CN116902217B - Symmetrical positioning assembly and method based on aircraft composite structural member - Google Patents
Symmetrical positioning assembly and method based on aircraft composite structural member Download PDFInfo
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- CN116902217B CN116902217B CN202311177958.3A CN202311177958A CN116902217B CN 116902217 B CN116902217 B CN 116902217B CN 202311177958 A CN202311177958 A CN 202311177958A CN 116902217 B CN116902217 B CN 116902217B
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- 239000002131 composite material Substances 0.000 title claims abstract description 140
- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000001125 extrusion Methods 0.000 claims abstract description 56
- 230000000712 assembly Effects 0.000 claims abstract description 4
- 238000000429 assembly Methods 0.000 claims abstract description 4
- 238000001179 sorption measurement Methods 0.000 claims description 34
- 239000000523 sample Substances 0.000 claims description 33
- 239000000463 material Substances 0.000 claims description 18
- 238000005452 bending Methods 0.000 claims description 8
- 230000006835 compression Effects 0.000 claims description 7
- 238000007906 compression Methods 0.000 claims description 7
- 230000001788 irregular Effects 0.000 claims description 7
- 238000010521 absorption reaction Methods 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims description 4
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 238000004891 communication Methods 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 3
- 230000003139 buffering effect Effects 0.000 description 2
- 239000000945 filler Substances 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Classifications
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- 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
- B64F5/50—Handling or transporting aircraft components
-
- 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
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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)
- Transportation (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The invention discloses a symmetrical positioning assembly and a symmetrical positioning method based on an aircraft composite structural member, and relates to the technical field of symmetrical positioning assemblies of aircraft composite structural members. The symmetrical positioning assembly and the method based on the aircraft composite structural member have the advantages that when the I-shaped composite structural member is positioned, the symmetrical positioning assembly and the method are placed in the positioning frame, the lower part of the positioning frame is in contact with the bottom support frame, the two sides of the positioning frame are horizontally distributed with the preliminary positioning assembly, and when the preliminary positioning assembly clamps the I-shaped composite structural member, the extrusion force between the two parts is controlled within a certain range, so that deformation of the I-shaped composite structural member caused by excessive extrusion is prevented, and the situation that the deformation position of the I-shaped composite structural member is elastically reset to cause inaccurate positioning is avoided in the subsequent loading process.
Description
Technical Field
The invention relates to the technical field of symmetrical positioning assemblies of aircraft composite structural members, in particular to a symmetrical positioning assembly and a symmetrical positioning method based on an aircraft composite structural member.
Background
An aircraft refers to an aircraft having wings, one or more engines, driven forward by its own power, and capable of having a greater density in the atmosphere than air. If the aircraft is less dense than air, it is a balloon or airship. Without a power plant, the aircraft can only glide in the air, which is called a glider, and if the aircraft wings are not fixed, the aircraft wings rotate to generate lift by the wing wings, namely a helicopter or a rotorcraft, and fixed-wing aircraft is the most common aircraft type. The power source comprises a piston engine, a turboprop engine, a turbofan engine or a rocket engine and the like, the front and rear beams of the aircraft are integrally formed by adopting a composite material, and then the front and rear beams of the aircraft are loaded onto the aircraft and are required to be accurately positioned by a symmetrical positioning assembly, so that the loaded integrated front and rear beams can be ensured to act maximally.
The existing symmetrical positioning assembly based on the aircraft composite structural member generally realizes the positioning of the aircraft composite structural member in the use process through an extrusion mode, fine adjustment is carried out on the aircraft composite structural member after extrusion limiting, thereby completing the accurate positioning of the composite structural member, however, the front and rear beams of the aircraft are integrally formed by adopting composite materials, the cross section is I-shaped, the outer edge strips on the two sides are provided with open and closed angle designs, the size is as long as 7 meters, the composite material is easy to deform after the part characteristic is cured, particularly the outer edge strips are provided with angle irregular rebound phenomenon after the part is formed, the extrusion limiting mode is easy to cause extrusion deformation to the composite structural member with large size and easy to deform due to overlarge extrusion force, so that after the composite structural member is symmetrically positioned, the composite structural member is loaded on the aircraft, deformation resetting is carried out on the outer side, thereby causing loading precision deviation, and reducing the use value of the symmetrical positioning assembly.
