CN114687546B - Aeroengine assembly platform - Google Patents
Aeroengine assembly platform Download PDFInfo
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- CN114687546B CN114687546B CN202210613844.8A CN202210613844A CN114687546B CN 114687546 B CN114687546 B CN 114687546B CN 202210613844 A CN202210613844 A CN 202210613844A CN 114687546 B CN114687546 B CN 114687546B
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- platform
- aircraft engine
- sliding
- rack
- linkage rod
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- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04G—SCAFFOLDING; FORMS; SHUTTERING; BUILDING IMPLEMENTS OR AIDS, OR THEIR USE; HANDLING BUILDING MATERIALS ON THE SITE; REPAIRING, BREAKING-UP OR OTHER WORK ON EXISTING BUILDINGS
- E04G1/00—Scaffolds primarily resting on the ground
- E04G1/15—Scaffolds primarily resting on the ground essentially comprising special means for supporting or forming platforms; Platforms
- E04G1/152—Platforms made of metal or with metal-supporting frame
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
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- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04G—SCAFFOLDING; FORMS; SHUTTERING; BUILDING IMPLEMENTS OR AIDS, OR THEIR USE; HANDLING BUILDING MATERIALS ON THE SITE; REPAIRING, BREAKING-UP OR OTHER WORK ON EXISTING BUILDINGS
- E04G1/00—Scaffolds primarily resting on the ground
- E04G1/18—Scaffolds primarily resting on the ground adjustable in height
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- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04G—SCAFFOLDING; FORMS; SHUTTERING; BUILDING IMPLEMENTS OR AIDS, OR THEIR USE; HANDLING BUILDING MATERIALS ON THE SITE; REPAIRING, BREAKING-UP OR OTHER WORK ON EXISTING BUILDINGS
- E04G5/00—Component parts or accessories for scaffolds
- E04G5/14—Railings
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Mechanical Engineering (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses an aircraft engine assembly platform which comprises a bottom platform, stand columns, an upper platform, an aircraft engine supporting mechanism and a control box, wherein the stand columns are arranged at the four corners of the bottom platform in a one-to-one correspondence manner; the top of the aero-engine supporting mechanism penetrates through the upper platform; the aircraft engine supporting mechanism comprises two supporting seats and an angle rotating clamping mechanism arranged on the supporting seats; the aero-engine is arranged on the angle rotating clamping mechanism. Through the scheme, the invention has the advantages of simple structure, convenience and quickness in use, reliability in installation and operation and the like, and has very high practical value and popularization value in the field of aeroengines.
Description
Technical Field
The invention relates to the technical field of aero-engine installation, in particular to an aero-engine assembling platform.
Background
At present, the installation of an aircraft engine in the prior art generally comprises two modes: firstly, assembly of a certain part is realized by using a universal hoisting device and a universal platform and adding a manual auxiliary cushion block. And secondly, a simple mounting platform is manufactured, and the assembly of parts of fixed stations is realized.
Both of these approaches have their inherent drawbacks:
the first mode is complicated to operate, low in efficiency and accompanied by unpredictable potential safety hazards.
The second approach suffers from the following disadvantages:
first, poor applicability, slight modifications of parts, and possible mismatch of mounting platforms. Secondly, the transfer is troublesome during the multistation assembly, and is inefficient, and the place utilization ratio is low. And thirdly, the operation, debugging and design of the parts are inconvenient to carry out multi-station and multi-angle observation and analysis.
Therefore, an aircraft engine assembly platform which is simple in structure, convenient to use, reliable in installation and operation and capable of achieving any angle and any station is urgently needed.
Disclosure of Invention
Aiming at the problems, the invention aims to provide an aircraft engine assembling platform, and the technical scheme adopted by the invention is as follows:
an aircraft engine assembly platform is used for carrying an aircraft engine to be installed and comprises a bottom platform, stand columns which are arranged at four corners of the bottom platform in a one-to-one correspondence mode, an upper platform which is arranged on the stand columns and ascends and descends along the direction of the stand columns, an aircraft engine supporting mechanism which is arranged in the middle of the bottom platform and used for carrying the aircraft engine to be installed, and a control box which is connected with the upper platform and the aircraft engine supporting mechanism; the top of the aero-engine supporting mechanism penetrates through the upper platform;
the aero-engine support mechanism comprises two support seats and an angle rotation clamping mechanism arranged on the support seats; the aero-engine is arranged on the angle rotating clamping mechanism.
