CN108791950B - Assembly equipment for assembling large-scale parts of airplane - Google Patents
Assembly equipment for assembling large-scale parts of airplane Download PDFInfo
- Publication number
- CN108791950B CN108791950B CN201810672589.8A CN201810672589A CN108791950B CN 108791950 B CN108791950 B CN 108791950B CN 201810672589 A CN201810672589 A CN 201810672589A CN 108791950 B CN108791950 B CN 108791950B
- Authority
- CN
- China
- Prior art keywords
- aircraft
- sliding seat
- fixedly connected
- crane
- rotating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000008093 supporting effect Effects 0.000 claims abstract description 87
- 230000007246 mechanism Effects 0.000 claims description 20
- 230000001154 acute effect Effects 0.000 claims description 6
- 230000000712 assembly Effects 0.000 claims description 5
- 238000000429 assembly Methods 0.000 claims description 5
- 230000009471 action Effects 0.000 claims description 4
- 230000005484 gravity Effects 0.000 claims description 4
- 210000001503 joint Anatomy 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 4
- 230000003028 elevating effect Effects 0.000 description 9
- 230000003014 reinforcing effect Effects 0.000 description 7
- 208000027418 Wounds and injury Diseases 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000006378 damage Effects 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
- B66D3/00—Portable or mobile lifting or hauling appliances
- B66D3/12—Chain or like hand-operated tackles with or without power transmission gearing between operating member and lifting rope, chain or cable
- B66D3/14—Chain or like hand-operated tackles with or without power transmission gearing between operating member and lifting rope, chain or cable lever operated
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
- B66D2700/00—Capstans, winches or hoists
- B66D2700/01—Winches, capstans or pivots
- B66D2700/0116—Manually or spring operated winches
Abstract
The invention discloses assembly equipment for assembling large-sized components of an airplane, which comprises a front assembly fixture and a rear assembly fixture, wherein the front assembly fixture comprises a front bracket main body, a front lifting device for controlling the large-sized components of the airplane to lift and a front rotating device which is rotatably arranged on the front lifting device and is used for supporting the large-sized components of the airplane at one end of the large-sized components of the airplane, and the rear assembly fixture comprises a rear bracket main body, a rear lifting device for controlling the large-sized components of the airplane to lift and a rear rotating device which is rotatably arranged on the rear lifting device and is used for supporting the large-sized components of the airplane at the other end of the large-sized components of the airplane. According to the assembly equipment for assembling the large-sized components of the airplane, the front assembly tool and the rear assembly tool are arranged to be matched, so that the large-sized components of the airplane can be supported, lifted and rotated, the large-sized components of the airplane can be assembled with other components conveniently, and the assembly work efficiency of the large-sized components of the airplane is improved.
Description
Technical Field
The invention belongs to the technical field of general aviation auxiliary equipment, and particularly relates to assembly equipment for assembling large-sized parts of an aircraft.
Background
During the manufacturing process of an aircraft, assembly of components and large parts (such as fuselage, wings) of the aircraft requires assistance of assembly tooling; alternatively, the components and large parts of the aircraft are assembled on an assembly fixture. The existing auxiliary tool for aircraft assembly mainly adopts a bracket type, the aircraft is jacked up from the lower part, and then a special operation platform is manufactured.
Although the existing aircraft assembly auxiliary tool solves the problem that large parts can be assembled simultaneously, the following practical problems still exist in the practical assembly production process: 1. the assembly type rack has higher manufacturing cost, different type racks are required to be manufactured according to different parts, and the different type racks have no good applicability; 2. after the assembly is completed, a plurality of people are required to cooperate when the workpiece is taken out from the bracket, so that the problems of sliding injury and the like on the surface of the workpiece are easily caused; 3. the workpiece is generally horizontally placed, and compared with a part of assembly work, the workpiece can cause smaller operation space, and the problems of higher assembly difficulty and the like are solved.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems existing in the prior art. Therefore, the invention provides assembly equipment for assembling large parts of an aircraft, and aims to facilitate assembly operation of the large parts of the aircraft.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: the assembly equipment for assembling the large-sized components of the aircraft comprises a front assembly fixture and a rear assembly fixture which are arranged in a relative manner, wherein the front assembly fixture comprises a front bracket main body, a front lifting device which is arranged on the front bracket main body and used for controlling the large-sized components of the aircraft to lift and a front rotating device which is arranged on the front lifting device and used for providing support for the large-sized components of the aircraft at one end of the large-sized components of the aircraft, and the rear assembly fixture comprises a rear bracket main body, a rear lifting device which is arranged on the rear bracket main body and used for controlling the large-sized components of the aircraft to lift and a rear rotating device which is arranged on the rear lifting device and used for providing support for the large-sized components of the aircraft at the other end of the large-sized components of the aircraft.
The front lifting device comprises a front sliding seat and a front lifting control mechanism, wherein the front sliding seat is movably arranged on the front bracket main body, the front lifting control mechanism is connected with the front sliding seat and used for controlling the front sliding seat to move along the vertical direction, the front rotating device is rotationally connected with the front sliding seat, and the rotation center line of the front rotating device is parallel to the first direction.
The front lifting control mechanism comprises a front fixed pulley arranged on the front bracket main body, a front inhaul cable which is connected with the front sliding seat and bypasses the front fixed pulley, and a front crane for controlling the front inhaul cable to release and roll.
The front crane is arranged on the front bracket main body, is positioned below the front fixed pulley and is a hand-operated crane.
The front rotating device comprises a front rotating frame and a front supporting piece, wherein the front rotating frame is rotationally connected with the front lifting device, and the front supporting piece is arranged on the front rotating frame and used for being connected with the large-scale part of the airplane.
The front rotating frame comprises a front bracket connected with the front supporting piece and a front rotating rod connected with the front bracket and rotationally connected with the front lifting device, and the front bracket is provided with a plurality of front brackets and all the front brackets are distributed around the outer side of the front supporting piece.
The rear lifting device comprises a rear sliding seat and a rear lifting control mechanism, wherein the rear sliding seat is movably arranged on the rear bracket main body, the rear lifting control mechanism is connected with the rear sliding seat and used for controlling the rear sliding seat to move along the vertical direction, the rear rotating device is rotationally connected with the rear sliding seat, and the rotation center line of the rear rotating device is parallel to the first direction.
The rear lifting control mechanism comprises a rear fixed pulley arranged on the rear bracket main body, a rear stay rope which is connected with the rear sliding seat and bypasses the rear fixed pulley, and a rear crane for controlling the rear stay rope to release and roll.
The large-scale part of aircraft is the aircraft fuselage, back rotary device include with back rotary frame that back elevating gear rotates to be connected and set up and be used for the back support piece of being connected with the large-scale part of aircraft on the back rotary frame, back elevating gear has and lets a locking pin insert so that back rotary device and back elevating gear keep relatively fixed's locking hole, back rotary frame has and lets locking pin male mounting hole, and the mounting hole sets up a plurality of and all mounting holes for following circumference evenly distributed.
The rear support piece comprises a first rear support rod connected with the rear rotating frame and a second rear support rod connected with the first rear support rod and used for being connected with the large-scale part of the airplane through bolts, the second rear support rod extends towards the upper side of the first rear support rod, the rear support rod is provided with a first bolt hole, a second bolt hole and a third bolt hole, the bolts penetrate through the first bolt hole, the second bolt hole and the third bolt hole, and the first bolt hole and the second bolt hole are located above the third bolt hole.
According to the assembly equipment for assembling the large-sized components of the aircraft, the front assembly tool and the rear assembly tool are arranged to be matched, so that the large-sized components of the aircraft can be supported, lifted and rotated, operators can operate in a large range, the large-sized components of the aircraft and other components can be assembled conveniently, the structure is simple, the use is convenient, the cost is low, the maintenance is easy, and the assembly work efficiency of the large-sized components of the aircraft is improved.