Disclosure of Invention
The invention discloses a symmetrical positioning component based on an aircraft composite structural member, which aims to solve the technical problems that the existing symmetrical positioning component based on the aircraft composite structural member generally realizes the positioning of the aircraft composite structural member in an extrusion mode, after extrusion limiting, fine adjustment is carried out on the aircraft composite structural member so as to finish the accurate positioning of the composite structural member, however, an aircraft front beam and an aircraft rear beam are integrally formed by adopting composite materials, the cross section is I-shaped, two side outer edge strips are provided with opening and closing angle designs, the size is as long as 7 meters, the composite material is easy to deform after the part characteristics are solidified, particularly the outer edge strips are provided with an irregular rebound phenomenon after the part is formed, the extrusion limiting mode is easy to cause extrusion deformation on the composite structural member with large size and easy to deform due to overlarge extrusion force, so that after the composite structural member is symmetrically positioned, the composite structural member is loaded on an aircraft, deformation resetting condition appears on the outer side, and the loading precision is caused.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the utility model provides a symmetrical positioning subassembly based on aircraft combined material structure, includes chassis and locating frame, the locating frame is close to the outside of two long limits and all is equipped with preliminary locating component, and preliminary locating component includes the mounting bracket, and one side fixedly connected with cylinder one in the locating frame is faced to the mounting bracket, and the output fixedly connected with movable rod of cylinder one, the equal fixedly connected with cylinder two in opposite one side of movable rod, and the equal fixedly connected with grip block of output of two cylinders two, two grip blocks all open towards the outside in the locating frame has the mounting groove, and the inside of two mounting grooves all is equipped with pressure sensor, the equal fixedly connected with abduction board in both sides of movable rod, and one side of two abduction boards all is equipped with spacing gasbag towards the locating frame, and the top fixedly connected with deformation guide piece of abduction board, and the outside equidistance of abduction board leaves there is the pressure release hole, and one side equidistance fixedly connected with interception pole of locating frame is kept away from to the abduction board, the bottom fixedly connected with gallows of abduction board, and the top fixedly connected with air pump of gallows, the one end fixedly connected with of air pump, the other end of connecting pipe is pegged graft in the inside of spacing gasbag.
Through being provided with preliminary locating component, when carrying out I shape combined material location, place it in the locating frame, its below and bottom support frame contact, its both sides are horizontal distribution with preliminary locating component, and preliminary locating component is when realizing I shape combined material centre gripping, extrusion force control between the two is in certain within range to prevent I shape combined material and deformation because of the extrusion excessively, ensure that the condition emergence that I shape combined material deformation position elastic reset caused the location inaccurate can not appear in the follow-up loading process, improve the use value of this equipment.
In a preferred scheme, the top fixedly connected with slide rail of abduction board, and the inside equidistance sliding connection of slide rail has the slip stock, and the equal fixedly connected with pull rod in one side that every slip stock is close to the top, and the slip stock is towards the equidistant fixedly connected with connection spring pole in one side of locating frame, and the other end fixedly connected with same filling rod of a plurality of connection spring poles.
In a preferred scheme, the locating frame is close to the both sides of minor face and all is equipped with I shape inboard locating component, and I shape inboard locating component includes propulsion frame and side frame, and side frame fixed connection is in the outside of locating frame, and side frame is towards the one side fixedly connected with electric telescopic handle of locating frame, propulsion frame fixed connection in electric telescopic handle's output.
In a preferred scheme, the propulsion frame is fixedly connected with a self-adjusting rail facing one side of the positioning frame, self-adjusting sliding blocks are in equidistant sliding connection in the self-adjusting rail, shaft brackets are fixedly connected to the outer sides of the self-adjusting sliding blocks, and self-adjusting squeeze rollers are connected to the inner sides of the shaft brackets through bearings.
In a preferred scheme, the outside that the propulsion frame is close to both ends is all fixedly connected with spacing rail, and the inside fixedly connected with driving motor that the propulsion frame is close to spacing rail is opened there is the motor groove, driving motor's output shaft passes through the shaft coupling fixedly connected with axis of rotation, the inside sliding connection of spacing rail has spacing slider, the top fixedly connected with same connecting rod of axis of rotation and spacing slider, the outside fixedly connected with extension piece of spacing slider, the outside fixedly connected with bearing plate of extension piece, the outside equidistance fixedly connected with extrusion spring bar of bearing plate, the other end of a plurality of extrusion spring bars is equipped with same elastic extrusion board.
Through being provided with I shape inboard locating component, after accomplishing I shape combined material's preliminary location, adjust electric telescopic handle and drive the propulsion frame and remove to I shape combined material's intermediate position, after self-adjusting squeeze roll and I shape combined material intermediate position contact, if the contact position is protruding position, then self-adjusting slider at self-adjusting squeeze roll rear slides in the self-adjusting rail, ensure self-adjusting squeeze roll can not cause extrusion deformation to I shape combined material's outside, after I shape combined material is close to the both sides of center department spacing, start driving motor, driving motor drives spacing slider and rotates, make the elastic extrusion board rotate to I shape combined material's L type kink, extrusion of extrusion spring pole makes elastic extrusion board step by step with L type kink two face contact laminating, thereby further improve the fastness of location centre gripping, ensure that it is in stable state in the follow-up symmetrical adjustment process.
In a preferred scheme, the chassis is close to the top at four angles and all is equipped with symmetrical regulation subassembly, and symmetrical regulation subassembly is including laying the board, lays board fixed connection in the top of chassis, lays the top of board and is equipped with digital display symmetry indicator.
In a preferred scheme, lay the top fixedly connected with of board and connect the bent lever, and connect the top fixedly connected with of bent lever and place the frame, be equipped with the wire on the digital display symmetrical indicator, the other end of wire is connected with the probe, the outside of probe is equipped with outer ring plate, the top fixedly connected with of outer ring plate two installation poles, the equal fixedly connected with cavity adsorption plate in the outside of two installation poles, the cavity adsorption plate has the absorption hole towards the one side equidistance departure of probe, the inside of every absorption hole all is equipped with the vacuum adsorption dish, one side fixedly connected with pump frame of probe is kept away from to the cavity adsorption plate, the top fixedly connected with vacuum pump of pump frame, the evacuation end of vacuum pump passes through the inside of pipe connection in the cavity adsorption plate.
