Automatic clamping mechanism for aero-engine assembly mounting section

Abstract

The utility model belongs to the technical field of engine clamping devices, and discloses an automatic clamping mechanism for aero-engine assembly mounting joints, which comprises a semicircular base, two first clamping components and a second clamping component, the semicircular base is mounted on a rotating unit and can be driven by the rotating unit to rotate, and the two first clamping components are mounted on the semicircular base. The two first clamping assemblies are fixedly installed at the two ends of the semicircular base, the middle of the semicircular base extends towards one side to be fixedly provided with an extension rod, the second clamping assembly is fixed to one side of the semicircular base through the extension rod, and the two ends and the middle of the aero-engine are clamped and fixed through the first clamping assemblies and the second clamping assembly. The cross V-shaped notch and the shearing pin hole are respectively designed at the tail end of the mounting section and the middle position of the shaft, and the rotation stopping pin and the shearing pin are inserted into the cross V-shaped notch and the shearing pin hole, so that the rotation stopping effect of engine parts is enhanced, and the clamping device has the advantages of high clamping precision, stable performance and high automation degree.

Description

TECHNICAL FIELD

[0001] The utility model belongs to engine clamping device technical field especially relates to an automatic clamping mechanism of aero-engine assembly installation section. BACKGROUND

[0002] In recent years, with the development of robot technology, artificial intelligence technology and the accelerated integration of manufacturing industry, the transformation and upgrading pace is accelerating in the field of aero-engine manufacturing from top-level design. The automatic flexible production unit represented by robot application, the beat pulsation type assembly production line, etc. has gradually replaced the manual assembly of engine products. It has high automation degree, strong flexibility and adaptability, and realizes a new manufacturing mode of high efficiency and agility through information technology integration. At present, the assembly and manufacturing of domestic aero-engine still mainly adopts the traditional rigid assembly on the vehicle, and the positioning connection of aero-engine and assembly vehicle is realized through the manual fixing and clamping of installation section by bolts and nuts. This device lacks real-time feedback and self-adaptive adjustment function, has long changeover time, poor modularization and reconfigurability, and is difficult to adapt to the rapid changeover demand of multi-variety and small-batch production, which seriously restricts the bottleneck of the improvement of aero-engine assembly automation technology. SUMMARY

[0003] The utility model aims at providing an automatic clamping mechanism of aero-engine assembly installation section to solve the above technical problems.

[0004] To achieve the above purpose, the specific technical scheme of the automatic clamping mechanism of aero-engine assembly installation section of the utility model is as follows:

[0005] An automatic clamping mechanism of aero-engine assembly installation section, comprising a semicircular base, two clamping assemblies one and one clamping assembly two, the semicircular base is installed on the rotating unit and can rotate under the driving of the rotating unit, two clamping assemblies one are fixedly installed at both ends of the semicircular base, an extension rod is fixedly extended to one side in the middle of the semicircular base, the clamping assembly two is fixed on one side of the semicircular base through an extension rod, and the clamping assembly one and the clamping assembly two realize the clamping and fixing of both ends and the middle of the aero-engine.

[0006] Further, the clamping assembly one comprises a fixed seat, an upper pressing plate, a linear shaft and a locking cylinder one, the fixed seat is fixedly installed at both ends of the semicircular base, the linear shaft is fixedly installed on the fixed seat, the upper pressing plate is in sliding connection with the linear shaft, the locking cylinder one is connected with the upper pressing plate, the fixed seat is internally provided with an arc-shaped groove, the aero-engine is connected with mounting nodes at both ends, the mounting nodes are arranged in the arc-shaped groove, the upper pressing plate is provided with a through hole for the mounting nodes to pass through in the middle, the locking cylinder one outputs linear motion to drive the upper pressing plate to reciprocate linearly, the upper pressing plate moves from the rear side to the front side, and the mounting nodes are limited in the through hole of the upper pressing plate, so that the engine mounting node is fixed.

[0007] Further, the fixed seat comprises a bottom plate, a front side plate and a rear side plate, the front side plate and the rear side plate are fixedly installed on both sides of the bottom plate and are connected through the linear shaft, the locking cylinder one is fixedly installed on the front side plate, and the front side plate and the bottom plate are provided with arc-shaped grooves in the middle and at the front end.

[0008] Further, the upper pressing plate is provided with a rotation stopping pin at the top, the mounting node is provided with a cross-shaped V-shaped notch matched with the rotation stopping pin, after the upper pressing plate moves into the mounting node, the rotation stopping pin is clamped into the cross-shaped V-shaped notch of the mounting node, and rotation of the product during clamping is prevented.

