresponds the ball groove and extends to in the ring channel and offset with the tank bottom of ring channel.

Preferably, the transmission mechanism comprises a transmission rod, the transmission rod is connected to the base and the placing plate through a bearing in a rotating mode, a transmission cavity is formed in the base corresponding to the position of the transmission rod, the lower end of the transmission rod penetrates through the upper end cavity wall of the transmission cavity, extends into the transmission cavity and is fixedly connected with a transmission gear, a transmission groove is formed in the upper surface of the placing plate corresponding to the position of the transmission rod, and the upper end of the transmission rod extends into the transmission groove and is fixedly connected with a first bevel gear.

Preferably, the four clamping mechanisms comprise a T-shaped sliding groove, the four T-shaped sliding grooves are arranged in a surrounding manner about the transmission groove, a first lead screw is rotatably connected between opposite groove walls of the four T-shaped sliding grooves through a bearing, one end of the first lead screw extends into the transmission groove, a second bevel gear is fixedly connected to one end of the first lead screw, which is located in the transmission groove, and is meshed with the first bevel gear, a first lead screw nut is connected to each of the four first lead screw, which is located on a rod wall of the T-shaped sliding groove, a T-shaped sliding block is fixedly sleeved on an outer side wall of the first lead screw nut, the four T-shaped sliding blocks are respectively and slidably connected in the corresponding T-shaped sliding grooves, and the upper ends of the four T-shaped sliding blocks penetrate through one notch of the corresponding T-shaped sliding groove and extend upwards and are fixedly connected with clamping rods.

Preferably, conveying mechanism includes a transport chamber, carry the chamber to set up in the inside of base, it is connected with a second lead screw to rotate through the bearing between the relative inner chamber wall in chamber to carry, the wherein one end of second lead screw runs through the corresponding lateral wall of base and extends to the outer and a rotation handle of fixedly connected with of base, threaded connection has two second screw-nut, two on the second lead screw lies in one section pole wall of transport chamber equal fixedly connected with transport piece on the lateral wall of second screw-nut.

Preferably, two the latch mechanism all includes a slide opening that is the setting of L type, two the slide opening is all seted up on the upper end chamber wall of carrying the chamber, two the drill way that the slide opening kept away from and is carried chamber one end is linked together with transmission chamber and ring channel respectively, corresponds a ring gear of fixedly connected with on the annular piece lateral wall of slide opening position corresponds two the joint piece that equal fixedly connected with one was the setting of L type on the transport piece of slide opening position, wherein one the joint piece is kept away from a rack of the one end fixedly connected with of transport piece, another the joint piece is kept away from the one end of transport piece and is passed through a rack of the fixedly connected with of acceptance mechanism.

Preferably, extend the mechanism and include a fixed slot, the fixed slot is seted up in one of them joint piece and is kept away from the one end of carrying the piece, a spring of tank bottom fixedly connected with of fixed slot, a dead lever of one end fixedly connected with of fixed slot tank bottom is kept away from to the spring, the dead lever is kept away from the spring and is run through the notch of fixed slot and extend to the transmission intracavity and be connected with the rack.

Preferably, be the symmetry form on the relative cell wall of fixed slot and seted up two spacing grooves, two equal sliding connection has a stopper in the spacing groove, two stopper one end in opposite directions all extends to in the fixed slot and fixed connection is on the relative pole wall of dead lever.

The clamping device for detecting the aircraft parts has the advantages that:

1. when the clamping device for detecting the aircraft parts is used, firstly, one of the clamping mechanisms is driven by the conveying mechanism to fix the transmission gear, so that the first bevel gear cannot rotate, at the moment, the placing plate can be rotated clockwise to drive the second bevel gear to rotate, the second bevel gear drives the first screw rod to rotate through matching with the first bevel gear, and the first screw rod drives the clamping rod to move towards the center of the placing plate through matching with the first screw rod nut, so that different parts can be clamped.

2. According to the clamping device for detecting the aircraft parts, after the parts are clamped and fixed, the two clamping mechanisms can be driven by the conveying mechanism, and the supporting mechanism and the transmission mechanism are respectively fixed by the two clamping mechanisms, so that the clamping mechanism cannot loosen after the parts are clamped and fixed.