Drawings
The present specification includes the following drawings, the contents of which are respectively:
FIG. 1 is a schematic view of the use of the assembly apparatus for assembling large parts of an aircraft of the present invention;
FIG. 2 is a schematic structural view of a front assembly fixture;
FIG. 3 is a schematic view of a front assembly tooling at another angle;
FIG. 4 is a front view of a front assembly fixture;
FIG. 5 is a schematic structural view of a post-assembly tooling;
FIG. 6 is a schematic view of a structure of a rear assembly fixture at another angle;
FIG. 7 is a front view of the rear assembly fixture;
marked in the figure as: 1. an aircraft fuselage; 2. a front bracket main body; 201. a front base; 202. casters; 203. a front upright; 204. a front top plate; 205. a front guide bar; 3. a front sliding seat; 4. a rear sliding seat; 5. a front rotating device; 501. a front support; 502. a front rotating rod; 503. a first connecting rod; 504. a second connecting rod; 505. a third connecting rod; 506. a front rotating shaft; 507. a reinforcing rod; 6. a rear rotating device; 601. a rear rotating frame; 602. a mounting hole; 603. a rear rotating shaft; 604. a first rear support bar; 605. a second rear support bar; 606. a first bolt hole; 607. a second bolt hole; 608. a third bolt hole; 7. a rear bracket main body; 701. a rear base; 702. casters; 703. a rear pillar; 704. a rear top plate; 705. a rear guide bar; 8. a front crane; 9. a front guy cable; 10. a front fixed pulley; 11. a rear crane; 12. a rear stay; 13. a rear fixed pulley; 14. a locking pin; 15. and a limiting plate.
Detailed Description
The following detailed description of the embodiments of the invention, given by way of example only, is presented in the accompanying drawings to aid in a more complete, accurate and thorough understanding of the concepts and aspects of the invention, and to aid in its practice, by those skilled in the art.
As shown in fig. 1 to 7, the present invention provides an assembly apparatus for assembling a large-sized component of an aircraft, comprising a front assembly fixture and a rear assembly fixture which are arranged in opposition, the front assembly fixture comprising a front bracket body 2, a front lifting device which is provided on the front bracket body 2 and is used for controlling the large-sized component of the aircraft to lift, and a front rotating device 5 which is rotatably provided on the front lifting device and is used for supporting the large-sized component of the aircraft at one end of the large-sized component of the aircraft, the rear assembly fixture comprising a rear bracket body 7, a rear lifting device which is provided on the rear bracket body 7 and is used for controlling the large-sized component of the aircraft to lift, and a rear rotating device 6 which is rotatably provided on the rear lifting device and is used for providing support for the large-sized component of the aircraft at the other end of the large-sized component of the aircraft.
Specifically, as shown in fig. 1 to 7, the large-sized component of the aircraft is an aircraft body, the front assembly fixture is used for connecting one end of the aircraft body for installing an aircraft nose with the aircraft body, the rear assembly fixture is used for connecting the other end of the aircraft body (i.e. the tail of the aircraft body) with the aircraft body, and when the large-sized component of the aircraft is used, the front assembly fixture and the rear assembly fixture are positioned on the same straight line parallel to a first direction, and the first direction is a horizontal direction. The front assembly tool is matched with the rear assembly tool and is used for supporting an aircraft fuselage together, lifting and rotating of the aircraft fuselage can be achieved together, the aircraft fuselage is assembled with other parts conveniently, the other parts are middle wing assemblies, the middle wing assemblies are mainly formed by connecting a fuselage bilge (the lower part of the aircraft fuselage is provided with a part which is fixedly connected with the aircraft fuselage), a middle wing box and an engine cabin, the middle wing box and the engine cabin are two, each middle wing box is respectively located between one engine cabin and the fuselage bilge, and each middle wing box is fixedly connected with one engine cabin and the fuselage bilge to form the middle wing assembly.
As shown in fig. 1 to 4, the front lifting device includes a front sliding seat 3 movably disposed on the front bracket main body 2 and a front lifting control mechanism connected with the front sliding seat 3 and used for controlling the front sliding seat 3 to move along a vertical direction, the front rotating device 5 is rotatably connected with the front sliding seat 3, a rotation center line of the front rotating device 5 is parallel to the first direction, and a moving direction of the front lifting device is the vertical direction. The front rotating device 5 is rotatable relative to the front sliding seat 3, the front sliding seat 3 can drive the front rotating device 5 to synchronously move along the vertical direction, and then the rotation and lifting of the large-sized part of the airplane can be realized, the height position and the gesture of the large-sized part of the airplane can be adjusted, and the assembly with the middle wing assembly is convenient.
As shown in fig. 1 to 4, the front sliding seat 3 is slidably connected with the front bracket main body 2, the front bracket main body 2 plays a role in guiding the front sliding seat 3, the front sliding seat 3 has a sliding groove, the sliding groove is a long groove extending in the vertical direction on the front sliding seat 3, at least two parallel sliding grooves are arranged, and a part of the front bracket main body 2 is embedded into the sliding groove on the front sliding seat 3, so that the front sliding seat 3 can be guided, and the front sliding seat 3 and the front rotating device 5 can be ensured to operate stably.
As shown in fig. 1 to 4, the front elevation control mechanism includes a front fixed pulley 10 provided on the front bracket main body 2, a front cable 9 connected to the front sliding seat 3 and bypassing the front fixed pulley 10, and a front crane 8 for controlling the front cable 9 to be released and wound up. The front fixed pulley 10 is rotatably arranged on the front bracket main body 2, the front fixed pulley 10 is positioned at the top of the front bracket main body 2, the axis of the front fixed pulley 10 is parallel to the second direction, the second direction is the horizontal direction, and the second direction is perpendicular to the first direction. The front fixed pulley 10 is provided with one, the front guy rope 9 is a steel rope, one end of the front guy rope 9 is fixedly connected with the front sliding seat 3, the other end of the front guy rope 9 is fixedly connected with the front crane 8, the front crane 8 is used for providing driving force for lifting the front lifting device, and the front crane 8 controls the front guy rope 9 to release and roll up. When the front crane 8 rolls up the front stay rope 9, the front stay rope 9 is gradually wound on the front crane 8, and at the moment, the front stay rope 9 pulls the front sliding seat 3 to move upwards along the vertical direction, and the front sliding seat 3 drives the front rotating device 5 to synchronously rise; when the front crane 8 releases the front guy rope 9, the front guy rope 9 is gradually pulled out from the front crane 8, at this time, the front sliding seat 3 moves downwards along the vertical direction under the action of self gravity, the front crane 8 controls the descending speed of the front sliding seat 3, and the front sliding seat 3 drives the front rotating device 5 to synchronously descend.
The front lifting control mechanism is compact in structure and convenient to arrange, the whole volume of the tool can be reduced, compared with other lifting devices formed in the prior art, lifting is realized in a jack mode, the front lifting control mechanism can easily lift the machine body to a higher height, and further the middle wing assembly can be conveniently moved below the machine body of the aircraft, if the machine body is lifted to the same height by the jack mode, the requirement on the jack is higher, the jack is required to be larger and longer, the corresponding jack is heavier, the cost is high, the lifting operation is time-consuming and labor-consuming, and the whole volume of the tool is larger; the front lifting control mechanism is easier to control the height position of the airplane body, is convenient to operate by adopting a hand-operated mode, saves labor and is better in stability.