Furthermore, a guardrail is arranged on the periphery of the upper part of the upper platform; an escalator is arranged between the upper platform and the bottom platform.
Furthermore, the angle rotating clamping mechanism comprises a first speed reducer arranged on the supporting seats, a first motor connected with the first speed reducer, a connecting seat arranged between the two supporting seats, connected with the first speed reducer and driven by the first motor to rotate, arc-shaped supporting seats connected with the two connecting seats, and clamps arranged on the arc-shaped supporting seats and the connecting seats in a one-to-one correspondence manner; the clamp is extruded on the outer edge of the aircraft engine.
Furthermore, the clamp comprises a gear rack mechanism, a first operating plate connected with the gear rack mechanism, and an extrusion head connected with the gear rack mechanism and facing to the outer edge of the aircraft engine; the first operating disk drives the extrusion head to stretch and retract along the radial direction of the aircraft engine.
Preferably, the bottom of the bottom platform is provided with a plurality of universal wheels; and the bottom platform is provided with a traction connecting mechanism.
Furthermore, a hollow part is arranged in the upper platform; the top of the aero-engine support mechanism is arranged in the hollow part of the upper platform.
Furthermore, the upper platform comprises a second sliding rail sliding seat component and a second rack which are arranged on any stand column along the direction of the stand column, a sliding seat which is sleeved on the stand column and connected with the second sliding rail sliding seat component and the second rack, an operating platform which is arranged on the sliding seat, and a lifting driving mechanism which is arranged at the bottom of the operating platform and drives the operating platform to lift along the direction of the second rack.
Furthermore, the lifting driving mechanism comprises a second worm and gear speed reducing mechanism fixed at the bottom of the operation platform, a second motor connected with the second worm and gear speed reducing mechanism, a third linkage rod in transmission connection with the second motor, second commutators arranged at the end parts of the third linkage rod in a one-to-one correspondence manner, a fourth linkage rod with one end connected with the second commutators, and a second bearing seat fixed at the bottom of the operation platform and connected with the middle part of the fourth linkage rod; a second gear connected with a second commutator is arranged in the sliding seat; the second gear is in meshed connection with the second rack.
Furthermore, two groups of sliding shielding plates and sliding driving mechanisms are arranged at the bottom of the upper platform; any group of sliding shielding plates can shield the local space of the hollow part at one side of the sliding shielding plate after sliding and recovering.
Furthermore, the sliding driving mechanism comprises a first worm and gear speed reducing mechanism fixed at the bottom of the operating platform, a second operating panel connected with the first worm and gear speed reducing mechanism and extending to the operating platform, a first linkage rod connected with the first worm and gear speed reducing mechanism at the middle part, first commutators arranged at the end parts of the first linkage rod in a one-to-one correspondence manner, a second linkage rod connected with the first commutators at one end, a first bearing seat arranged at the other end of the second linkage rod and fixed at the bottom of the operating platform, a first rack arranged at the bottom of the sliding shielding plate, a first gear arranged on the second linkage rod and meshed and connected with the first rack, and a plurality of first sliding rail sliding seat assemblies arranged between the sliding shielding plate and the operating platform; the first sliding rail sliding seat assembly is arranged along the direction of the first rack.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention skillfully arranges the upper platform, and arranges the lifting driving mechanism and the sliding driving mechanism shielded by the hollow part on the platform so as to realize the lifting of the platform and the penetration space when the aeroengine rotates and changes positions, thereby ensuring that the aeroengine is more reliably installed;
(2) the aero-engine support mechanism is arranged, the clamp is used for clamping and fixing, the first motor is used for driving the aero-engine to change the angle, so that the longitudinal position and the transverse position of the aero-engine are reversed, and the reliable installation and disassembly are ensured;
in conclusion, the invention has the advantages of simple structure, convenient use, reliable installation and operation and the like, and has very high practical value and popularization value in the field of aeroengines.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope of protection, and it is obvious for those skilled in the art that other related drawings can be obtained according to these drawings without inventive efforts.
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic front view of the present invention.
FIG. 3 is a left side view of a partial structure of the present invention.
Fig. 4 is a left-view partial structural diagram (ii) of the present invention.
Fig. 5 is a right-view partial structural diagram of the present invention.
FIG. 6 is a schematic structural view of an aircraft engine support mechanism of the present invention.
In the drawings, the names of the parts corresponding to the reference numerals are as follows:
1. a bottom platform; 2. a column; 3. a guardrail; 4. an aircraft engine support mechanism; 5. an escalator; 6. a control box; 7. an upper platform; 11. a traction connection mechanism; 12. a universal wheel; 21. a second slide rail carriage assembly; 22. a second rack; 41. a supporting seat; 42. a first decelerator; 43. a first motor; 44. a connecting seat; 45. an arc-shaped supporting seat; 461. a rack and pinion mechanism; 462. a first operation panel; 463. an extrusion head; 70. an operating platform; 71. a sliding shutter; 72. a coasting drive mechanism; 73. a lifting drive mechanism; 721. a first worm gear reduction mechanism; 722. a second operation panel; 723. a first linkage rod; 724. a first commutator; 725. a second linkage rod; 726. a first gear; 727. a first bearing housing; 728. a first rack; 729. a first slide rail slide carriage assembly; 731. a second worm gear reduction mechanism; 732. a second motor; 733. a third link lever; 734. a second commutator; 736. a second bearing housing; 737. a fourth link lever; 738. a slide base; 739. a second gear.
Detailed Description
To further clarify the objects, technical solutions and advantages of the present application, the present invention will be further described with reference to the accompanying drawings and examples, and embodiments of the present invention include, but are not limited to, the following examples. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Examples
As shown in fig. 1 to 6, the present embodiment provides an aircraft engine mounting platform for mounting an aircraft engine to be mounted. First, the terms "first", "second", and the like in the present embodiment are used only for distinguishing the same kind of components, and are not to be construed as specifically limiting the scope of protection. In the present embodiment, the terms of orientation such as "bottom", "top", "edge", "center", and the like are explained based on the drawings.
In the embodiment, the aircraft engine assembly platform mainly comprises a bottom platform 1, a stand column 2, a guardrail 3, an aircraft engine supporting mechanism 4, a staircase 5, a control box 6 and an upper platform 7. In order to make the platform movable, a plurality of universal wheels 12 are arranged at the bottom of the bottom platform 1, and a traction connecting mechanism 11 is arranged on the bottom platform 1. In the present embodiment, the aircraft engine support mechanism 4 is disposed in the middle of the bottom platform 1 for carrying an aircraft engine to be installed. The aircraft engine supporting mechanism 4 comprises two supporting seats 41 and an angle rotating clamping mechanism arranged on the supporting seats 41; the aero-engine is arranged on the angle rotating clamping mechanism.
In this embodiment, the aero-engine support mechanism 4 needs to switch the aero-engine longitudinally and transversely, and then, a hollow portion is provided in the upper platform 7; the top of the aero-engine support mechanism 4 is placed in the hollow portion of the upper platform 7. In order to ensure the reliable position change of the aero-engine, the hollow part comprises a central hole in the middle and rectangular holes on two sides.
In this embodiment, in order to realize the direction switching of the aircraft engine, the angular rotation clamping mechanism includes a first speed reducer 42 disposed on the support base 41, a first motor 43 connected to the first speed reducer 42, a connecting base 44 disposed between the two support bases 41, connected to the first speed reducer 42, and driven to rotate by the first motor 43, an arc-shaped support base 45 connected to the two connecting bases 44, and clamps disposed on the arc-shaped support base 45 and the connecting base 44 in a one-to-one correspondence; the clamp is extruded on the outer edge of the aircraft engine. Wherein, any one of the clamps comprises a rack and pinion mechanism 461, a first operating plate 462 connected with the rack and pinion mechanism 461, and a pressing head 463 connected with the rack and pinion mechanism 461 and facing the outer edge of the aircraft engine; the first operating plate 462 drives the extrusion head 463 to extend and retract in the radial direction of the aircraft engine. The first motor 43 drives the first speed reducer 42 to rotate, and drives the arc-shaped supporting seat 45 and the three clamps to rotate, so that the direction of the aircraft engine is switched.
In this embodiment, the upper platform 7 needs to be lifted, and then, the upper platform 7 includes a second slide rail slide carriage assembly 21 and a second rack 22 that are arranged on any one of the columns 2 along the direction of the column 2, a slide carriage 738 that is sleeved on the column 2 and is connected with the second slide rail slide carriage assembly 21 and the second rack 22, an operating platform 70 that is arranged on the slide carriage 738, and a lifting driving mechanism 73 that is arranged at the bottom of the operating platform 70 and drives the operating platform 70 to lift along the direction of the second rack 22. The lifting driving mechanism 73 includes a second worm gear speed reducing mechanism 731 fixed at the bottom of the operation platform 70, a second motor 732 connected to the second worm gear speed reducing mechanism 731, a third linkage 733 in transmission connection with the second motor 732, second commutators 734 arranged at the end portions of the third linkage 733 in one-to-one correspondence, a fourth linkage 737 having one end connected to the second commutators 734, and a second bearing seat 736 fixed at the bottom of the operation platform 70 and connected to the middle portion of the fourth linkage 737; a second gear 739 connected with the second commutator 734 is arranged in the sliding base 738; the second gear 739 is engaged with the second rack 22. In this embodiment, the second motor 732 is used to drive the second worm gear speed reducer 731, the second commutator 734, the third link 733, and the fourth link 737 to rotate, and drive the second gear 739 to move in engagement with the second rack 22, so as to lift the operation platform 70.
In addition, in the present embodiment, when rectangular holes on both sides of the hollow portion need to be shielded, the rectangular holes are shielded by two sets of sliding shielding plates 71 and sliding driving mechanisms 72 at the bottom of the upper platform 7; any one set of sliding shielding plates 71 slides and recovers to shield a partial space of the hollow portion on the side where the sliding shielding plates 71 are located. The sliding driving mechanism 72 comprises a first worm and gear speed reducing mechanism 721 fixed at the bottom of the operating platform 70, a second operating panel 722 connected with the first worm and gear speed reducing mechanism 721 and extending to the operating platform 70, a first linkage 723 the middle of which is connected with the first worm and gear speed reducing mechanism 721, a first commutator 724 arranged at the end of the first linkage 723 in a one-to-one correspondence manner, a second linkage 725 with one end connected with the first commutator 724, a first bearing seat 727 arranged at the other end of the second linkage 725 and fixed at the bottom of the operating platform 70, a first rack 728 arranged at the bottom of the sliding shutter 71, a first gear 726 arranged on the second linkage 725 and engaged with the first rack 728, and a plurality of first sliding rail sliding seat assemblies 729 arranged between the sliding shutter 71 and the operating platform 70; the first sled carriage assembly 729 is disposed along the first rack 728. In the present embodiment, the second operation panel 722 is used to drive the first worm gear speed reducer 721, the first linkage rod 723, and the second linkage rod 725 to rotate, and drive the first gear 726 to engage with the first rack 728 to travel, so as to drive the sliding shielding plate 71 to shield or leak out of the rectangular hole.
The above-described embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention, but all changes that can be made by applying the principles of the present invention and performing non-inventive work on the basis of the principles shall fall within the scope of the present invention.
Claims (7)
1. An aircraft engine assembly platform is used for carrying aircraft engines to be installed and is characterized by comprising a bottom platform (1), stand columns (2) which are arranged at four corners of the bottom platform (1) in a one-to-one correspondence manner, an upper platform (7) which is arranged on the stand columns (2) and ascends and descends along the directions of the stand columns (2), an aircraft engine supporting mechanism (4) which is arranged in the middle of the bottom platform (1) and is used for carrying the aircraft engines to be installed, and a control box (6) which is connected with the upper platform (7) and the aircraft engine supporting mechanism (4); the top of the aero-engine supporting mechanism (4) penetrates through the upper platform (7) to be arranged;
the aircraft engine supporting mechanism (4) comprises two supporting seats (41) and an angle rotating clamping mechanism arranged on the supporting seats (41); the aero-engine is arranged on the angle rotating clamping mechanism;
a hollow part is arranged in the upper platform (7); the top of the aero-engine support mechanism (4) is arranged in the hollow part of the upper platform (7);
two groups of sliding shielding plates (71) and sliding driving mechanisms (72) are arranged at the bottom of the upper platform (7); any group of sliding shielding plates (71) can shield the local space of the hollow part at one side of the sliding shielding plate (71) after sliding recovery;
the sliding driving mechanism (72) comprises a first worm and gear speed reducing mechanism (721) fixed at the bottom of the operating platform (70), a second operating disk (722) connected with the first worm and gear speed reducing mechanism (721) and extending to the operating platform (70), a first linkage rod (723) with the middle connected with the first worm and gear speed reducing mechanism (721), first commutators (724) arranged at the end parts of the first linkage rod (723) in a one-to-one correspondence manner, a second linkage rod (725) with one end connected with the first commutators (724), first bearing seats (727) arranged at the other end of the second linkage rod (725) and fixed at the bottom of the operating platform (70), a first rack (728) arranged at the bottom of the sliding shielding plate (71), a first gear (726) arranged on the second linkage rod (725) and connected with the first rack (728) in a meshing manner, and a plurality of first sliding rail sliding slide group sliding seats arranged between the shielding plate (71) and the operating platform (70) A member (729); the first sled carriage assembly (729) is disposed along the first rack (728).
2. An aircraft engine assembly platform according to claim 1, characterised in that the upper peripheral edge of the upper platform (7) is provided with a guard rail (3); an escalator (5) is arranged between the upper platform (7) and the bottom platform (1).
3. An aircraft engine assembly platform according to claim 1 or 2, wherein the angle rotation clamping mechanism comprises a first speed reducer (42) arranged on the support base (41), a first motor (43) connected with the first speed reducer (42), a connecting base (44) arranged between the two support bases (41), connected with the first speed reducer (42) and driven to rotate by the first motor (43), an arc-shaped support base (45) connected with the two connecting bases (44), and clamps arranged on the arc-shaped support base (45) and the connecting base (44) in a one-to-one correspondence manner; the clamp is extruded on the outer edge of the aircraft engine.
4. An aircraft engine assembly platform according to claim 3, characterised in that the clamp comprises a rack and pinion mechanism (461), a first operating plate (462) connected to the rack and pinion mechanism (461), and a pressing head (463) connected to the rack and pinion mechanism (461) and facing towards the outer edge of the aircraft engine; the first operating plate (462) drives the extrusion head (463) to extend and retract along the radial direction of the aircraft engine.
5. An aircraft engine assembly platform according to claim 1, characterised in that the bottom of the bottom platform (1) is provided with a plurality of universal wheels (12); and a traction connecting mechanism (11) is arranged on the bottom platform (1).
6. The aircraft engine assembly platform according to claim 1, wherein the upper platform (7) comprises a second sliding rail sliding seat component (21) and a second rack (22) which are arranged on any one upright (2) along the direction of the upright (2), a sliding seat (738) which is sleeved on the upright (2) and is connected with the second sliding rail sliding seat component (21) and the second rack (22), an operating platform (70) which is arranged on the sliding seat (738), and a lifting driving mechanism (73) which is arranged at the bottom of the operating platform (70) and drives the operating platform (70) to lift along the direction of the second rack (22).
7. The aircraft engine assembly platform of claim 6, wherein the lifting driving mechanism (73) comprises a second worm gear speed reducing mechanism (731) fixed at the bottom of the operating platform (70), a second motor (732) connected with the second worm gear speed reducing mechanism (731), a third linkage rod (733) in transmission connection with the second motor (732), a second commutator (734) arranged at the end part of the third linkage rod (733) in a one-to-one correspondence manner, a fourth linkage rod (737) with one end connected with the second commutator (734), and a second bearing seat (736) fixed at the bottom of the operating platform (70) and connected with the middle part of the fourth linkage rod (737); a second gear (739) connected with a second commutator (734) is arranged in the sliding seat (738); the second gear (739) is meshed with the second rack (22).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210613844.8A CN114687546B (en) | 2022-06-01 | 2022-06-01 | Aeroengine assembly platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210613844.8A CN114687546B (en) | 2022-06-01 | 2022-06-01 | Aeroengine assembly platform |
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| Publication Number | Publication Date |
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| CN114687546A CN114687546A (en) | 2022-07-01 |
| CN114687546B true CN114687546B (en) | 2022-08-12 |
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| CN202210613844.8A Active CN114687546B (en) | 2022-06-01 | 2022-06-01 | Aeroengine assembly platform |
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| CN113953736A (en) * | 2021-08-29 | 2022-01-21 | 欧兰容 | Welding system based on industrial manufacturing |
| CN113736969A (en) * | 2021-09-28 | 2021-12-03 | 安徽理工大学 | Dual-purpose ultrasonic shot peening strengthening device for round rod and flat-plate-shaped test piece |
| CN216577573U (en) * | 2021-12-30 | 2022-05-24 | 浙江星舰工业自动化有限公司 | Multi-angle overturning fixture for aero-engine production |
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