Drawings

FIG. 1 is a schematic structural view of a clamping device for detecting aircraft parts according to the present invention;

FIG. 2 is an enlarged schematic structural view of a portion A in FIG. 1 of a clamping device for detecting an aircraft component according to the present invention;

FIG. 3 is an enlarged schematic structural view of a portion B in FIG. 1 of the clamping device for detecting aircraft parts according to the present invention;

FIG. 4 is a sectional view of a top view of a placement plate of the clamping device for detecting aircraft parts according to the present invention;

FIG. 5 is a cross-sectional view of a top view of a base of the clamping device for detecting aircraft parts according to the present invention;

FIG. 6 is a schematic top view of a clamping device for detecting aircraft parts according to the present invention;

fig. 7 is a cross-sectional side view of a clamping device for detecting an aircraft component according to the present invention.

In the figure: the device comprises a base 1, a supporting mechanism 2, an annular groove 21, an annular block 22, a placing plate 23, a ball groove 24, a ball 25, a transmission mechanism 3, a transmission rod 31, a transmission cavity 32, a transmission gear 33, a transmission groove 34, a first bevel gear 35, a clamping mechanism 4, a T-shaped sliding groove 41, a first screw rod 42, a second bevel gear 43, a first screw rod nut 44, a T-shaped sliding block 45, a clamping rod 46, a conveying mechanism 5, a conveying cavity 51, a second screw rod 52, a second screw rod nut 53, a conveying block 54, a rotating handle 55, a clamping mechanism 6, a sliding hole 61, a gear ring 62, a clamping block 63, a rack 64, an extending mechanism 7, a fixing groove 71, a spring 72, a fixing rod 73, a limiting groove 8 and a limiting block 9.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.

Referring to fig. 1-7, a clamping device for aircraft part detection comprises a base 1, a supporting mechanism 2 is arranged on the upper surface of the base 1, a transmission mechanism 3 is rotatably connected between the supporting mechanism 2 and the base 1 through a bearing, four clamping mechanisms 4 are arranged on the upper surface of the supporting mechanism 2 around the transmission mechanism 3 in a decorative manner, a conveying mechanism 5 is arranged in the base 1 at positions corresponding to the supporting mechanism 2 and the transmission mechanism 3, a clamping mechanism 6 is arranged at positions corresponding to the supporting mechanism 2 and the transmission mechanism 3 of the conveying mechanism 5, and an extension mechanism 7 is arranged in one clamping mechanism 6.

Wherein, supporting mechanism 2 includes a ring channel 21, ring channel 21 sets up the upper surface at base 1, the ring channel 21 internal rotation is connected with an annular piece 22, the notch that ring channel 21 was run through to annular piece 22's upper end upwards extends and fixedly connected with one places board 23, a plurality of ball groove 24 has been seted up to the even equidistance of lower surface that annular piece 22 is located ring channel 21, equal roll connection has a ball 25 in a plurality of ball groove 24, the lower terminal surface of a plurality of ball 25 all runs through the notch that corresponds ball groove 24 and extends to in the ring channel 21 and offsets with the tank bottom of ring channel 21.

The transmission mechanism 3 comprises a transmission rod 31, the transmission rod 31 is connected to the base 1 and the placing plate 23 through a bearing in a rotating mode, a transmission cavity 32 is formed in the base 1 corresponding to the position of the transmission rod 31, the lower end of the transmission rod 31 penetrates through the upper end cavity wall of the transmission cavity 32 and extends into the transmission cavity 32 and is fixedly connected with a transmission gear 33, a transmission groove 34 is formed in the upper surface of the placing plate 23 corresponding to the position of the transmission rod 31, and the upper end of the transmission rod 31 extends into the transmission groove 34 and is fixedly connected with a first bevel gear 35.

Wherein, four fixture 4 all include a T type spout 41, four T type spouts 41 are the setting of encircleing form about drive groove 34, all be connected with a first lead screw 42 through the bearing rotation between the relative cell wall of four T type spouts 41, wherein one end of four first lead screws 42 all extends to in the drive groove 34, four first lead screws 42 are located the equal fixedly connected with second bevel gear 43 of one end of drive groove 34, four second bevel gears 43 all mesh with first bevel gear 34 mutually, four first lead screws 42 are located the equal threaded connection of pole wall in T type spout 41 and have a first screw-nut 44, all fixedly cup jointed a T type slider 45 on four first screw-nut 44's the lateral wall, four T type sliders 45 are sliding connection respectively in the T type spout 41 that corresponds, the upper end of four T type sliders 45 all runs through the notch of corresponding T type spout 41 and upwards extends and a clamping rod 46 of fixedly connected with.

Wherein, conveying mechanism 5 includes a transport chamber 51, transport chamber 51 sets up in the inside of base 1, it is connected with a second lead screw 52 to rotate through the bearing between the relative inner chamber wall of transport chamber 51, one of them one end of second lead screw 52 runs through the corresponding lateral wall of base 1 and extends to the base 1 outside and a rotation handle 55 of fixedly connected with, threaded connection has two second screw-nut 53 on the one section pole wall that second lead screw 52 is located transport chamber 51, equal fixedly connected with transport piece 54 on two second screw-nut 53's the lateral wall.