As shown in fig. 1 to 4, the front crane 8 is disposed on the front bracket main body 2, the front crane 8 is located below the front fixed pulley 10, the front crane 8 is fixedly connected with the front bracket main body 2, the height of the front crane 8 is smaller than that of the front fixed pulley 10, the lower end of the front guy cable 9 is fixedly connected with the lower end of the front sliding seat 3, and the lower end of the front sliding seat 3 is located below the front fixed pulley 10. Preferably, the front crane 8 is a hand-operated crane (also called a hand winch), which is manually rotated by manpower to roll up and release the front guy rope 9, and the structure of the hand-operated crane is well known to those skilled in the art and will not be described herein. The existing hand-operated cranes have an automatic braking function, can realize self-locking, are safer during operation, and can enable large parts of the aircraft to be kept at a set height position. The hand-operated crane is convenient to operate, good in reliability and high in safety, the height position of the large-sized part of the aircraft is conveniently controlled to be adjusted, and the assembly efficiency of the aircraft body and the middle wing assembly is improved.
As shown in fig. 1 to 4, the front rotating device 5 includes a front rotating frame rotatably connected to the front elevating device and a front support 501 provided on the front rotating frame for connection with a large-sized part of the aircraft. The large-scale part of aircraft is the aircraft fuselage, front support piece 501 is used for being connected with the aircraft fuselage at the one end that is used for installing the aircraft fuselage at the aircraft fuselage, front support piece 501's one end is used for forming detachable connection through bolt and aircraft fuselage, make things convenient for the dismouting, front support piece 501's shape is the same with the shape of aircraft fuselage, front support piece 501 is the front circle back point, the surface is smooth, slightly resemble the shape of water droplet, be streamline structure, the suitability with the aircraft fuselage is good, ensure can be connected with the aircraft fuselage reliably, the axis of front support piece 501 is parallel with the axis of preceding pivot 506, front support piece 501's end edge is equipped with the through-hole that lets the bolt pass, the end edge of aircraft fuselage also is equipped with the through-hole that lets the bolt pass. After the end part of the front supporting piece 501 is in butt joint with the end part of the aircraft body, the front supporting piece 501 is fixedly connected with the aircraft body through bolts, after the front supporting piece 501 is connected with the aircraft body into a whole, the front lifting device can drive the aircraft body to synchronously lift through the front rotating device 5, and the front rotating device 5 can drive the aircraft body to rotate relative to the front lifting device.
As shown in fig. 1 to 4, the front rotating frame includes a front bracket connected to the front support 501 and a front rotating lever 502 connected to the front bracket and rotatably connected to the front elevating device, and the front bracket is provided in plurality and all of the front brackets are distributed around the outer side of the front support 501. The front rotating rod 502 is rotatably connected with the front sliding seat 3 through a front rotating shaft 506, the axis of the front rotating shaft 506 (i.e. the rotation center line of the front rotating device 5) is parallel to the first direction, the front rotating rod 502 has a certain length, the length direction of the front rotating rod 502 is perpendicular to the first direction, the front rotating shaft 506 is fixedly connected with the front rotating rod 502 at the middle position of the length direction of the front rotating rod 502, and the upper end of the front sliding seat 3 is provided with a shaft hole for inserting the front rotating shaft 506. The front rotating lever 502 is fixedly connected to the front brackets, all the front brackets are fixedly connected as one body, the front supporting member 501 is fixedly connected to all the front brackets, and in the first direction, the front rotating lever 502 is located between the front supporting member 501 and the front bracket main body 2. Preferably, the front bracket has a U-shaped structure, and includes a first connecting rod 503, a second connecting rod 504, and a third connecting rod 505 sequentially connected, where the first connecting rod 503, the second connecting rod 504, and the third connecting rod 505 have a certain length, the length of the third connecting rod 505 is smaller than that of the first connecting rod 503, the length direction of the second connecting rod 504 is parallel to the first direction, and the length direction of the first connecting rod 503 is perpendicular to the first direction. One end of the second connecting rod 504 of each front bracket is fixedly connected with one end of the first connecting rod 503, the other end of the second connecting rod 504 is fixedly connected with one end of the third connecting rod 505, the other end of the third connecting rod 505 is fixedly connected with the front supporting member 501, the other end of the first connecting rod 503 is fixedly connected with the end of the first connecting rod 503 of the rest front brackets, and the end of the first connecting rod 503 is in the same plane parallel to the first direction with the axis of the front supporting member 501 and the axis of the front rotating shaft 506. The first connecting rods 503, the second connecting rods 504 and the third connecting rods 505 are all located on the outer side of the front supporting piece 501, all the first connecting rods 503 are distributed radially, and all the second connecting rods 504 are distributed continuously along the circumferential direction on the outer side of the front supporting piece 501.
As shown in fig. 1 to 4, in the present embodiment, four front brackets are provided, all the front brackets are continuously distributed in the circumferential direction on the outer side of the front support 501, the front rotating lever 502 is located between two front brackets adjacent in the circumferential direction and the front rotating lever 502 is fixedly connected with the first connecting rods 503 of the two front brackets, one end in the longitudinal direction of the front rotating lever 502 is fixedly connected with one of the first connecting rods 503, the other end in the longitudinal direction of the front rotating lever 502 is fixedly connected with the other first connecting rod 503, and the front rotating shaft 506 is located at the middle position of the two first connecting rods 503. The front rotating device 5 has simple structure and good support stability.
As shown in fig. 1 to 4, it is preferable that the front rotating frame includes a reinforcing bar 507 connected to the front rotating lever 502 and the front brackets, the reinforcing bar 507 is located between two front brackets adjacent in the circumferential direction and one end of the reinforcing bar 507 is fixedly connected to the first connecting bar 503 of the two front brackets, the other end of the reinforcing bar 507 is fixedly connected to the front rotating lever 502 at an intermediate position in the longitudinal direction of the front rotating lever 502, and the longitudinal direction of the reinforcing bar 507 is perpendicular to the longitudinal direction of the front rotating lever 502 and the axis of the front rotating shaft. The arrangement of the reinforcing rods 507 improves the overall strength of the front rotating frame, and further improves the stability and reliability of supporting large parts of the aircraft.
As shown in fig. 1 to 4, the front bracket body 2 includes a front base 201, and a front guide bar 205 and a front pillar 203 provided on the front base 201, the front guide bar 205 and the front pillar 203 extending toward an upper side of the front base 201, and lower ends of the front guide bar 205 and the front pillar 203 being fixedly connected to the front base 201. The front guide rods 205 are arranged in two, the front guide rods 205 are arranged vertically, the two front guide rods 205 are positioned on the same straight line parallel to the second direction, a certain distance is reserved between the two front guide rods 205, the front sliding seat 3 is in sliding connection with the two front guide rods 205, the two front guide rods 205 are respectively inserted into sliding grooves formed in the front sliding seat 3, the two front guide rods 205 are matched with each other, the front sliding seat 3 is guided, and the length of the front sliding seat 3 is smaller than that of the front guide rods 205. The front bracket main body 2 further comprises a front top plate 204, the upper ends of the two front guide rods 205 are fixedly connected with the front top plate 204, the front top plate 204 is a flat plate which is horizontally arranged, the front upright post 203 and the front guide rods 205 are positioned below the front top plate 204, the front fixed pulleys 10 are rotatably arranged on the front top plate 204, and the front fixed pulleys 10 are positioned below the front top plate 204. The front upright posts 203 are arranged in two, the two front upright posts 203 are positioned on the same straight line parallel to the second direction, the upper ends of the two front upright posts 203 are fixedly connected with the front top plate 204, the two front upright posts 203 and the two guide rods are distributed in a rectangular shape, the front top plate 204 is a rectangular plate, and the two front upright posts 203 and the two guide rods are respectively fixedly connected with the front top plate 204 at a right-angle corner of the front top plate 204. A certain distance is reserved between the two front upright posts 203, the front crane 8 is positioned between the two front upright posts 203, and the front crane 8 is fixedly connected with the two front upright posts 203. The front upright 203 is inclined, and an included angle is formed between the length direction of the front upright 203 and the first direction, and the included angle is an acute angle, and an included angle is also formed between the length direction of the front upright 203 and the second direction, and the included angle is an acute angle.