Through being provided with symmetry regulation subassembly, after I shape combined material location is accomplished, the manual work removes the probe to four angles tops of I shape combined material, the probe contacts with it, then start the vacuum pump, the vacuum pump is through carrying out the evacuation to each vacuum adsorption dish on the cavity adsorption plate for the vacuum adsorption dish adsorbs in I shape combined material's the outside, ensures that the probe is in stable contact's state with I shape combined material, ensures symmetry regulation in-process, need not the manual work and goes to carry out the location of probe, probe and I shape combined material synchronous motion, improves symmetry regulation's precision.
In a preferred scheme, four support columns are fixedly connected to the top of the underframe, the top of each two support columns is fixedly connected with one adjusting rail I, two sliding blocks I are fixedly connected to the inner parts of the two adjusting rails I in a sliding mode, end blocks I are fixedly connected to the two ends of the adjusting rails I, a hydraulic cylinder I is fixedly connected to one side, facing the sliding blocks I, of each end block, and the output end of each hydraulic cylinder I is fixedly connected to the outer side of each sliding block I.
In a preferred scheme, two of the first sliding blocks located on different first adjusting rails are fixedly connected with the same second adjusting rail, two ends of the second adjusting rail are fixedly connected with second end blocks, two opposite sides of the second end blocks are fixedly connected with second hydraulic cylinders, two output ends of the second hydraulic cylinders are fixedly connected with second sliding blocks, the second sliding blocks are slidably connected to the inside of the second adjusting rail, the positioning frame is fixedly connected to the tops of the four second sliding blocks, and the bottom support frame is fixedly connected to the top of the bottom frame below the positioning frame.
By arranging the first adjusting rail and the second adjusting rail, after the I-shaped composite material is positioned, the probe and the I-shaped composite material are in contact, the first hydraulic cylinder and the second hydraulic cylinder are repeatedly adjusted to drive the I-shaped composite material on the inner side of the positioning frame to move, whether the I-shaped composite material is in a symmetrical distribution state is judged by numerical values on the digital display symmetrical indicator, and the final symmetrically positioned I-shaped composite material is ensured to be perfectly butted with an airplane.
A method of using a symmetrical positioning assembly based on an aircraft composite structure as described above, the method of using the symmetrical positioning assembly comprising the steps of:
step one: when the I-shaped composite material is positioned, the I-shaped composite material is placed in a positioning frame, the lower part of the I-shaped composite material is in contact with a bottom support frame, a clamping plate on a first driving movable rod of an adjusting cylinder clamps two sides of the I-shaped composite material, a pressure-bearing sensor monitors pressure in real time in the process of pushing and clamping, after the limiting in the first step is completed, an air pump is started, the air pump inflates the inside of a limiting air bag, the limiting air bag presents an expansion trend, part of the limiting air bag is extruded through a pressure relief hole, part of the limiting air bag is extruded to the outer wall of the I-shaped composite material, meanwhile, each filling rod is manually pulled to move to the filling air bag, and the irregular concave position on the outer side of the I-shaped composite material is filled through the filling rod;
step two: after the preliminary positioning of the I-shaped composite material is finished, the electric telescopic rod is regulated to drive the pushing frame to move to the middle position of the I-shaped composite material, the driving motor is started, and the driving motor drives the limiting sliding block to rotate, so that the elastic extrusion plate rotates to the L-shaped bending position of the I-shaped composite material, and the extrusion of the extrusion spring rod enables the elastic extrusion plate to be gradually contacted and attached with two surfaces of the L-shaped bending position;
step three: after the positioning of the I-shaped composite material is finished, manually moving the probe above four corners of the I-shaped composite material, enabling the probe to be in contact with the probe, and then starting a vacuum pump, wherein the vacuum pump vacuumizes each vacuum adsorption disc through the hollow adsorption plate, so that the vacuum adsorption discs are adsorbed on the outer side of the I-shaped composite material;
step four: and repeatedly adjusting the I-shaped composite material on the inner sides of the positioning frames driven by the first hydraulic cylinder and the second hydraulic cylinder to move, determining that the I-shaped composite material is in a symmetrical distribution state through numerical values on the digital display symmetrical indicator, and stopping the work of the first hydraulic cylinder and the second hydraulic cylinder if the numerical values on the digital display symmetrical indicator show that the I-shaped composite material is in the symmetrical distribution state.