Wherein, two latch mechanisms 6 all include a sliding hole 61 that is the setting of L type, two sliding hole 61 are all seted up on the upper end chamber wall of carrying chamber 51, the drill way that two sliding hole 61 kept away from and carry chamber 51 one end is linked together with transmission chamber 32 and ring channel 21 respectively, correspond a ring gear 62 of fixedly connected with on the annular piece 22 lateral wall of sliding hole 61 position, correspond joint piece 63 that equal fixedly connected with was the setting of L type on the transport piece 54 of two sliding hole 61 positions, wherein a joint piece 63 keeps away from a rack 64 of one end fixedly connected with of transport piece 54, another joint piece 63 keeps away from a rack 64 of one end fixedly connected with of transport piece 54 through checking and accepting mechanism 7 fixedly connected with.

The extending mechanism 7 includes a fixing groove 71, the fixing groove 71 is provided at one end of one of the clamping blocks 63 far from the conveying block 54, a spring 72 is fixedly connected to the bottom of the fixing groove 71, a fixing rod 73 is fixedly connected to one end of the spring 72 far from the bottom of the fixing groove 71, and the fixing rod 73 far from the spring 72 penetrates through the notch of the fixing groove 71, extends into the transmission cavity 32 and is connected with the rack 64.

Wherein, be two spacing grooves 8 on the relative cell wall of fixed slot 71 and seted up for the symmetry form, equal sliding connection has a stopper 9 in two spacing grooves 8, and two stopper 9 one ends in opposite directions all extend to in the fixed slot 71 and fixed connection is on the relative pole wall of dead lever 73.

The working principle is as follows: when the aircraft is used, the handle 55 is rotated to drive the second screw rod 52 to rotate, the second screw rod 52 is in threaded connection with the second screw rod nut 53, so that the two conveying blocks 54 and the clamping blocks 63 can be driven to move synchronously, the spring 72 in one clamping block 63 can push the fixing rod 73, the fixing rod 73 can push the rack 64 to be meshed with the transmission gear 33 firstly, further, the transmission gear 33, the transmission rod 31 and the first bevel gear 35 can be prevented from rotating, meanwhile, the other rack 64 is not meshed with the gear ring 62, so that the annular block 22 and the placing plate 23 can rotate, at the moment, aircraft parts are placed in the center of the placing plate 23, the placing plate 23 is rotated clockwise, the placing plate 23 synchronously drives the four second bevel gears 43 to move, and the second bevel gears 43 are driven to rotate when moving because the first bevel gear 35 cannot rotate, second bevel gear 43 then drives first lead screw 42 and carries out synchronous rotation, first lead screw 42 drives T type slider 45 through the cooperation with first screw-nut 44 and removes, T type slider 45 drives supporting rod 46 and removes to the intermediate position, and until accomplish the centre gripping to spare part, after the centre gripping is accomplished, can drive second lead screw 52 through rotating handle 55 and rotate, second lead screw 52 through with second screw-nut 53 between threaded connection, can drive two transport block 54 and joint piece 63 synchronous motion, and then make two joint pieces 63 fix transmission gear 33 and gear ring 62 respectively, and then can avoid annular piece 22 to rotate, annular piece 22 can' T rotate then supporting rod 46 can not produce not hard up.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.

Claims

1. The utility model provides an aircraft spare part detects uses clamping device, includes a base (1), its characterized in that, the upper surface of base (1) is provided with a supporting mechanism (2), it is connected with a drive mechanism (3) to rotate through the bearing jointly between supporting mechanism (2) and base (1), the upper surface of supporting mechanism (2) is around decorating being provided with four fixture (4) about drive mechanism (3), be provided with one conveying mechanism (5) on the inside of base (1) is about the position of supporting mechanism (2) and drive mechanism (3), all be provided with one latch mechanism (6) on the position that conveying mechanism (5) correspond supporting mechanism (2) and drive mechanism (3), one of them the inside of latch mechanism (6) is provided with one and extends mechanism (7).