[0009] Further, the semicircular base is further fixedly provided with a shearing pin and a pushing cylinder inside at both ends, the output end of the pushing cylinder is fixedly connected with the shearing pin, the mounting node is provided with a shearing pin hole, and the shearing pin is stretched into the shearing pin hole of the mounting node under the action of the pushing cylinder, so that the axial fixing of the mounting node is realized.

[0010] Further, the clamping assembly two comprises a base, a bolt, a V-shaped support assembly and a locking cylinder two, the base is fixedly installed on the extension rod, the locking cylinder two is fixedly installed on the base and is fixedly connected with the V-shaped support assembly at the output end, the V-shaped support assembly is connected with two bolts at the upper end, the aero-engine body is provided with an expansion casing positioning hole at the lower end, and the V-shaped support assembly drives the bolts to reciprocate linearly under the drive of the locking cylinder two, so that the bolts are inserted into or withdrawn from the expansion casing positioning hole of the aero-engine.

[0011] Further, the base is fastened with the extension rod through hand screws, and replacement is facilitated.

[0012] Further, the locking cylinder one and the locking cylinder two are CDLQB25-45DCM.

[0013] 1) The automatic clamping mechanism of the aero-engine assembly mounting joint changes the traditional manual bolt and nut fixing and clamping mode, solves the constraint dependence on manual operation, and breaks through the key process demand of product clamping automation of automatic assembly and manufacturing;

[0014] 2) The automatic clamping mechanism of the aero-engine assembly mounting joint changes the traditional manual bolt and nut fixing and clamping mode, solves the constraint dependence on manual operation, and breaks through the key process demand of product clamping automation of automatic assembly and manufacturing;

[0015] 3) The automatic clamping mechanism of the aero-engine assembly mounting joint changes the traditional manual bolt and nut fixing and clamping mode, solves the constraint dependence on manual operation, and breaks through the key process demand of product clamping automation of automatic assembly and manufacturing;

[0016] 4) The automatic clamping mechanism of the aero-engine assembly mounting joint changes the traditional manual bolt and nut fixing and clamping mode, solves the constraint dependence on manual operation, and breaks through the key process demand of product clamping automation of automatic assembly and manufacturing; BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is a structure schematic view of the automatic clamping mechanism of the aero-engine assembly mounting joint of the utility model;

[0018] Figure 2 It is a structure schematic view of the automatic clamping mechanism of the aero-engine assembly mounting joint of the utility model;

[0019] Figure 3 It is a structure schematic view of the automatic clamping mechanism of the aero-engine assembly mounting joint of the utility model;

[0020] Figure 4 It is a structure schematic view of the automatic clamping mechanism of the aero-engine assembly mounting joint of the utility model;

[0021] Figure 5 It is a structure schematic view of the automatic clamping mechanism of the aero-engine assembly mounting joint of the utility model;

[0022] Figure 6 It is a structure schematic view of the automatic clamping mechanism of the aero-engine assembly mounting joint of the utility model;

[0023] Figure 7 It is a structure schematic view of the automatic clamping mechanism of the aero-engine assembly mounting joint of the utility model;

[0024] Marked description: 1, semicircular base; 2, clamping assembly one; 21, fixed seat; 211, bottom plate; 212, front side plate; 213, rear side plate; 22, upper pressing plate; 221, through hole; 222, rotation stop pin; 23, linear shaft; 24, with lock cylinder one; 25, L-shaped connecting plate; 26, shear pin; 27, push cylinder; 28, arc-shaped groove; 3, clamping assembly two; 31, base; 32, bolt; 33, V-shaped support assembly; 34, with lock cylinder two; 4, rotating unit; 5, aero-engine; 51, mounting section; 511, cross V-shaped notch; 512, shear pin hole; 52, diffuser casing positioning hole. DETAILED DESCRIPTION

[0025] In order to better understand the purpose, structure and function of the utility model, the utility model aero-engine assembly mounting section automatic clamping mechanism is described in further detail below in conjunction with the drawings.

[0026] As Figure 1 The utility model discloses an aero-engine assembly mounting section automatic clamping mechanism, including semicircular base 1, two clamping assembly one 2 and a clamping assembly two 3, semicircular base 1 is installed on rotating unit 4, can be rotated under the driving of rotating unit 4, two clamping assembly one 2 is fixedly installed at both ends of semicircular base 1, and one extension rod 11 is fixed in the middle of semicircular base 1 to one side, and clamping assembly two 3 is fixed in one side of semicircular base 1 through one extension rod 11. Clamping assembly one 2 and clamping assembly two 3 realize the clamping of the both ends and the middle of aero-engine 5.