As shown in fig. 1 to 4, the front bracket main body 2 further includes a caster 202 disposed on the front base 201, the caster 202 is located below the front base 201, the caster 202 is fixedly connected with the front base 201, the caster 202 is three, the three casters 202 are distributed in three points, the caster 202 contacts with the ground and can roll on the ground, so that an operator can conveniently push the front assembly fixture and the large-scale components of the aircraft to integrally move. The front swivel device 5 is located outside the front bracket main body 2, and the front swivel device 5 is located above one of the casters 202.
The front bracket main body 2 has the advantages of simple structure, high strength and good support stability, and can provide stable support for large parts of an airplane. The front upright posts 203 are obliquely arranged, the two front upright posts 203 are arranged in a V shape, the distance between the upper ends of the two front upright posts 203 is smaller than the distance between the lower ends of the two front upright posts 203, the overall strength is improved by arranging the front upright posts 203, the assembly fixture is uniformly stressed by the arrangement of the front upright posts 203, the stability of the assembly fixture is ensured, and the support stability of large parts of an airplane is further improved.
As shown in fig. 1, 5 to 7, the rear lifting device comprises a rear sliding seat 4 movably arranged on a rear bracket main body 7 and a rear lifting control mechanism connected with the rear sliding seat 4 and used for controlling the rear sliding seat 4 to move along the vertical direction, the rear rotating device 6 is rotationally connected with the rear sliding seat 4, the rotation center line of the rear rotating device 6 is parallel to the first direction, and when in use, the rotation center line of the rear rotating device 6 and the rotation center line of the front rotating device 5 are the same straight line parallel to the first direction, and the moving direction of the rear lifting device is the vertical direction. The rear rotating device 6 is rotatable relative to the rear sliding seat 4, the rear sliding seat 4 can drive the rear rotating device 6 to synchronously move along the vertical direction, and then the rotation and lifting of the large-sized part of the airplane can be realized, the height position and the gesture of the large-sized part of the airplane can be adjusted, and the assembly with the middle wing assembly is convenient.
As shown in fig. 1, 5 to 7, the rear sliding seat 4 is slidably connected with the rear bracket main body 7, the rear bracket main body 7 plays a role in guiding the rear sliding seat 4, the rear sliding seat 4 is provided with a sliding groove which is an elongated groove extending in the vertical direction on the rear sliding seat 4, at least two parallel sliding grooves are arranged, and a part of the rear bracket main body 7 is embedded into the sliding groove on the rear sliding seat 4, so that the rear sliding seat 4 can be guided, and the stable operation of the rear sliding seat 4 and the rear rotating device 6 is ensured.
As shown in fig. 1 and 5 to 7, the rear lift control mechanism includes a rear fixed pulley 13 provided on the rear bracket main body 7, a rear stay 12 connected to the rear slide block 4 and bypassing the rear fixed pulley 13, and a rear crane 11 for controlling the release and retraction of the rear stay 12. The rear fixed pulley 13 is rotatably arranged on the rear bracket main body 7, the rear fixed pulley 13 is positioned at the top of the rear bracket main body 7, the axis of the rear fixed pulley 13 is parallel to the second direction, the second direction is the horizontal direction, and the second direction is perpendicular to the first direction. The rear fixed pulley 13 is provided with one, the rear stay rope 12 is a steel rope, one end of the rear stay rope 12 is fixedly connected with the rear sliding seat 4, the other end of the rear stay rope 12 is fixedly connected with the rear crane 11, the rear crane 11 is used for providing driving force for lifting the rear lifting device, and the rear crane 11 controls the rear stay rope 12 to release and roll. When the rear crane 11 rolls up the rear stay rope 12, the rear stay rope 12 is gradually wound on the rear crane 11, and at the moment, the rear stay rope 12 pulls the rear sliding seat 4 to move upwards along the vertical direction, and the rear sliding seat 4 drives the rear rotating device 6 to synchronously rise; when the rear crane 11 releases the rear stay rope 12, the rear stay rope 12 is gradually pulled out from the rear crane 11, at this time, the rear sliding seat 4 moves downwards along the vertical direction under the action of self gravity, the rear crane 11 controls the descending speed of the rear sliding seat 4, and the rear sliding seat 4 drives the rear rotating device 6 to synchronously descend.
The rear lifting control mechanism is compact in structure and convenient to arrange, the whole volume of the tool can be reduced, compared with other lifting devices formed in the prior art, lifting is realized in a jack mode, the rear lifting control mechanism can easily lift the machine body to a higher height, and further the middle wing assembly can be conveniently moved below the machine body of the aircraft, if the machine body is lifted to the same height by the jack mode, the requirement on the jack is higher, the jack is required to be larger and longer, the corresponding jack is heavier, the cost is high, the lifting operation is time-consuming and labor-consuming, and the whole volume of the tool is larger; the rear lifting control mechanism is also easier to control the height position of the aircraft body, and is convenient to operate in a hand-operated mode, labor-saving and better in stability.
As shown in fig. 1 and fig. 5 to fig. 7, the rear crane 11 is disposed on the rear bracket body 7, the rear crane 11 is located below the rear fixed pulley 13, the rear crane 11 is fixedly connected with the rear bracket body 7, the height of the rear crane 11 is smaller than that of the rear fixed pulley 13, the lower end of the rear guy cable 12 is fixedly connected with the lower end of the rear sliding seat 4, and the lower end of the rear sliding seat 4 is located below the rear fixed pulley 13. Preferably, the rear crane 11 is a hand-operated crane (also called a hand winch), which is manually rotated by manpower to roll and release the rear cable 12, and the structure of the hand-operated crane is well known to those skilled in the art and will not be described herein. The existing hand-operated cranes have an automatic braking function, can realize self-locking, are safer during operation, and can enable large parts of the aircraft to be kept at a set height position. The hand-operated crane is convenient to operate, good in reliability and high in safety, the height position of the large-sized part of the aircraft is conveniently controlled to be adjusted, and the assembly efficiency of the aircraft body and the middle wing assembly is improved.
As shown in fig. 1, 5 to 7, the rear rotating device 6 includes a rear rotating frame 601 rotatably connected to the rear elevating device and a rear support provided on the rear rotating frame 601 for connection with a large-sized part of the aircraft. The large aircraft component is an aircraft fuselage, the front support 501 is for connection to the aircraft fuselage at one end of the aircraft fuselage for mounting an aircraft nose, and the rear support is for connection to the aircraft fuselage at the other end of the aircraft fuselage (i.e., the tail of the aircraft fuselage). One end of the rear supporting piece is fixedly connected with the rear rotating frame 601, the other end of the rear supporting piece is detachably connected with the aircraft body through bolts, the rear supporting piece is convenient to assemble and disassemble, reliable connection with the aircraft body is guaranteed, through holes for the bolts to pass through are formed in the end portions of the rear supporting piece, and through holes for the bolts to pass through are formed in the tail portions of the aircraft body. After the rear supporting piece is in butt joint with the tail part of the aircraft body, the rear supporting piece is fixedly connected with the aircraft body through bolts, and after the rear supporting piece is connected with the aircraft body into a whole, the rear lifting device can drive the aircraft body to synchronously lift through the rear rotating device 6, and the rear rotating device 6 can drive the aircraft body to rotate relative to the rear lifting device. The rear rotating frame 601 is rotatably connected to the rear sliding seat 4 through a rear rotating shaft 603, and an axis of the rear rotating shaft 603 (i.e., a rotation center line of the rear rotating device 6) is parallel to the first direction.