According to the symmetrical positioning component based on the aircraft composite structural member, when the I-shaped composite structural member is positioned, the symmetrical positioning component is placed in the positioning frame, the lower part of the symmetrical positioning component is in contact with the bottom support frame, the adjusting cylinder drives the clamping plates on the moving rods to clamp two sides of the I-shaped composite structural member, the pressure-bearing sensors monitor the pressure in real time in the process of pushing and clamping, the I-shaped composite structural member is prevented from deforming due to overlarge extrusion force, the air pump is started after the limiting air bag is completely limited, the limiting air bag presents an expansion trend, part of the limiting air bag is extruded through the pressure relief holes, part of the limiting air bag is extruded to the outer wall of the I-shaped composite structural member, the limiting air bag is gradually attached to the outer side of the I-shaped composite structural member in the extrusion process, the extrusion force between the limiting air bag and the I-shaped composite structural member is reduced due to the partial inward sinking of the limiting air bag, the fact that deformation of the I-shaped composite structural member is avoided, meanwhile, the filling rods are manually pulled to the filling air bag, the filling rod is filled in the irregular concave positions of the outer side of the I-shaped composite structural member, the connecting spring rod on the filling rod plays a role in pressure buffering, and the effect of ensuring that the filling rod is not to cause excessive extrusion of the composite structural member to deform after the I-shaped structural member is positioned, and the positioning effect is achieved, and the positioning is better.
Drawings
Fig. 1 is a schematic diagram of the overall structure of a symmetrical positioning assembly based on an aircraft composite structure according to the present invention.
Fig. 2 is a top view of the overall structure of a symmetrical positioning assembly based on an aircraft composite structure according to the present invention.
Fig. 3 is a schematic view of a preliminary positioning assembly of a symmetrical positioning assembly based on an aircraft composite structure according to the present invention.
Fig. 4 is a side view of the overall structure of fig. 3.
Fig. 5 is a schematic diagram of a combined structure of a limit airbag and a filling rod of a symmetrical positioning assembly based on an aircraft composite structural member.
Fig. 6 is a schematic diagram of an i-shaped inner positioning assembly of a symmetrical positioning assembly based on an aircraft composite structure according to the present invention.
Fig. 7 is a schematic diagram of a combined structure of a self-adjusting squeeze roller and a pushing frame of a symmetrical positioning assembly based on an aircraft composite structure.
Fig. 8 is a schematic diagram of a combined structure of an elastic extrusion plate and a limit rail of a symmetrical positioning assembly based on an aircraft composite structural member.
Fig. 9 is a schematic diagram of a symmetrical adjusting assembly of a symmetrical positioning assembly based on a composite structural member of an aircraft according to the present invention.
Fig. 10 is a schematic view of the internal structure of a placement frame of a symmetrical positioning assembly based on an aircraft composite structure according to the present invention.
In the figure: 1. a chassis; 2. adjusting the first rail; 3. an end block II; 4. adjusting a second rail; 5. a positioning frame; 6. a second sliding block; 7. a second hydraulic cylinder; 8. an end block I; 9. a bottom support frame; 10. a symmetrical adjustment assembly; 1001. a placement plate; 1002. a wire; 1003. placing a frame; 1004. digital display symmetry indicator; 1005. connecting a bent rod; 1006. a hollow adsorption plate; 1007. a vacuum pump; 1008. a pump frame; 1009. a vacuum adsorption plate; 1010. a probe; 1011. an outer ring plate; 1012. a mounting rod; 11. a support column; 12. a first hydraulic cylinder; 13. a first sliding block; 14. a preliminary positioning component; 1401. a mounting frame; 1402. a first cylinder; 1403. a moving rod; 1404. an abduction plate; 1405. a deformation guide piece; 1406. a clamping plate; 1407. a pressure-bearing sensor; 1408. a limit air bag; 1409. a second cylinder; 1410. an interception bar; 1411. an air pump; 1412. a hanging bracket; 1413. a connecting pipe; 1414. a pressure relief hole; 1415. connecting a spring rod; 1416. a filler rod; 1417. a pull rod; 1418. sliding the long rod; 1419. a slide rail; 15. i-shaped inner side positioning components; 1501. a propulsion rack; 1502. extruding a spring rod; 1503. self-track-adjusting; 1504. self-adjusting squeeze rollers; 1505. a shaft bracket; 1506. an elastic extrusion plate; 1507. an electric telescopic rod; 1508. a side frame; 1509. a self-adjusting sliding block; 1510. an extension piece; 1511. a pressure bearing plate; 1512. a connecting rod; 1513. a rotating shaft; 1514. a driving motor; 1515. a limit rail; 1516. and a limit sliding block.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments.
The symmetrical positioning assembly based on the aircraft composite structural member is mainly applied to the existing symmetrical positioning assembly based on the aircraft composite structural member, positioning of the aircraft composite structural member is generally realized in an extrusion mode, fine adjustment is carried out on the aircraft composite structural member after extrusion limiting, and thus accurate positioning of the composite structural member is completed.