[0027] As Figures 2-3As shown, the clamping assembly one 2 includes a fixed seat 21, an upper pressing plate 22, a linear shaft 23 and a locking cylinder one 24, the fixed seat 21 is fixedly installed at both ends of the semicircular base 1, the linear shaft 23 is fixedly installed on the fixed seat 21, the upper pressing plate 22 is in sliding connection with the linear shaft 23, the locking cylinder one 24 is connected with the upper pressing plate 22, and the locking cylinder one 24 outputs linear motion to drive the upper pressing plate 22 to reciprocate linearly. Specifically, the fixed seat 21 includes a bottom plate 211, a front side plate 212 and a rear side plate 213, the front side plate 212 and the rear side plate 213 are fixed on both sides of the bottom plate 211, and are connected through the linear shaft 23, the upper pressing plate 22 is in sliding connection with the linear shaft 23, the locking cylinder one 24 is fixedly installed on the front side plate 212, the front side plate 212 has an arc-shaped groove 28 in the middle and at the front end of the bottom plate 211, the mounting joint 51 is connected at both ends of the aero-engine 5, the mounting joint 51 is arranged in the arc-shaped groove 28, the upper pressing plate 22 has a through hole 221 in the middle for the mounting joint 51 to pass through, the output end of the locking cylinder one 24 is fixedly connected with the upper pressing plate 22 through an L-shaped connecting plate 25, the locking cylinder one 24 outputs linear motion to drive the upper pressing plate 22 to reciprocate linearly, the upper pressing plate 22 moves from the rear side to the front side, and the mounting joint 51 is limited in the through hole of the upper pressing plate 22, so that the engine mounting joint is held. Meanwhile, the upper pressing plate 22 is provided with a rotation stopping pin 222 at the top, the mounting joint 51 has a cross-shaped V-shaped notch 511 matched with the rotation stopping pin 222, after the upper pressing plate 22 moves into the mounting joint 51, the rotation stopping pin 222 is clamped into the cross-shaped V-shaped notch 511 of the mounting joint 51, so that the product is prevented from rotating during clamping (when the diffuser casing is not assembled), and the angular accurate positioning of the engine part is realized.

[0028] As shown in Figures 4-6 The semicircular base 1 is further fixed with a shearing pin 26 and a pushing cylinder 27 at both ends, the output end of the pushing cylinder 27 is fixedly connected with the shearing pin 26, the mounting joint 51 has a shearing pin hole 512, and the shearing pin 26 extends into the shearing pin hole 512 of the mounting joint 51 under the action of the pushing cylinder 27, so that the axial fixation of the mounting joint 51 is realized, and the rotation stopping effect of the engine part is enhanced.

[0029] The locking cylinder one 24 and the pushing cylinder 27 are both provided with a detection position sensor, so as to ensure that each clamping action is safe and reliable.

[0030] As shown in Figure 7As shown, the clamping assembly two 3 includes a base 31, a latch 32, a V-shaped support assembly 33 and a locking cylinder two 34, the base 31 is fixedly installed on the extension rod 11 and is fastened by hand screws, convenient to replace. The locking cylinder two 34 is fixedly installed on the base 31, the output end is fixedly connected with the V-shaped support assembly 33, the upper end of the V-shaped support assembly 33 is connected with two latches 32, the lower end of the aero-engine 5 body has a diffuser casing positioning hole 52, the V-shaped support assembly 33 drives the latch to reciprocate linearly under the driving of the locking cylinder two 34, realizes that the latch inserts or exits the diffuser casing positioning hole 52 of the aero-engine 5.

[0031] The model of the locking cylinder one 24 and the locking cylinder two 34 is CDLQB25-45DCM, it has spring lock holding force, has the function of air cut-off self-locking, under the condition of air cut-off and power cut-off, the cylinder still keeps the clamping state, prevents product from falling off, and has manual unlocking function, can manually unlock.

[0032] It can be understood that the utility model is described through some embodiments, and those skilled in the art know that various changes or equivalent replacements can be made to these features and embodiments without departing from the spirit and scope of the utility model.In addition, under the guidance of the utility model, these features and embodiments can be modified to adapt to specific conditions and materials without departing from the spirit and scope of the utility model.Therefore, the utility model is not limited by the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of the present application belong to the scope protected by the utility model.