As shown in fig. 1, 5 to 7, the rear elevating device has a locking hole for inserting a locking pin 14 to keep the rear rotating device 6 and the rear elevating device relatively fixed, the rear rotating frame 601 has a mounting hole 602 for inserting the locking pin 14, the mounting holes 602 are provided in plurality and all the mounting holes 602 are uniformly distributed in the circumferential direction, and all the mounting holes 602 on the rear rotating frame 601 are uniformly distributed in the circumferential direction with the rotation center line of the rear rotating device 6 as the center line, and the locking hole on the rear elevating device can be aligned with any one of the mounting holes 602 on the rear rotating frame 601. The rear lifting device further comprises a limiting plate 15 arranged on the rear sliding seat 4, a locking hole is formed in the limiting plate 15, the locking hole is a through hole penetrating through the limiting plate 15 in the plate thickness direction, the locking hole is a round hole, the axis of the locking hole is parallel to the first direction, the limiting plate 15 is located below the rear rotating shaft 603, the limiting plate 15 is fixedly connected with the rear sliding seat 4, and the limiting plate 15 extends towards the outer side of the rear sliding seat 4. After the large-sized component of the aircraft rotates to a proper angle, the locking hole on the limiting plate 15 is aligned with one mounting hole 602 on the rear rotating frame 601, the locking pin 14 is inserted into the mounting hole 602 and the locking hole, circumferential limiting of the rear rotating device 6 is achieved, the rear rotating device 6, the limiting plate 15 and the rear sliding seat 4 are kept relatively fixed, the rear rotating device 6 is locked, and then the large-sized component of the aircraft can be kept at the rotated angle position. At the same time, the front swivel device 5 and the front slide mount 3 can also be held relatively stationary by the connected large aircraft parts. When the large-sized part of the airplane needs to be rotated again, the rear rotating device 6 can be rotated by only pulling out the locking pin 14 to unlock the rear rotating device 6, so that the operation is convenient and simple, and the efficiency is high.
As shown in fig. 1 and fig. 5 to 7, the rear rotating frame 601 is of a regular polygon structure, the rear rotating shaft 603 is connected with the rear rotating frame 601 at the center of the rear rotating frame 601, the rear rotating frame 601 is located at the outer side of the rear bracket main body 7, the limiting plate 15 is located between the rear rotating frame 601 and the rear sliding seat 4, the rear supporting member is fixedly connected with the rear rotating frame 601 at the center of the rear rotating frame 601, the mounting hole 602 is formed in the rear rotating frame 601 and is a through hole (the thickness direction of the rear rotating frame 601 is parallel to the axis thereof) penetrating through the rear rotating frame 601 in the thickness direction of the rear rotating frame 601, and the locking pin 14 can be inserted and pulled out. The positions of the mounting holes 602 are close to the outer edge of the rear rotating frame 601, all the mounting holes 602 are continuously distributed along the outer edge of the rear rotating frame 601, and the mounting holes 602 are far away from the axis of the rear rotating frame 601, so that the operation is convenient.
As shown in fig. 1 and 5 to 7, in the present embodiment, 8 mounting holes 602 are provided in total, and the rear rotating frame 601 has a regular octagonal structure. The number of the mounting holes 602 is large, so that the angle adjusting range of the rear rotating device 6 is wide, the assembly requirement of the large-scale part and middle wing assembly of the aircraft is met, the assembly work is convenient, and the assembly efficiency is improved. When an operator operates, the rear rotating device 6 and the airplane body are rotated by pulling the rotating frame 601, and the rear rotating device 6 with the structure is more convenient to rotate.
As shown in fig. 1 and fig. 5 to 7, the limiting holes are preferably multiple, all the limiting holes are continuously distributed along the circumferential direction in a preset radian range (the preset radian range is smaller than 90 degrees) by taking the rotation center line of the rear rotating device 6 as the center line on the limiting plate 15, all the limiting holes are uniformly distributed on the limiting plate 15, the included angle between two circumferentially adjacent limiting holes is smaller than the included angle between two circumferentially adjacent mounting holes 602 on the rear rotating frame 601, so that fine adjustment of angles can be performed during assembly of large-scale components of the aircraft, the flexibility is good, the angle adjusting range of the rear rotating device 6 is wide, the assembly requirement during assembly of the large-scale components and middle wing assemblies of the aircraft is met, the assembly work is convenient, and the assembly efficiency is improved.
As shown in fig. 1, 5 to 7, the rear support includes a first rear support bar 604 connected to the rear swivel frame 601 and a second rear support bar 605 connected to the first rear support bar 604 for connection to the large-sized aircraft component by bolts, the second rear support bar 605 extending toward above the first rear support bar 604, the rear support bar having a first bolt hole 606, a second bolt hole 607, and a third bolt hole 608 through which the bolts pass, the first and second bolt holes 606 and 607 being located above the third bolt hole 608. The first rear support bar 604 is fixedly connected to the rear rotating frame 601 at the center of the rear rotating frame 601, and the first rear support bar 604 protrudes toward the outside of the rear rotating frame 601. The first rear supporting rod 604 is disposed obliquely, the first rear supporting rod 604 has a certain length, an included angle is formed between the length direction of the first rear supporting rod 604 and the first direction, the included angle is an acute angle, and the length direction of the first rear supporting rod 604 is perpendicular to the second direction. The first rear support bar 604 extends toward the outside upper side of the rear rotating frame 601, the lower end of the first rear support bar 604 is fixedly connected with the rear rotating frame 601, and the upper end of the first rear support bar 604 is fixedly connected with the second rear support bar 605. The first rear support bar 604 is for providing support, the large aircraft component is an aircraft fuselage, the front support 501 is for connecting to the aircraft fuselage at one end of the aircraft fuselage for mounting the aircraft nose, and the second rear support bar 605 is for connecting to the aircraft fuselage by bolts at the other end of the aircraft fuselage (i.e. the tail of the aircraft fuselage). The first bolt hole 606, the second bolt hole 607 and the third bolt hole 608 are arranged on the second rear supporting rod 605, the first bolt hole 606, the second bolt hole 607 and the third bolt hole 608 are arranged at three points, namely, the second rear supporting rod 605 is connected with the aircraft body at three positions, the connection with the aircraft body is reliable, the disassembly and assembly are convenient, and the support for the aircraft body is stable. The second rear supporting rod 605 is obliquely arranged, the second rear supporting rod 605 has a certain length, and an included angle is formed between the length direction of the second rear supporting rod 605 and the length direction of the first rear supporting rod 604 and is not smaller than 90 degrees. The second rear supporting rod 605 extends towards the upper side of the first rear supporting rod 604, the lower end of the second rear supporting rod 605 is fixedly connected with the upper end of the first rear supporting rod 604, the third bolt hole 608 is formed in the lower end of the second rear supporting rod 605, the first bolt hole 606 and the second bolt hole 607 are formed in the upper end of the second rear supporting rod 605, and the vertical distance between the upper end of the second rear supporting rod 605 and the rear rotating frame 601 is smaller than the vertical distance between the lower end of the second rear supporting rod 605 and the rear rotating frame 601.