2. The aircraft component inspection clamping device of claim 1, the supporting mechanism (2) comprises an annular groove (21), the annular groove (21) is arranged on the upper surface of the base (1), an annular block (22) is rotationally connected in the annular groove (21), the upper end of the annular block (22) penetrates through the notch of the annular groove (21), extends upwards and is fixedly connected with a placing plate (23), the even equidistance of lower surface that annular piece (22) were located ring channel (21) has seted up a plurality of ball groove (24), a plurality of equal roll connection has a ball (25), a plurality of in ball groove (24) the lower terminal surface of ball (25) all runs through the notch that corresponds ball groove (24) and extends to in ring channel (21) and offsets with the tank bottom of ring channel (21).

3. The aircraft part detection clamping device according to claim 1, wherein the transmission mechanism (3) comprises a transmission rod (31), the transmission rod (31) is connected to the base (1) and the placing plate (23) in a rotating mode through a bearing, a transmission cavity (32) is formed in the base (1) corresponding to the position of the transmission rod (31), the lower end of the transmission rod (31) penetrates through the upper end cavity wall of the transmission cavity (32) and extends into the transmission cavity (32) and is fixedly connected with a transmission gear (33), a transmission groove (34) is formed in the upper surface of the placing plate (23) corresponding to the position of the transmission rod (31), and the upper end of the transmission rod (31) extends into the transmission groove (34) and is fixedly connected with a first bevel gear (35).

4. The aircraft part detecting and clamping device according to claim 1, wherein each of the four clamping mechanisms (4) comprises a T-shaped sliding groove (41), the four T-shaped sliding grooves (41) are arranged in a surrounding manner with respect to the transmission groove (34), a first lead screw (42) is rotatably connected between the opposite groove walls of the four T-shaped sliding grooves (41) through a bearing, one end of each of the four first lead screws (42) extends into the transmission groove (34), one end of each of the four first lead screws (42) located in the transmission groove (34) is fixedly connected with a second bevel gear (43), the four second bevel gears (43) are engaged with the first bevel gears (34), and a first lead screw nut (44) is threadedly connected to the rod wall of each of the four first lead screws (42) located in the T-shaped sliding grooves (41), four all fixed T type slider (45) of having cup jointed on the lateral wall of first feed screw nut (44), four T type slider (45) sliding connection respectively is in T type spout (41) that correspond, four the notch that corresponds T type spout (41) all runs through and upwards extends and a clamping rod (46) of fixedly connected with in the upper end of T type slider (45).

5. The aircraft part detection clamping device according to claim 1, wherein the conveying mechanism (5) comprises a conveying cavity (51), the conveying cavity (51) is arranged inside the base (1), a second lead screw (52) is rotatably connected between the inner cavity walls of the conveying cavity (51) through a bearing, one end of the second lead screw (52) penetrates through the corresponding side wall of the base (1) and extends out of the base (1), a rotating handle (55) is fixedly connected with the outer cavity wall of the base (1), two second lead screw nuts (53) are in threaded connection with one section of the rod wall of the second lead screw (52) located in the conveying cavity (51), and a conveying block (54) is fixedly connected with the outer side wall of each of the two second lead screw nuts (53).

6. The aircraft part detects and uses clamping device according to claim 1, characterized in that, two clamping mechanism (6) all include one be the sliding hole (61) that the L type set up, two sliding hole (61) all set up on the upper end chamber wall of transport chamber (51), two the drill way that sliding hole (61) kept away from transport chamber (51) one end is linked together with transmission chamber (32) and ring channel (21) respectively, correspond fixedly connected with a gear ring (62) on the annular block (22) lateral wall of sliding hole (61) position, correspond two equal fixedly connected with one is the joint piece (63) that the L type set up on transport block (54) of sliding hole (61) position, wherein one joint piece (63) keep away from the one end fixedly connected with a rack (64) of transport block (54), another joint piece (63) keep away from the one end of transport block (54) and pass through acceptance mechanism (7) fixedly connected with a piece tooth A strip (64).

7. The aircraft part detecting clamping device as claimed in claim 1, wherein the extending mechanism (7) comprises a fixing groove (71), the fixing groove (71) is formed at one end of one of the clamping blocks (63) far away from the conveying block (54), a spring (72) is fixedly connected to the bottom of the fixing groove (71), a fixing rod (73) is fixedly connected to one end of the spring (72) far away from the bottom of the fixing groove (71), and the fixing rod (73) far away from the spring (72) penetrates through the notch of the fixing groove (71), extends into the transmission cavity (32) and is connected with the rack (64).

8. The aircraft part detecting clamping device as claimed in claim 7, wherein two limiting grooves (8) are symmetrically formed in opposite groove walls of the fixing groove (71), a limiting block (9) is slidably connected in each of the two limiting grooves (8), and opposite ends of the two limiting blocks (9) extend into the fixing groove (71) and are fixedly connected to opposite rod walls of the fixing rod (73).