Claims

1. An automatic clamping mechanism for an aircraft engine mounting fitting, characterized in that, The utility model provides a kind of aviation engine clamping device, including semicircular base (1), two clamping components one (2) and a clamping component two (3), the semicircular base (1) is installed on rotating unit (4), can be rotated under the driving of rotating unit (4), two clamping components one (2) are fixedly installed in semicircular base (1) both ends, the semicircular base (1) middle extends to one side and is fixed with an extension rod, the clamping component two (3) is fixed in semicircular arc base side by an extension rod, the clamping component one (2) and clamping component two (3) realize the clamping of the both ends and middle of aviation engine (5) fixed.

2. The automatic clamping mechanism for aero-engine assembly mounting joint according to claim 1, characterized in that, The clamping component one (2) includes fixed seat (21), upper pressing plate (22), linear shaft (23) and lock cylinder one (24), the fixed seat (21) is fixedly installed in semicircular base (1) both ends, the linear shaft (23) is fixedly installed in fixed seat (21), the upper pressing plate (22) is slidably connected with linear shaft (23), the lock cylinder one (24) is connected with upper pressing plate (22), the fixed seat (21) has arc groove (28) in, the both ends of aviation engine (5) are connected with mounting section (51), the mounting section (51) is placed in arc groove (28), the upper pressing plate (22) has through hole (221) for mounting section (51) to pass through in middle, the lock cylinder one (24) exports linear motion to drive upper pressing plate (22) reciprocating linear motion, the upper pressing plate (22) moves from rear side to front side, limits mounting section (51) in the through hole (221) of upper pressing plate (22), realizes the holding of engine mounting section (51).

3. The automatic clamping mechanism for aero-engine mounting lug assembly according to claim 2, characterized in that, The fixed seat (21) includes bottom plate (211), front side plate (212) and rear side plate (213), the front side plate (212) and rear side plate (213) are fixed on the both sides of bottom plate (211), and are connected by linear shaft (23) between, the lock cylinder one (24) is fixedly installed on front side plate (212), the front side plate (212) has arc groove (28) in middle and bottom plate (211) front end, the output end of lock cylinder one (24) is fixedly connected with upper pressing plate (22) by an L-shaped connecting plate (25).

4. The automatic clamping mechanism for aero-engine mounting lug assembly according to claim 3, characterized in that, The upper pressing plate (22) is provided with a rotation-stopping pin (222) on the top, and the mounting section (51) has a cross-shaped V-shaped notch (511) at the end, which cooperates with the rotation-stopping pin (222). After the upper pressing plate (22) moves into the mounting section (51), the rotation-stopping pin (222) is clamped into the cross-shaped V-shaped notch (511) of the mounting section (51), preventing the product from rotating during clamping.

5. The automatic clamping mechanism for aero-engine mounting lug assembly as claimed in claim 3, wherein, The semicircular base (1) is also fixed with a shearing pin (26) and a push cylinder (27) inside both ends, the output end of the push cylinder (27) is fixedly connected with the shearing pin (26), the mounting section (51) has a shearing pin hole (512), and the shearing pin (26) extends into the shearing pin hole (512) of the mounting section (51) under the action of the push cylinder (27), thereby realizing the axial fixation of the mounting section (51).

6. The automatic clamping mechanism for aero-engine assembly mounting joint as claimed in claim 1, wherein, The clamping assembly two (3) comprises a base (31), a latch (32), a V-shaped support assembly (33) and a locking cylinder two (34), the base (31) is fixedly installed on the extension rod, the locking cylinder two (34) is fixedly installed on the base (31), the output end is fixedly connected with the V-shaped support assembly (33), the upper end of the V-shaped support assembly (33) is connected with two latches (32), the lower end of the aero-engine (5) body has a diffuser casing positioning hole (52), the V-shaped support assembly (33) drives the latch (32) to reciprocate linearly under the drive of the locking cylinder two (34), so that the latch (32) is inserted into or withdrawn from the diffuser casing positioning hole (52) of the aero-engine (5).

7. The automatic clamping mechanism for aero-engine assembly mounting joint according to claim 6, characterized in that, The base (31) is fastened with the extension rod by hand screwing, so that replacement is facilitated.

8. The automatic clamping mechanism for aero-engine mounting lug assembly as claimed in claim 2, wherein, The locking cylinder one (24) and the locking cylinder two (34) are CDLQB25-45DCM.

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