As shown in fig. 1 and 5 to 7, the rear bracket body 7 includes a rear chassis 701, and rear guide rods 705 and rear uprights 703 provided on the rear chassis 701, the rear guide rods 705 and rear uprights 703 extending upward of the rear chassis 701, and lower ends of the rear guide rods 705 and rear uprights 703 being fixedly connected to the rear chassis 701. The two rear guide rods 705 are arranged vertically, the two rear guide rods 705 are positioned on the same straight line parallel to the second direction, a certain distance is reserved between the two rear guide rods 705, the rear sliding seat 4 is in sliding connection with the two rear guide rods 705, the two rear guide rods 705 are respectively inserted into sliding grooves formed in the rear sliding seat 4, the two rear guide rods 705 are matched with each other, the rear sliding seat 4 is guided, and the length of the rear sliding seat 4 is smaller than that of the rear guide rods 705. The rear bracket main body 7 further comprises a rear top plate 704, the upper ends of the two rear guide rods 705 are fixedly connected with the rear top plate 704 seat, the rear top plate 704 is a flat plate which is horizontally arranged, the rear upright post 703 and the rear guide rods 705 are positioned below the rear top plate 704, the rear fixed pulleys 13 are rotatably arranged on the rear top plate 704, and the rear fixed pulleys 13 are positioned below the rear top plate 704. The rear upright posts 703 are arranged in two, the two rear upright posts 703 are positioned on the same straight line parallel to the second direction, the upper ends of the two rear upright posts 703 are fixedly connected with the rear top plate 704, the two rear upright posts 703 and the two guide rods are distributed in a rectangular mode, the rear top plate 704 is a rectangular plate, and the two rear upright posts 703 and the two guide rods are respectively fixedly connected with the rear top plate 704 at a right-angle corner of the rear top plate 704. A certain distance is provided between the two rear posts 703, the rear crane 11 is located between the two rear posts 703 and the rear crane 11 is fixedly connected with the two rear posts 703. The rear upright post 703 is inclined, an included angle is formed between the length direction of the rear upright post 703 and the first direction, the included angle is an acute angle, and an included angle is also formed between the length direction of the rear upright post 703 and the second direction, and the included angle is an acute angle.
As shown in fig. 1 and fig. 5 to 7, the rear bracket body 7 further includes a caster 702 disposed on the rear base 701, the caster 702 is located below the rear base 701, the caster 702 is fixedly connected with the rear base 701, the casters 702 are three, the three casters 702 are distributed in three points, the casters 702 are in contact with the ground and can roll on the ground, so that an operator can conveniently push the rear assembly fixture and the large-scale components of the aircraft to integrally move. The rear swivel means 6 is located outside the rear bracket body 7, and the rear swivel means 6 is located above one of the casters 702.
The rear bracket main body 7 is simple in structure, high in strength and good in support stability, and can provide stable support for large parts of an airplane. The rear upright post 703 is obliquely arranged, the two rear upright posts 703 are arranged in a V shape, the distance between the upper ends of the two rear upright posts 703 is smaller than the distance between the lower ends of the two rear upright posts 703, the overall strength is improved by arranging the rear upright posts 703, the assembly fixture is uniformly stressed by the arrangement of the rear upright posts 703, the stability of the assembly fixture is ensured, and the support stability of large-scale components of an airplane is further improved.
The invention is described above by way of example with reference to the accompanying drawings. It will be clear that the invention is not limited to the embodiments described above. As long as various insubstantial improvements are made using the method concepts and technical solutions of the present invention; or the invention is not improved, and the conception and the technical scheme are directly applied to other occasions and are all within the protection scope of the invention.
Claims (1)
1. The assembly equipment for assembling the large-sized aircraft component is characterized by comprising a front assembly tool and a rear assembly tool which are arranged in a relative manner, wherein the front assembly tool comprises a front bracket main body, a front lifting device which is arranged on the front bracket main body and is used for controlling the large-sized aircraft component to lift, and a front rotating device which is rotatably arranged on the front lifting device and is used for supporting the large-sized aircraft component at one end of the large-sized aircraft component, and the rear assembly tool comprises a rear bracket main body, a rear lifting device which is arranged on the rear bracket main body and is used for controlling the large-sized aircraft component to lift, and a rear rotating device which is rotatably arranged on the rear lifting device and is used for supporting the large-sized aircraft component at the other end of the large-sized aircraft component;
the large-scale part of the aircraft is an aircraft body, the front assembly fixture is used for connecting one end of the aircraft body, which is used for installing an aircraft nose, with the aircraft body, the rear assembly fixture is used for connecting the other end of the aircraft body with the aircraft body, and when the large-scale part of the aircraft is used, the front assembly fixture and the rear assembly fixture are positioned on the same straight line parallel to a first direction, and the first direction is a horizontal direction; the front assembly tool and the rear assembly tool are matched and used for supporting an aircraft fuselage together, lifting and rotating of the aircraft fuselage can be achieved together, the aircraft fuselage can be assembled with other parts, the other parts are middle wing assemblies, the middle wing assemblies are mainly formed by connecting a fuselage bilge, a middle wing box and an engine cabin, the two middle wing boxes are respectively arranged between one engine cabin and the fuselage bilge, and the middle wing boxes are fixedly connected with one engine cabin and the fuselage bilge to form the middle wing assembly;
The front lifting device comprises a front sliding seat movably arranged on the front bracket main body and a front lifting control mechanism connected with the front sliding seat and used for controlling the front sliding seat to move along the vertical direction, the front rotating device is rotationally connected with the front sliding seat, the rotation center line of the front rotating device is parallel to the first direction, and the moving direction of the front lifting device is the vertical direction;
the front lifting control mechanism comprises a front fixed pulley arranged on the front bracket main body, a front inhaul cable which is connected with the front sliding seat and bypasses the front fixed pulley, and a front crane for controlling the front inhaul cable to release and roll; the front fixed pulley is rotatably arranged on the front bracket main body, the front fixed pulley is positioned at the top of the front bracket main body, the axis of the front fixed pulley is parallel to the second direction, the second direction is the horizontal direction, and the second direction is vertical to the first direction; the front fixed pulley is provided with one front guy cable, one end of the front guy cable is fixedly connected with the front sliding seat, the other end of the front guy cable is fixedly connected with the front crane, the front crane is used for providing driving force for lifting the front lifting device, and the front crane controls the front guy cable to release and roll; when the front crane rolls up the front stay rope, the front stay rope is gradually wound on the front crane, and at the moment, the front stay rope pulls the front sliding seat to move upwards along the vertical direction, and the front sliding seat drives the front rotating device to synchronously rise; when the front crane releases the front stay rope, the front stay rope is gradually pulled out from the front crane, at the moment, the front sliding seat moves downwards along the vertical direction under the action of self gravity, the front crane controls the descending speed of the front sliding seat, and the front sliding seat drives the front rotating device to synchronously descend;
The front crane is arranged on the front bracket main body, the front crane is positioned below the front fixed pulley, the front crane is fixedly connected with the front bracket main body, the height of the front crane is smaller than that of the front fixed pulley, the lower end of the front inhaul cable is fixedly connected with the lower end of the front sliding seat, and the lower end of the front sliding seat is positioned below the front fixed pulley;