Referring to fig. 1-10, a symmetrical positioning assembly based on aircraft combined material structure spare, including chassis 1 and locating frame 5, the outside that locating frame 5 is close to two long limits all is equipped with preliminary positioning assembly 14, and preliminary positioning assembly 14 includes mounting bracket 1401, one side fixedly connected with cylinder 1402 in the locating frame 5 of mounting bracket 1401, the output fixedly connected with dwang 1403 of cylinder one 1402, the equal fixedly connected with cylinder two 1409 of opposite side of dwang 1403, and the output of two cylinders two 1409 all fixedly connected with clamping plate 1406, two clamping plate 1406 all opens the mounting groove towards the outside in the locating frame 5, the inside of two mounting groove all is equipped with sensor 1407, the both sides of dwang 1403 all fixedly connected with abduction board 1404, and one side of two abduction boards 1404 all is equipped with spacing gasbag 1408 towards locating frame 5, the top fixedly connected with deformation guide piece 1405, the outside equidistance of abduction board 1404 leaves there is the pressure release hole, one side fixedly connected with interception pole 1412 of abduction board 1404, the bottom of two cylinders 1419 of external board 1415 is connected with the backing rail 1419, the equal distance is connected with the inside of a plurality of connecting rods 1416 fixed connection rods 1416, the inside of equal distance rods 1413 are connected with the side of connecting rods 1413, the inside of connecting rods 1416 fixed connection rods 1413 are connected with the top rods 1416 of the equal distance rods 1416, the inside connecting rods 1413 are connected with the connecting rods 1416, the equal distance rods 1416 are connected with the connecting rods 1416, and the equal distance rods are connected with the connecting rods 1415.
Specifically, when the positioning of the I-shaped composite material is performed, the I-shaped composite material is placed in the positioning frame 5, the lower part of the positioning frame is contacted with the bottom end supporting frame 9, the first adjusting cylinder 1402 drives the clamping plates 1406 on the moving rod 1403 to clamp the two sides of the I-shaped composite material, and in the process of pushing and clamping, the pressure-bearing sensor 1407 monitors the pressure in real time, so that the deformation of the I-shaped composite material caused by overlarge extrusion force is prevented.
It should be noted that, when the air pump 1411 is started, the air pump 1411 inflates the inside of the limiting air bag 1408, the limiting air bag 1408 presents an expansion trend, part of the position of the limiting air bag 1408 is extruded through the pressure release hole 1414, part of the position extrudes the outer wall of the i-shaped composite material, during the extrusion process, the limiting air bag 1408 is gradually attached to the outer side of the i-shaped composite material, the extrusion force between the limiting air bag 1408 and the outer side of the i-shaped composite material is reduced due to the local inward sinking of the limiting air bag 1408, and the outer side of the i-shaped composite material is ensured not to deform.
In a specific application scene, each filling rod 1416 is manually pulled to move to the filling air bag, irregular concave positions on the outer side of the I-shaped composite material are filled through the filling rods 1416, the connecting spring rods 1415 on the filling rods 1416 play a role in pressure buffering, the situation that excessive extrusion deformation is caused on the outer side of the I-shaped composite material in the filling process of the filling rods 1416 is avoided, after the filling of the filling rods 1416 is completed, the wedge degree between the I-shaped composite material and the primary positioning assembly 14 is higher, and the positioning and clamping effects are better.
Referring to fig. 1, fig. 2, fig. 6, fig. 7 and fig. 8, in a preferred embodiment, both sides of the positioning frame 5 near the short side are respectively provided with an i-shaped inner positioning component 15, and the i-shaped inner positioning component 15 includes a pushing frame 1501 and a side frame 1508, the side frame 1508 is fixedly connected to the outer side of the positioning frame 5, one side of the side frame 1508 facing the positioning frame 5 is fixedly connected with an electric telescopic rod 1507, the pushing frame 1501 is fixedly connected to the output end of the electric telescopic rod 1507, one side of the pushing frame 1501 facing the positioning frame 5 is fixedly connected with a self-adjusting rail 1503, the inside of the self-adjusting rail 1503 is in equidistant sliding connection with a self-adjusting slide 1509, the outer side of each self-adjusting slide 1509 is fixedly connected with a shaft bracket 1505, the inner side of each shaft bracket 1505 is connected with self-adjusting extrusion rollers 1504 through bearings, the outer sides of the pushing frame 1501 near both ends are fixedly connected with a limit rail 1515, the top of the pushing frame 1501 near the limit rail 1515 is provided with a motor groove, the inside of the motor groove is fixedly connected with a driving motor 1514, the output shaft of the driving motor 1514 is fixedly connected to the output shaft of the electric telescopic rod 1503 through a coupling, one side of the driving motor 1513 is fixedly connected with a rotation shaft 1513, one side of the driving motor 1516 is fixedly connected with a plurality of limit blocks 1511, the inside of limit blocks 1511 is fixedly connected with a plurality of limit blocks 1511, the same compression plates 1511 are fixedly connected with a plurality of limit blocks 1511, and the same compression plates 1511 are fixedly connected with the same compression plate.
After the preliminary positioning of the i-shaped composite material is completed, the electric telescopic rod 1507 is adjusted to drive the pushing frame 1501 to move to the middle position of the i-shaped composite material, when the self-adjusting extrusion roller 1504 contacts with the middle position of the i-shaped composite material, if the contact position is a convex position, the self-adjusting slide block 1509 at the rear of the self-adjusting extrusion roller 1504 slides in the self-adjusting rail 1503, so that the self-adjusting extrusion roller 1504 can not cause extrusion deformation to the outer side of the i-shaped composite material, after the two sides of the i-shaped composite material, which are close to the center, are limited, the driving motor 1514 is started, the driving motor 1514 drives the limiting slide block 1516 to rotate, so that the elastic extrusion plate 1506 rotates to the L-shaped bending position of the i-shaped composite material, and the extrusion of the extrusion spring rod 1502 gradually contacts and adheres to the two surfaces of the L-shaped bending position, so that the positioning and clamping firmness is further improved, and the stable state of the self-adjusting extrusion roller 1504 in the subsequent symmetrical adjustment process is ensured.
Referring to fig. 1, fig. 2, fig. 9 and fig. 10, in a preferred embodiment, the top of the chassis 1 near four corners is provided with a symmetrical adjusting component 10, and the symmetrical adjusting component 10 includes a mounting plate 1001, the mounting plate 1001 is fixedly connected to the top of the chassis 1, the top of the mounting plate 1001 is provided with a digital display symmetrical indicator 1004, the top of the mounting plate 1001 is fixedly connected with a connecting bent rod 1005, the top of the connecting bent rod 1005 is fixedly connected with a placing frame 1003, a wire 1002 is provided on the digital display symmetrical indicator 1004, the other end of the wire 1002 is connected with a probe 1010, an outer ring plate 1011 is provided on the outer side of the probe 1010, two mounting rods 1012 are fixedly connected with hollow adsorption plates 1006, one side of each hollow adsorption plate facing the probe 1010 is equidistantly separated from the hollow adsorption plates, the inside of each adsorption hole is provided with a vacuum adsorption plate 1009, one side of each hollow adsorption plate 1006 far from the probe 1010 is fixedly connected with a pump frame 1008, the top of the frame 1008 is fixedly connected with a vacuum pump 1007, and the vacuum end of the vacuum pump 1007 is connected to the inside of the hollow adsorption plate 1006 through a pipeline.
Specifically, after the positioning of the i-shaped composite material is completed, the probe 1010 is manually moved to the upper parts of four corners of the i-shaped composite material, the probe 1010 is contacted with the i-shaped composite material, then the vacuum pump 1007 is started, and the vacuum pump 1007 pumps vacuum to each vacuum adsorption disc 1009 through the hollow adsorption plate 1006, so that the vacuum adsorption discs 1009 are adsorbed on the outer sides of the i-shaped composite material, the probe 1010 and the i-shaped composite material are ensured to be in a stable contact state, the probe 1010 is ensured to be positioned without manual work in the symmetrical adjustment process, and the probe 1010 and the i-shaped composite material are synchronously moved, so that the accuracy of symmetrical adjustment is improved.
Referring to fig. 1 and 2, in a preferred embodiment, four support columns 11 are fixedly connected to the top of the chassis 1, the top of each two support columns 11 is fixedly connected to the same first adjusting rail 2, two sliding blocks 13 are slidably connected to the inside of each first adjusting rail 2, two end blocks 8 are fixedly connected to the two ends of each first adjusting rail 2, a hydraulic cylinder 12 is fixedly connected to one side of each end block 8 facing the sliding block 13, and the output end of each hydraulic cylinder 12 is fixedly connected to the outer side of each sliding block 13.
In the invention, the tops of two sliding blocks I13 positioned on different first adjusting rails 2 are fixedly connected with the same second adjusting rail 4, two ends of the second adjusting rail 4 are fixedly connected with the second end blocks 3, two opposite sides of the second end blocks 3 are fixedly connected with the second hydraulic cylinders 7, the output ends of the second hydraulic cylinders 7 are fixedly connected with the second sliding blocks 6, the second sliding blocks 6 are slidably connected in the second adjusting rail 4, the positioning frame 5 is fixedly connected with the tops of the four sliding blocks II 6, and the top of the underframe 1 positioned below the positioning frame 5 is fixedly connected with the bottom end supporting frame 9.
A method of using a symmetrical positioning assembly based on an aircraft composite structure, using a symmetrical positioning assembly based on an aircraft composite structure as described above, the method of using a symmetrical positioning assembly comprising the steps of:
step one: when the I-shaped composite material is positioned, the I-shaped composite material is placed in the positioning frame 5, the lower part of the I-shaped composite material is contacted with the bottom support frame 9, the first adjusting cylinder 1402 drives the clamping plates 1406 on the moving rods 1403 to clamp the two sides of the I-shaped composite material, the pressure-bearing sensor 1407 monitors the pressure in real time in the process of pushing and clamping, after the limiting in the first step is completed, the air pump 1411 is started, the air pump 1411 inflates the inside of the limiting air bag 1408, the limiting air bag 1408 presents the expansion trend, part of the limiting air bag 1408 is extruded through the pressure relief holes 1414, part of the limiting air bag 1408 extrudes the outer wall of the I-shaped composite material, meanwhile, each filling rod 1416 is manually pulled to move to the filling air bag, and irregular concave positions on the outer side of the I-shaped composite material are filled through the filling rods 1416;
step two: after the preliminary positioning of the I-shaped composite material is completed, the electric telescopic rod 1507 is regulated to drive the pushing frame 1501 to move to the middle position of the I-shaped composite material, the driving motor 1514 is started, the driving motor 1514 drives the limit sliding block 1516 to rotate, the elastic extrusion plate 1506 rotates to the L-shaped bending position of the I-shaped composite material, and the extrusion of the extrusion spring rod 1502 enables the elastic extrusion plate 1506 to be gradually contacted and attached with two surfaces of the L-shaped bending position;
step three: after the positioning of the I-shaped composite material is completed, manually moving the probe 1010 above four corners of the I-shaped composite material, contacting the probe 1010 with the probe, then starting the vacuum pump 1007, and vacuumizing each vacuum adsorption disc 1009 through the hollow adsorption plate 1006 by the vacuum pump 1007 so that the vacuum adsorption discs 1009 are adsorbed on the outer sides of the I-shaped composite material;
step four: and repeatedly adjusting the first hydraulic cylinder 12 and the second hydraulic cylinder 7 to drive the I-shaped composite material at the inner side of the positioning frame 5 to move, determining that the I-shaped composite material is in a symmetrical distribution state through numerical values on the digital display symmetrical indicator 1004, and stopping the work of the first hydraulic cylinder 12 and the second hydraulic cylinder 7 if the numerical values on the digital display symmetrical indicator 1004 show that the I-shaped composite material is in the symmetrical distribution state.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.
Claims (10)
1. The utility model provides a symmetry positioning module based on aircraft combined material structure, a serial communication port, including chassis (1) and locating frame (5), the outside that locating frame (5) is close to two long limits all is equipped with preliminary positioning module (14), and preliminary positioning module (14) include mounting bracket (1401), one side fixedly connected with cylinder one (1402) in mounting bracket (1401) is facing locating frame (5), the output fixedly connected with movable rod (1403) of cylinder one (1402), the opposite side of movable rod (1403) all fixedly connected with cylinder two (1409), and the output of two cylinders two (1409) all fixedly connected with grip block (1406), two grip block (1406) all open towards the outside in locating frame (5) and have the mounting groove, and the inside of two mounting grooves all is equipped with pressure-bearing sensor (1407), the both sides of movable rod (1403) all are fixedly connected with abduction board (1404), and one side that two abduction board (1405) are facing locating frame (5) all is equipped with spacing (1408), and the top fixedly connected with deflector plate (1405) of abduction board (1404) is kept away from the fixed connection of fixed equal distance from positioning frame (1404) of positioning frame (1404), and the top of gallows (1412) fixedly connected with air pump (1411), the one end fixedly connected with connecting pipe (1413) of air pump (1411), the other end of connecting pipe (1413) peg graft in the inside of spacing gasbag (1408).
2. The symmetrical positioning assembly based on the aircraft composite structural member according to claim 1, wherein the top of the abduction plate (1404) is fixedly connected with a sliding rail (1419), the inside of the sliding rail (1419) is equidistantly and slidingly connected with sliding long rods (1418), one side of each sliding long rod (1418) close to the top is fixedly connected with a pull rod (1417), one side of each sliding long rod (1418) facing the positioning frame (5) is equidistantly and fixedly connected with a connecting spring rod (1415), and the other ends of the plurality of connecting spring rods (1415) are fixedly connected with the same filling rod (1416).
3. The symmetrical positioning assembly based on the aircraft composite structural member according to claim 2, wherein the two sides of the positioning frame (5) close to the short sides are respectively provided with an I-shaped inner positioning assembly (15), the I-shaped inner positioning assembly (15) comprises a pushing frame (1501) and a side frame (1508), the side frame (1508) is fixedly connected to the outer side of the positioning frame (5), an electric telescopic rod (1507) is fixedly connected to one side of the side frame (1508) facing the positioning frame (5), and the pushing frame (1501) is fixedly connected to the output end of the electric telescopic rod (1507).
4. A symmetrical positioning assembly based on a composite structural member of an aircraft according to claim 3, wherein the side of the propulsion frame (1501) facing the positioning frame (5) is fixedly connected with a self-adjusting rail (1503), the inside of the self-adjusting rail (1503) is slidingly connected with self-adjusting sliding blocks (1509) at equal intervals, the outer side of each self-adjusting sliding block (1509) is fixedly connected with a shaft bracket (1505), and the inner side of each shaft bracket (1505) is connected with a self-adjusting extrusion roller (1504) through a bearing.
5. The symmetrical positioning assembly based on the aircraft composite structural member according to claim 4, wherein the outer sides of the pushing frames (1501) close to two ends are fixedly connected with limiting rails (1515), motor grooves are formed in the tops of the pushing frames (1501) close to the limiting rails (1515), driving motors (1514) are fixedly connected to the inner portions of the motor grooves, rotation shafts (1513) are fixedly connected to output shafts of the driving motors (1514) through couplings, limiting sliding blocks (1516) are slidingly connected to the inner portions of the limiting rails (1515), the rotation shafts (1513) and the top portions of the limiting sliding blocks (1516) are fixedly connected with the same connecting rod (1512), extension pieces (1510) are fixedly connected to the outer sides of the limiting sliding blocks (1516), compression plates (1511) are fixedly connected to the outer sides of the compression plates (1511) at equal distances, and the other ends of the compression spring rods (1502) are provided with the same elastic compression plates (1506).
6. The symmetrical positioning assembly based on the aircraft composite structural member according to claim 5, wherein the symmetrical adjusting assemblies (10) are arranged at the tops of the chassis (1) close to the four corners, the symmetrical adjusting assemblies (10) comprise placing plates (1001), the placing plates (1001) are fixedly connected to the tops of the chassis (1), and digital display symmetrical indicators (1004) are arranged at the tops of the placing plates (1001).
7. The symmetrical positioning assembly based on the aircraft composite structural member according to claim 6, wherein the top fixedly connected with of laying board (1001) connects bent rod (1005), and the top fixedly connected with of connecting bent rod (1005) places frame (1003), be equipped with wire (1002) on digital display symmetrical indicator (1004), the other end of wire (1002) is connected with probe (1010), the outside of probe (1010) is equipped with outer ring plate (1011), the top fixedly connected with of outer ring plate (1011) two installation poles (1012), the outside of two installation poles (1012) all fixedly connected with cavity adsorption plate (1006), the equal distance of one side of cavity adsorption plate (1006) towards probe (1010) leaves there is the absorption hole, the inside of every absorption hole all is equipped with vacuum adsorption dish (1009), one side that the probe (1010) was kept away from to cavity adsorption plate (1006) is fixedly connected with pump frame (1008), the top fixedly connected with vacuum pump (1007) of pump frame (1008), the evacuation end of vacuum pump (1007) is connected with the inside of cavity adsorption plate (1006) through the pipeline.
8. The symmetrical positioning assembly based on the aircraft composite structural member according to claim 7, wherein four support columns (11) are fixedly connected to the top of the underframe (1), the same first adjusting rail (2) is fixedly connected to the top of each two support columns (11), two first sliding blocks (13) are slidably connected to the inside of each first adjusting rail (2), two end blocks (8) are fixedly connected to the two ends of each first adjusting rail (2), a first hydraulic cylinder (12) is fixedly connected to one side, facing the first sliding blocks (13), of each end block (8), and the output end of each first hydraulic cylinder (12) is fixedly connected to the outer side of each first sliding block (13).
9. The symmetrical positioning assembly based on the aircraft composite structural member according to claim 8, wherein the tops of two sliding blocks I (13) positioned on different adjusting rails I (2) are fixedly connected with the same adjusting rail II (4), two ends of the adjusting rail II (4) are fixedly connected with end blocks II (3), two opposite sides of the two end blocks II (3) are fixedly connected with hydraulic cylinders II (7), the output ends of the two hydraulic cylinders II (7) are fixedly connected with sliding blocks II (6), the sliding blocks II (6) are slidably connected in the adjusting rail II (4), the positioning frame (5) is fixedly connected to the tops of the four sliding blocks II (6), and the bottom support frame (9) is fixedly connected to the top of the underframe (1) positioned below the positioning frame (5).
10. A method of using a symmetrical positioning assembly based on an aircraft composite structure as defined in claim 9, comprising the steps of:
step one: when the I-shaped composite material is positioned, the I-shaped composite material is placed in a positioning frame (5), the lower part of the I-shaped composite material is in contact with a bottom support frame (9), a first adjusting cylinder (1402) drives a clamping plate (1406) on a moving rod (1403) to clamp two sides of the I-shaped composite material, a pressure-bearing sensor (1407) monitors the pressure in real time in the process of pushing and clamping, an air pump (1411) is started after the limiting of the first step is completed, the air pump (1411) inflates the inside of a limiting air bag (1408), the limiting air bag (1408) presents an expansion trend, part of the limiting air bag (1408) is extruded through a pressure relief hole (1414), part of the limiting air bag (1408) extrudes the outer wall of the I-shaped composite material, meanwhile, each filling rod (1416) is manually pulled to move to the filling air bag, and irregular concave positions on the outer side of the I-shaped composite material are filled through the filling rods (1416).
Step two: after the preliminary positioning of the I-shaped composite material is finished, an electric telescopic rod (1507) is regulated to drive a pushing frame (1501) to move to the middle position of the I-shaped composite material, a driving motor (1514) is started, the driving motor (1514) drives a limit sliding block (1516) to rotate, an elastic extrusion plate (1506) rotates to an L-shaped bending position of the I-shaped composite material, and extrusion of an extrusion spring rod (1502) enables the elastic extrusion plate (1506) to be gradually contacted and attached with two surfaces of the L-shaped bending position;
step three: after the positioning of the I-shaped composite material is completed, manually moving the probe (1010) to the position above the four corners of the I-shaped composite material, enabling the probe (1010) to be in contact with the probe, then starting the vacuum pump (1007), and vacuumizing each vacuum adsorption disc (1009) through the hollow adsorption plate (1006) by the vacuum pump (1007), so that the vacuum adsorption discs (1009) are adsorbed on the outer side of the I-shaped composite material;
step four: and repeatedly adjusting the first hydraulic cylinder (12) and the second hydraulic cylinder (7) to drive the I-shaped composite material at the inner side of the positioning frame (5) to move, determining that the I-shaped composite material is in a symmetrical distribution state through numerical values on the digital display symmetrical indicator (1004), and stopping the work of the first hydraulic cylinder (12) and the second hydraulic cylinder (7) if the numerical values on the digital display symmetrical indicator (1004) show that the I-shaped composite material is in the symmetrical distribution state.
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