the front rotating device comprises a front rotating frame which is rotationally connected with the front lifting device and a front supporting piece which is arranged on the front rotating frame and is used for being connected with the large-scale part of the aircraft; the front support piece is used for being connected with the aircraft body at one end of the aircraft body for installing the aircraft nose, one end of the front support piece is used for being detachably connected with the aircraft body through bolts, the shape of the front support piece is the same as that of the aircraft nose, the axis of the front support piece is parallel to that of the front rotating shaft, through holes for the bolts to pass through are formed in the edge of the end part of the front support piece, and through holes for the bolts to pass through are also formed in the edge of the end part of the aircraft body; after the end part of the front supporting piece is in butt joint with the end part of the aircraft body, the front supporting piece is fixedly connected with the aircraft body through bolts, and after the front supporting piece is connected with the aircraft body into a whole, the front lifting device can drive the aircraft body to synchronously lift through the front rotating device, and the front rotating device can drive the aircraft body to rotate relative to the front lifting device;
The front rotating frame comprises a front bracket connected with the front supporting piece and a front rotating rod connected with the front bracket and rotationally connected with the front lifting device, and a plurality of front brackets are arranged and all the front brackets are distributed around the outer side of the front supporting piece; the front rotating rod is rotationally connected with the front sliding seat through a front rotating shaft, the axis of the front rotating shaft is in line with the first direction Xiang Xiangping, the length direction of the front rotating rod is perpendicular to the first direction, the front rotating shaft is fixedly connected with the front rotating rod at the middle position of the front rotating rod in the length direction, and the upper end of the front sliding seat is provided with a shaft hole for the front rotating shaft to be inserted;
the front rotating rods are fixedly connected with the front brackets, all the front brackets are fixedly connected into a whole, the front supporting pieces are fixedly connected with all the front brackets, and in the first direction, the front rotating rods are positioned between the front supporting pieces and the front bracket main body; the front bracket is of a U-shaped structure and comprises a first connecting rod, a second connecting rod and a third connecting rod which are sequentially connected, wherein the first connecting rod, the second connecting rod and the third connecting rod have a certain length, the length of the third connecting rod is smaller than that of the first connecting rod, the length direction of the second connecting rod is parallel to the first direction, and the length direction of the first connecting rod is perpendicular to the first direction; one end of a second connecting rod of each front bracket is fixedly connected with one end of a first connecting rod, the other end of the second connecting rod is fixedly connected with one end of a third connecting rod, the other end of the third connecting rod is fixedly connected with a front supporting piece, the other end of the first connecting rod is fixedly connected with the end parts of the first connecting rods of the rest front brackets, and the end of the first connecting rod is positioned in the same plane parallel to the axis of the front supporting piece and the axis of the front rotating shaft; the first connecting rods, the second connecting rods and the third connecting rods are all positioned at the outer sides of the front supporting pieces, all the first connecting rods are distributed in a radial manner, and all the second connecting rods are continuously distributed along the circumferential direction at the outer sides of the front supporting pieces;
The front brackets are arranged in four, all the front brackets are continuously distributed along the circumferential direction on the outer side of the front supporting piece, the front rotating rods are positioned between two front brackets adjacent in the circumferential direction and are fixedly connected with the first connecting rods of the two front brackets, one end of each front rotating rod in the length direction is fixedly connected with one of the first connecting rods, the other end of each front rotating rod in the length direction is fixedly connected with the other first connecting rod, and the front rotating shaft is positioned at the middle position of the two first connecting rods;
the rear lifting device comprises a rear sliding seat movably arranged on the rear bracket main body and a rear lifting control mechanism connected with the rear sliding seat and used for controlling the rear sliding seat to move along the vertical direction, the rear rotating device is rotationally connected with the rear sliding seat, the rotation center line of the rear rotating device is parallel to the first direction, and when the rear lifting device is used, the rotation center line of the rear rotating device and the rotation center line of the front rotating device are the same straight line parallel to the first direction, and the moving direction of the rear lifting device is the vertical direction;
the rear lifting control mechanism comprises a rear fixed pulley arranged on the rear bracket main body, a rear stay rope which is connected with the rear sliding seat and bypasses the rear fixed pulley, and a rear crane for controlling the rear stay rope to be released and rolled up; the rear fixed pulley is rotatably arranged on the rear bracket main body, the rear fixed pulley is positioned at the top of the rear bracket main body, the axis of the rear fixed pulley is parallel to the second direction, the second direction is the horizontal direction, and the second direction is vertical to the first direction; the rear fixed pulley is provided with one rear stay rope, one end of the rear stay rope is fixedly connected with the rear sliding seat, the other end of the rear stay rope is fixedly connected with the rear crane, the rear crane is used for providing driving force for lifting the rear lifting device, and the rear crane controls the rear stay rope to release and roll up; when the rear crane rolls up the rear stay rope, the rear stay rope is gradually wound on the rear crane, and at the moment, the rear stay rope pulls the rear sliding seat to move upwards along the vertical direction, and the rear sliding seat drives the rear rotating device to synchronously rise; when the rear crane releases the rear stay rope, the rear stay rope is gradually pulled out from the rear crane, at the moment, the rear sliding seat moves downwards along the vertical direction under the action of self gravity, the rear crane controls the descending speed of the rear sliding seat, and the rear sliding seat drives the rear rotating device to synchronously descend;
The rear crane is arranged on the rear bracket main body, the rear crane is positioned below the rear fixed pulley, the rear crane is fixedly connected with the rear bracket main body, the height of the rear crane is smaller than that of the rear fixed pulley, the lower end of the rear inhaul cable is fixedly connected with the lower end of the rear sliding seat, and the lower end of the rear sliding seat is positioned below the rear fixed pulley;
the rear rotating device comprises a rear rotating frame which is rotationally connected with the rear lifting device and a rear supporting piece which is arranged on the rear rotating frame and is used for being connected with the large-scale part of the aircraft; the front support piece is used for being connected with the aircraft body at one end of the aircraft body for installing the aircraft nose, and the rear support piece is used for being connected with the aircraft body at the other end of the aircraft body; one end of the rear supporting piece is fixedly connected with the rear rotating frame, and the other end of the rear supporting piece is used for forming detachable connection with the aircraft body through bolts; after the rear supporting piece is in butt joint with the tail part of the aircraft body, the rear supporting piece is fixedly connected with the aircraft body through bolts, and after the rear supporting piece is connected with the aircraft body into a whole, the rear lifting device can drive the aircraft body to synchronously lift through the rear rotating device, and the rear rotating device can drive the aircraft body to rotate relative to the rear lifting device; the rear rotating frame is rotationally connected with the rear sliding seat through a rear rotating shaft, and the axis of the rear rotating shaft is parallel to the first direction;
The rear lifting device is provided with a locking hole which is used for allowing a locking pin to be inserted so as to enable the rear rotating device and the rear lifting device to be relatively fixed, the rear rotating frame is provided with a plurality of mounting holes which are used for allowing the locking pin to be inserted, all the mounting holes are uniformly distributed along the circumferential direction, all the mounting holes on the rear rotating frame are uniformly distributed along the circumferential direction by taking the rotation center line of the rear rotating device as a center line, and the locking hole on the rear lifting device can be aligned with any one of all the mounting holes on the rear rotating frame;
the rear lifting device further comprises a limiting plate arranged on the rear sliding seat, the locking hole is arranged on the limiting plate, the locking hole is a through hole which is formed in the limiting plate in a penetrating manner along the plate thickness direction, the locking hole is a round hole, the axis of the locking hole is parallel to the first direction, the limiting plate is positioned below the rear rotating shaft, the limiting plate is fixedly connected with the rear sliding seat, and the limiting plate extends towards the outer side of the rear sliding seat; after the large-scale part of the aircraft rotates to a proper angle, a locking hole on the limiting plate is aligned with a mounting hole on the rear rotating frame, a locking pin is inserted into the mounting hole and the locking hole, circumferential limiting of the rear rotating device is achieved, the rear rotating device, the limiting plate and the rear sliding seat are kept relatively fixed, the rear rotating device is locked, and then the large-scale part of the aircraft can be kept at the rotated angle position; meanwhile, the front rotating device and the front sliding seat can be kept relatively fixed through the connected large-scale parts of the airplane; when the large-sized part of the airplane needs to be rotated again, the rear rotating device is unlocked only by extracting the locking pin, so that the large-sized part of the airplane and the rear rotating device can be rotated;
The rear rotating frame is of a regular polygon structure, the rear rotating shaft is connected with the rear rotating frame at the center of the rear rotating frame, the rear rotating frame is positioned at the outer side of the rear bracket main body, the limiting plate is positioned between the rear rotating frame and the rear sliding seat, the rear supporting piece is fixedly connected with the rear rotating frame at the center of the rear rotating frame, the mounting hole is formed in the rear rotating frame and is a through hole penetrating through the rear rotating frame in the thickness direction of the rear rotating frame, and the locking pin can be inserted and pulled out; the positions of the mounting holes are close to the outer edge of the rear rotating frame, and all the mounting holes are continuously distributed along the outer edge of the rear rotating frame;
the limiting holes are arranged in a plurality, all the limiting holes are circumferentially and continuously distributed in a preset radian range by taking the rotation center line of the rear rotating device as the center line on the limiting plate, all the limiting holes are uniformly distributed on the limiting plate, and the included angle between two circumferentially adjacent limiting holes is smaller than the included angle between two circumferentially adjacent mounting holes on the rear rotating frame;
the rear support piece comprises a first rear support rod connected with the rear rotating frame and a second rear support rod connected with the first rear support rod and used for being connected with the large-scale part of the airplane through bolts, the second rear support rod extends towards the upper side of the first rear support rod, the rear support rod is provided with a first bolt hole, a second bolt hole and a third bolt hole, the bolts penetrate through the first bolt hole, the second bolt hole and the third bolt hole, and the first bolt hole and the second bolt hole are positioned above the third bolt hole; the first rear supporting rod is fixedly connected with the rear rotating frame at the center of the rear rotating frame and extends towards the outer side of the rear rotating frame; the first rear supporting rod is obliquely arranged, the first rear supporting rod has a certain length, an included angle is formed between the length direction of the first rear supporting rod and the first direction, the included angle is an acute angle, and the length direction of the first rear supporting rod is perpendicular to the second direction; the first rear supporting rod extends towards the upper outer side of the rear rotating frame, the lower end of the first rear supporting rod is fixedly connected with the rear rotating frame, and the upper end of the first rear supporting rod is fixedly connected with the second rear supporting rod; the first rear supporting rod is used for providing a supporting effect, the large-sized part of the aircraft is an aircraft body, the front supporting piece is used for connecting one end of the aircraft body, which is used for installing an aircraft nose, with the aircraft body, and the second rear supporting rod of the rear supporting piece is used for connecting the other end of the aircraft body with the aircraft body through bolts; the first bolt hole, the second bolt hole and the third bolt hole are arranged on the second rear supporting rod, and the first bolt hole, the second bolt hole and the third bolt hole are arranged at three points, namely the second rear supporting rod is connected with the airplane body at three positions;
The second rear supporting rod is obliquely arranged, the second rear supporting rod has a certain length, and an included angle is formed between the length direction of the second rear supporting rod and the length direction of the first rear supporting rod and is not smaller than 90 degrees; the second back bracing piece is the top extension towards first back bracing piece, and the lower extreme of second back bracing piece and the upper end fixed connection of first back bracing piece, and the third bolt hole setting is in the lower extreme of second back bracing piece, and first bolt hole and second bolt hole setting are in the upper end of second back bracing piece, and the perpendicular distance between the upper end of second back bracing piece and the back swivel mount is less than the perpendicular distance between the lower extreme of second back bracing piece and the back swivel mount.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810672589.8A CN108791950B (en) | 2018-06-26 | 2018-06-26 | Assembly equipment for assembling large-scale parts of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810672589.8A CN108791950B (en) | 2018-06-26 | 2018-06-26 | Assembly equipment for assembling large-scale parts of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108791950A CN108791950A (en) | 2018-11-13 |
| CN108791950B true CN108791950B (en) | 2023-12-29 |
Family
ID=64070877
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810672589.8A Active CN108791950B (en) | 2018-06-26 | 2018-06-26 | Assembly equipment for assembling large-scale parts of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108791950B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2990190A1 (en) * | 2012-05-02 | 2013-11-08 | Snecma | Tool for handling high pressure module of turbojet of aircraft, has fixing arms connected to vertical branches of support body by pivot joint, so as to allow rotation of high pressure module about horizontal rotation axis between branches |
| CN105259871A (en) * | 2014-07-09 | 2016-01-20 | 波音公司 | Metrology-based system for operating a flexible manufacturing system |
| CN105382778A (en) * | 2015-11-27 | 2016-03-09 | 中航成飞民用飞机有限责任公司 | Large-component turnover tool and large-component turnover method |
| JP2017136928A (en) * | 2016-02-02 | 2017-08-10 | 三菱重工業株式会社 | Holding jig fixing device |
| CN208453257U (en) * | 2018-06-26 | 2019-02-01 | 中电科芜湖钻石飞机制造有限公司 | Assembly equipment is used in the assembly of aircraft large component |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10421560B2 (en) * | 2016-08-09 | 2019-09-24 | Sikorsky Aircraft Corporation | Bond fixture for leading edge assembly |
-
2018
- 2018-06-26 CN CN201810672589.8A patent/CN108791950B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2990190A1 (en) * | 2012-05-02 | 2013-11-08 | Snecma | Tool for handling high pressure module of turbojet of aircraft, has fixing arms connected to vertical branches of support body by pivot joint, so as to allow rotation of high pressure module about horizontal rotation axis between branches |
| CN105259871A (en) * | 2014-07-09 | 2016-01-20 | 波音公司 | Metrology-based system for operating a flexible manufacturing system |
| CN105382778A (en) * | 2015-11-27 | 2016-03-09 | 中航成飞民用飞机有限责任公司 | Large-component turnover tool and large-component turnover method |
| JP2017136928A (en) * | 2016-02-02 | 2017-08-10 | 三菱重工業株式会社 | Holding jig fixing device |
| CN208453257U (en) * | 2018-06-26 | 2019-02-01 | 中电科芜湖钻石飞机制造有限公司 | Assembly equipment is used in the assembly of aircraft large component |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108791950A (en) | 2018-11-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105667829B (en) | It is a kind of it is same be other aircraft assembling/workover rig depressed place | |
| CN110155362B (en) | Lifting platform for overhauling vertical fin of airplane | |
| EP2900587B1 (en) | Rotating tower crane | |
| CN109896038B (en) | Unmanned aerial vehicle ejection system | |
| EP3132137B1 (en) | Mobile crane device and method for the temporary assembly of such a crane device | |
| CN200940078Y (en) | Mobile crane | |
| US8850682B2 (en) | Removal of components from aircraft | |
| CN107758561B (en) | Aeroengine lifting device | |
| CN109759998B (en) | Installation vehicle for turbofan aircraft engine | |
| CN108791950B (en) | Assembly equipment for assembling large-scale parts of airplane | |
| KR101358679B1 (en) | Hinge assembling apparatus for boom combination | |
| CN112031382B (en) | Stable scaffold with controllable height and using method | |
| CN212479052U (en) | Over-and-under type aircraft maintenance work ladder | |
| CN208453257U (en) | Assembly equipment is used in the assembly of aircraft large component | |
| CN110668324B (en) | Tower crane movable passageway system | |
| CN108639375B (en) | Method for assembling airplane fuselage and middle wing assembly | |
| CN108116691B (en) | Hydraulic ejection method of unmanned aerial vehicle | |
| CN216190569U (en) | Assembled wall body installation auxiliary device | |
| CN111284648A (en) | Rudder blade support frame and rudder blade mounting trolley | |
| CN106988596B (en) | Electric power tower | |
| CN114249248B (en) | Aviation accessory production is with equipment system | |
| CN220146044U (en) | Bathtub side cut device | |
| CN219690329U (en) | Hanging basket for bridge high-altitude operation | |
| CN220056210U (en) | Steel beam construction device | |
| CN213326606U (en) | Inclined elevator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |