CN111674071A - Meridian aircraft tire forming process - Google Patents
Meridian aircraft tire forming process Download PDFInfo
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- CN111674071A CN111674071A CN202010558934.2A CN202010558934A CN111674071A CN 111674071 A CN111674071 A CN 111674071A CN 202010558934 A CN202010558934 A CN 202010558934A CN 111674071 A CN111674071 A CN 111674071A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D30/00—Producing pneumatic or solid tyres or parts thereof
- B29D30/06—Pneumatic tyres or parts thereof (e.g. produced by casting, moulding, compression moulding, injection moulding, centrifugal casting)
- B29D30/08—Building tyres
- B29D30/20—Building tyres by the flat-tyre method, i.e. building on cylindrical drums
- B29D30/30—Applying the layers; Guiding or stretching the layers during application
- B29D30/3028—Applying the layers; Guiding or stretching the layers during application by feeding a continuous band and winding it helically, i.e. the band is fed while being advanced along the drum axis, to form an annular element
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Abstract
The invention discloses a radial aircraft tire molding process, and belongs to the technical field of aircraft tires. The radial aircraft tire forming process comprises first section cloth tube attaching, first section forming, second section belt bundle drum attaching and second section shaping drum shaping. The invention is applied to the manufacturing aspect of aviation tires, solves the problem of technical defects of the prior domestic radial aviation tires, and has the characteristics of realizing the industrial production of the radial aviation tires and excellent performance of the radial aviation tires obtained by production.
Description
Technical Field
The invention belongs to the technical field of aircraft tires, and particularly relates to a forming process of a radial aircraft tire.
Background
The aircraft tire is a very important landing part of an airplane and has the characteristics of large load, high speed, large deformation and high inflation internal pressure. Therefore, the aircraft tire must meet the conditions of impact resistance, puncture resistance, temperature rise resistance, and capability of withstanding the strong centrifugal force generated by the high-speed takeoff of the aircraft and the huge impact force at the moment of landing. Aircraft tires are classified into bias aircraft tires and radial aircraft tires. Among them, radial aircraft tires are more prominent in various properties than bias aircraft tires, and therefore, radial aircraft tires have been used as substitutes for conventional bias tires for aircraft landing gear components.
However, the concentration of the aircraft tire industry is very high, and the key technology is mastered by 5 enterprises (goodyear, japan priston, japan roommand, france, england dunlop) in 4 countries (america, japan, law, english) all over the world among a few international famous tire enterprises, and the industrialization is realized. At present, the traditional oblique crossing aircraft tire is mainly produced by the well-known aircraft tire manufacturers at home, the production process is relatively simple, and the radial aircraft tire production process technology is controlled by the aircraft tire manufacturers in monopoly state internationally.
Because the difference between the manufacturing process of the radial aircraft tire and the oblique aircraft tire is large, the technical development difficulty is large, and the precision requirement is high, the radial aircraft tire and the oblique aircraft tire need to be developed and produced by using a unique manufacturing process.
Disclosure of Invention
Aiming at the defects in the prior art, the technical problem to be solved by the invention is to overcome the technical defects of the conventional domestic radial aircraft tire, and provide a radial aircraft tire forming process which can realize the industrial production and excellent performance of the radial aircraft tire.
In order to solve the technical problem, the technical scheme adopted by the invention is as follows:
the invention provides a radial aircraft tire molding process, which sequentially comprises the following steps: the method comprises the following steps of first section cloth tube fitting, first section forming, second section belt bundle drum fitting and second section forming drum forming.
Preferably, the cloth tube fitting section comprises: 4, laminating the air-tight layer sheets; 1 layer of isolation rubber sheet is attached, 1 layer of fiber carcass cord is attached, and 1 layer of carcass is attached by coating rubber; coating glue on the 2 nd layer of fiber carcass cord and the 2 nd layer of carcass for gluing; coating rubber on the 3 rd layer of fiber carcass cord and the 3 rd layer of carcass for gluing; and (3) laminating the 1 layer of two symmetrical steel wire ring reinforcing layers and the rubber sheets to obtain a cloth cylinder laminating assembly.
Preferably, the lamination of the 4-layer air barrier layer sheet comprises extruding and curling the air barrier layer sheet with the width of 560-600mm, and continuously winding the air barrier layer sheet on a flat drum laminator head for 4 weeks.
Preferably, the one-segment forming comprises: mounting the cloth tube fitting assembly on a section of machine head of a section of forming machine, sequentially carrying out centering, expanding and rolling on a rubber component, positively wrapping a circular steel wire ring and a triangular rubber core assembly by a finger-shaped sheet, reversely wrapping a capsule, coating 1 layer of fiber carcass cord fabric and positively wrapping, coating 1 layer of carcass with rubber, and rolling; and then 1 layer of fiber carcass ply and forward wrapping, 1 layer of carcass coating rubber, rolling, using a capsule reverse wrapping method to attach 2 symmetrical wear-resistant rubbers, 2 symmetrical shoulder pad rubbers, 2 symmetrical filling rubbers and 2 symmetrical sidewall rubbers, and rolling to obtain a section of carcass.
Preferably, the attaching of the 2 symmetrical wear-resistant adhesives by using the capsule turn-up method comprises: and attaching the wear-resistant glue on a turn-up capsule, connecting the wear-resistant glue with the turn-up capsule, and turning over the wear-resistant glue layer in a capsule inflation turn-up mode to enable the wear-resistant glue layer to be tightly attached to the specified position of the opening of the green tire.
Preferably, the two-segment belt drum lamination comprises: firstly pasting a layer of cushion rubber sheet on a belt drum, finishing 2 layers of 1 period on the cushion rubber sheet layer by layer, continuously winding 6-8 belt layers in total in an S shape, pasting 1 layer of retreading base rubber after winding, then pasting a corrugated protective layer assembly and a tire tread, rolling layer by layer, and finishing belt layer winding, a corrugated protective layer and a tire tread assembly.
Preferably, the two-stage shaping drum shaping comprises: and combining the first-section green tire, the tire tread, the belted layer and the corrugated protection layer assembly on a two-section forming machine, and completing the forming process of the whole aircraft tire green tire through the links of pre-forming, super-forming and post-pressing combined rolling.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides a radial aircraft tire molding process which has the characteristics of being capable of realizing industrial production of radial aircraft tires and enabling the radial aircraft tires obtained through production to have excellent performance.
Drawings
FIG. 1 is a schematic view of a radial aircraft tire building process layout provided in an embodiment of the present invention;
FIG. 2 is a side view of a feeder frame number 1 according to an embodiment of the present invention;
FIG. 3 is a side view of a feed frame number 2 according to an embodiment of the present invention;
FIG. 4 is a side view of a No. 3 feeder frame according to an embodiment of the present invention;
FIG. 5 is a side view of a feed block No. 4 according to an embodiment of the present invention;
FIG. 6 is a front view of a section of a molding machine provided in accordance with an embodiment of the present invention;
FIG. 7 is a side view of a two-stage molding machine provided by an embodiment of the present invention;
in the above figures: 1. a flat drum laminating machine host machine; 2. flattening the drum; 3. a combined rolling device; 4. a front feeding frame; 5. a tailstock; 6. a forming drum; 7. a main machine of the forming drum; 8. an automatic transfer device; 9. combining press rolls; 10. a shaping drum host; 11. shaping drum; 12. a transfer ring; 13. a belt drum; 14. a belt drum main machine; 15. a tread feeding frame; 16. a tread feeding trolley; 17. a belt layer winding, conveying, tensioning and adjusting device; 18. a belted layer winding and storing device; 19. a corrugated protective layer feeding frame; 20. a corrugated protective layer cutting device; 21. a separation and combination rolling device; 22. renovating a base rubber sheet feeding device; 23. a belt winding device; 24. And (4) combining press rolls.
Detailed Description
The technical solutions in the embodiments of the present invention will be fully described in detail below with reference to the accompanying drawings. It is obvious that the described embodiments are only some specific embodiments, not all embodiments, of the general technical solution of the present invention. All other embodiments, which can be derived by a person skilled in the art from the general idea of the invention, fall within the scope of protection of the invention.
The invention provides a radial aircraft tire molding process, which sequentially comprises the following steps: the method comprises the following steps of first section cloth tube fitting, first section forming, second section belt bundle drum fitting and second section forming drum forming. The technological process is smooth, semi-finished rubber parts are transferred orderly, the integral standard operation of the whole process is easy to realize, and the technological method can improve the forming efficiency and forming precision of the radial aircraft tire and meet the use performance of the aircraft tire under high load, high impact and high speed. The process is different from a conventional radial tire two-stage molding method, the aviation tire molding rubber components are various, the compactness characteristics among the rubber components are particularly outstanding, and the product quality can be ensured only by laminating layer by layer in 4 process molding links.
In a preferred embodiment, the length of cloth tube fitting comprises: 4, laminating the air-tight layer sheets; 1 layer of isolation rubber sheet is attached, 1 layer of fiber carcass cord is attached, and 1 layer of carcass is attached by coating rubber; coating glue on the 2 nd layer of fiber carcass cord and the 2 nd layer of carcass for gluing; coating rubber on the 3 rd layer of fiber carcass cord and the 3 rd layer of carcass for gluing; and (3) laminating the 1 layer of two symmetrical steel wire ring reinforcing layers and the rubber sheets to obtain a cloth cylinder laminating assembly. The section of cloth tube is attached by using a flat drum attaching machine, the airtight layer of the conventional radial ply vehicle tire is only 1 layer, and the butt joint is overlapped greatly; the tire body cord fabric adopts a single-layer or multi-layer steel wire tire body, and the impact resistance is not strong; and basically no tyre body is coated with rubber, and the bonding performance between rubber components is not strong. The process adopts 4 layers of air-tight layer sheets for lamination, adopts fiber carcass cords and simultaneously performs carcass rubberizing, thereby being beneficial to improving the impact resistance of the tire, the binding force among components and the overall performance of the tire.
In a preferred embodiment, the lamination of the 4-layer air barrier sheet comprises extruding and curling the air barrier sheet with a width of 560-600mm, and continuously winding the air barrier sheet on a flat drum laminator head for 4 weeks. The process operation can ensure that the transition of the joint of the air-tight layer is small and has no hidden quality trouble. The conventional radial ply vehicle tire adopts 1 layer of airtight layer, has large overlapping thickness of butt joints, causes the hidden trouble of uneven weight distribution, and is different from the method that rubber components of an aviation tire must be uniformly distributed and laminated.
In a preferred embodiment, the section forming comprises: mounting the cloth tube fitting assembly on a section of machine head of a section of forming machine, sequentially carrying out centering, expanding and rolling on a rubber component, positively wrapping a circular steel wire ring and a triangular rubber core assembly by a finger-shaped sheet, reversely wrapping a capsule, coating 1 layer of fiber carcass cord fabric and positively wrapping, coating 1 layer of carcass with rubber, and rolling; and then 1 layer of fiber carcass ply and forward wrapping, 1 layer of carcass coating rubber, rolling, using a capsule reverse wrapping method to attach 2 symmetrical wear-resistant rubbers, 2 symmetrical shoulder pad rubbers, 2 symmetrical filling rubbers and 2 symmetrical sidewall rubbers, and rolling to obtain a section of tyre cylinder. The first-section forming is completed by a first-section forming machine, the combination of a first-section tire tube is completed on an aircraft tire forming machine, the tire is different from conventional radial vehicle tires, the types of rubber parts are various, each rubber part needs to be rolled, and finally a first-section tire blank is formed.
In a preferred embodiment, the attaching 2 symmetrical wear-resistant glues by using the capsule turn-up method comprises: and attaching the wear-resistant glue on a turn-up capsule, connecting the wear-resistant glue with the turn-up capsule, and turning over the wear-resistant glue layer in a capsule inflation turn-up mode to enable the wear-resistant glue layer to be tightly attached to the specified position of the opening of the green tire. Because the thickness of the wear-resistant glue is large, the process attaches the wear-resistant glue on the turn-up bladder, joints and then turns over the wear-resistant layer in a bladder inflation turn-up mode and then clings to the specified position of the tire blank opening, the turn-up process operation is easy to realize, the turn-up is smooth, the attachment is tight, the bilateral symmetry is good, and therefore the problems that the conventional radial vehicle tire is not solid in rolling, folds are formed, the rubber material is deformed in extension and serious potential quality hazards are caused by the fact that the conventional radial vehicle tire is attached and rolled in a rolling mode are solved.
In a preferred embodiment, the two-segment belt drum application comprises: firstly pasting a layer of cushion rubber sheet on a belt drum, finishing 2 layers of 1 period on the cushion rubber sheet layer by layer, continuously winding 6-8 belt layers in total in an S shape, pasting 1 layer of retreading base rubber after winding, then pasting a corrugated protective layer assembly and a tire tread, rolling layer by layer, and finishing belt layer winding, a corrugated protective layer and a tire tread assembly. The corrugated protective layer is a special part used on an aircraft tire, and is a semi-finished rubber part with the thickness of 2.3-3.0mm formed by coating glue on the upper and lower parts by using special aramid fiber wires in parallel at the interval of 120 pieces, the distance of 2.5-3.0mm, the amplitude of wave of 8-10mm and the wavelength of 28-32mm and rolling. The corrugated protective layer is flatly laid on the retreading base rubber on the belt ply, the butt joint angle is 45 degrees, the interface part is covered with a thin rubber sheet, and the butt joint is connected with the joint and compacted. The corrugated protection layer is used for tightening a belted layer group on the one hand, and provides a tire tread and a belted layer transition layer on the other hand, thereby optimizing the structural design, and effectively improving the puncture-proof characteristic of the aircraft tire as a puncture-proof layer of the aircraft tire. The corrugated protection layer effectively improves the uniformity of stress distribution on the width of the belted layer and reduces the edge stress of the belted layer. The corrugated protection layer effectively improves the uniformity of stress distribution on the width of the belted layer and reduces the edge stress of the belted layer, thereby solving the phenomenon of edge void of the belted layer.
In the process, the belt layer is formed by winding a belt strip, the belt strip is produced by arranging 7 nylon/aramid fiber composite cords in order and extruding and coating the rubber, the width of the belt strip is 10mm, the winding angle and the tire circumferential direction form 10-20 degrees, and a single strip and multiple turns of S-shaped winding is carried out by using a winding device to obtain a belt layer annular structure. The tire obtained by the process has the advantages that: (1) the nylon/aramid composite cord is used as the framework material of the tire, so that the excellent characteristics of the nylon/aramid composite cord can be reflected, and a good foundation is laid for meeting the use requirement of the radial aviation tire; (2) the multi-layer nylon/aramid fiber composite cord belt bundle structure layer can meet the use requirements of radial aircraft tires on high internal pressure, high speed, high load, large deformation and impact resistance. The conventional radial ply vehicle tire has no continuous single-strip multi-turn S-shaped winding method of the belt strip, and only 1 zero-degree belt layer is wound on the crown part of the tire body. The upper part of a carcass ply at the crown part of the tire is provided with a winding belted layer, the number of the belted layer is 6-8, 2 layers are arranged in one winding period, the winding period of the winding belted layer is converted and the width of the winding belted layer is gradually reduced layer by layer, the winding belted layer is combined together in an equal differential level half-overlapping winding mode, the angle of a cord line of the winding belted layer and the circumferential direction of the tire forms an angle of 10-20 degrees, the structure of the belted layer is wound to form an annular cylinder shape, wherein each layer of the belted layer is formed by winding a 10mm single belted. The belt structure has a spiral layer formed by spirally winding a non-stretchable and highly elastic nylon/aramid composite cord having a tensile strength of 1500MPa or more in the circumferential direction, and the annular belt structure provides the pneumatic aircraft tire with impact resistance and load resistance. The winding belt layer has a good tightening effect on the tire body and the tire crown part, the centrifugal force of the crown part is greatly reduced, the problem of tire body expansion is effectively solved, the performance requirements of large load and ultrahigh speed of the tire can be met, and the aviation tire can remarkably improve the partial abrasion of the tire shoulder part caused by 'dragging abrasion'.
In a preferred embodiment, the two-stage sizing drum sizing comprises: and combining the first section of tire blank, the tire tread, the belted layer and the corrugated protection layer assembly on a two-section forming machine, and completing the forming process of the whole aircraft tire through the links of pre-forming, super-forming and post-pressing combined rolling. Compared with the conventional radial vehicle tire, the shaping time and the shaping pressure of the shaping process are increased by 1 time, and the shaping quality is effectively ensured.
To more clearly and in detail describe the radial aircraft tire building process provided by the embodiments of the present invention, the following description will be given with reference to specific embodiments.
Example 1
The radial aircraft tire forming machine has the process layout as shown in figures 1, 2, 3, 4, 5, 6 and 7, the whole radial aircraft tire forming machine is arranged in a T shape as shown in figure 1, and the forming process steps are described as follows: the section of the feeding frame is distributed on the same side of the working area by taking the transverse direction as a transverse axis, and the feeding frames 1#, 2#, 3# and 4# are vertically arranged in parallel with the transverse axis and divided into a section of cloth cylinder attaching area and a section of forming area; the two sections are distributed on two sides by taking the longitudinal direction as the longitudinal axis and are divided into a two-section belted drum attaching area and a two-section shaping drum shaping area. Tensioning adjusting device 17, belted layer winding storage device 18, ripple protective layer feed frame 19, ripple protective layer cutting device 20, retreading base rubber sheet feedway 22 distribute in the different sides of workspace, and tread feed frame 15, tread feed dolly 16 distribute in the workspace homonymy. The first-stage and second-stage semi-finished product transfer is completed by an overhead gantry suspension type automatic conveying device 8, so that the semi-finished product transfer is efficient and smooth. The process layout of the forming machine is called a radial aircraft tire 'T + 2' forming machine layout method (2 refers to a first stage and a second stage).
The flat drum rigging machine host 1 provides support, expansion and contraction and transverse movement power for the flat drum 2;
the flat drum laminating machine main machine 1 and the flat drum 2 correspond to the No. 1 feeding frame at the position 2a, and laminating of the lining layer, the transition layer film and the No. 1 tire body cord fabric is realized;
the flat drum laminating machine main machine 1 and the flat drum 2 reach the position 2b under the action of the transverse driving force of the flat drum laminating machine main machine, correspond to the No. 2 feeding frame, after positioning, the upper layer 1 of tire body is coated with glue, and the first rolling is finished by utilizing the combined rolling device 3; then, coating rubber on the No. 2 tire body cord fabric and the upper tire body, and finishing secondary rolling by using the combined rolling device 3; then 3# carcass ply is added, a layer of carcass coating glue is pasted, a front feeding frame 4 is used for symmetrically pasting a reinforcing layer and a glue sheet, and a combined rolling device 3 is used for finishing the third rolling;
and (3) finishing the semi-finished composite part of the tire tube at the position 2b, enabling the flat drum laminating machine main machine 1 and the flat drum 2 to reach the position 2c under the action of transverse driving force of the flat drum laminating machine main machine 1, and taking down the tire tube by the automatic conveying device 8 to run to the position 2 d. The flat drum laminating machine main machine 1 and the flat drum 2 are reset to the position 2a to prepare for laminating the next tire tube;
the forming drum main machine 7 provides supporting, expansion and contraction and transverse translation power for the forming drum 6, and the tail seat 5 assists the forming drum main machine 7 and the forming drum 6 to complete forming processes of forward wrapping, ring buckling, reverse wrapping and the like of a section of tire tube. The gantry suspension type automatic conveying device 8 clamps the tire cylinder to move to the position 2d, at the moment, the forming drum 6 receives the tire cylinder at the position 2d, and the tail seat 5 reaches the position 5a under the action of the longitudinal driving of the position 5 b. Here, the tailstock 5, the forming drum 6 and the forming drum host 7 continue forming corresponding to the 3# supply frame: the finger-shaped sheet is wrapped positively, the ring is buckled by the ring buckling device, the capsule is wrapped reversely, the 4# tire body cord fabric is arranged, the tire body is wrapped positively, the rubber is coated on the tire body, the fourth rolling is finished by the combined pressing roller 9, then the 5# tire body cord fabric is arranged, the tire body is wrapped positively, the rubber is coated on the tire body, and the fifth rolling is finished by the combined pressing roller 9.
Under the action of the transverse driving force of the main machine 7 of the forming drum, the position 7a reaches the position 7b, and the reinforcing layer, the shoulder pad rubber and the filling rubber/wear-resistant rubber/sidewall rubber assembly are attached to the position corresponding to the No. 4 feeding frame. And under the action of the transverse driving force of the main forming drum 7, the position 7a is reached from the position 7b, and the last rolling of one section is finished by utilizing the combined pressing roller 9. At the moment, the tail seat 5 is reset from the position 5a to the position 5b under the action of longitudinal driving force, and the forming drum main machine 7 is in the reset position to prepare for forming the next green tire.
The gantry suspension type automatic conveying device 8 clamps a section of formed tire tube at the position 2d, longitudinally conveys the tire tube to a two-section forming machine forming drum, is matched and installed in place, and continues to be combined with a belt ply, a corrugated protective layer and a tire tread assembly finished in a two-section forming area.
In the figure, a shaping drum host 10, a shaping drum 11, a transfer ring 12, a belt drum 13 and a belt drum host 14 are two-section hosts, a belt winding, conveying, tensioning and adjusting device 17, a belt winding and storing device 18, a corrugated protective layer feeding frame 19, a corrugated protective layer cutting device 20 and a retreading base rubber sheet feeding device 22 are distributed on different sides of a working area, and a tread feeding frame 15 and a tread feeding trolley 16 are distributed on the same side of the working area.
The belt drum main machine 14 provides support, expansion and contraction and longitudinal translation power for the belt drum 13. The belt winding process comprises the following steps: a layer of buffer rubber sheet is firstly pasted on the belt drum 13, a plurality of layers of S-shaped belt layers are wound on the belt drum 13 by a belt layer winding storage device 18 and a belt layer winding device 23 (comprising a tensioning device, a winding head and the like), the winding head is provided with a rolling mechanism, the rolling is carried out layer by layer to form a cylindrical annular belt structure, and a layer of retreaded base rubber sheet is pasted by a retreaded base rubber sheet supply device 22.
Under the action of longitudinal driving force, the belt drum main machine 14 and the belt drum 13 reach 13b from 13a, and primary rolling of the belt drum 13 is completed by the combining and rolling device 21 (installed to 13b below the corrugated protection layer feeding frame). Utilize ripple protective layer feed frame 19, ripple protective layer cutting device 20 to pass through the feed frame conveyer belt and arrive on belted belt drum 13, accomplish the laminating of ripple protective layer, utilize deciliter rolling press device 21 to accomplish belted belt, the rolling press of heat preservation protective layer sub-assembly second time again. The tread feeding trolley 16 and the tread feeding frame 15 are used for completing the fitting of the tread, and the belt layer, the heat preservation protective layer and the tread assembly are rolled for the third time by the splitting and rolling device 21 at the last time.
The transfer ring 12 is used for transferring the belt layer, the corrugated protection layer and the tread composite formed by the belt drum to the two-section shaping drum 11 from the 13b position and returning to the transfer ring 12 to complete resetting. At this time, the belt drum 13 is driven longitudinally by the belt drum main machine 14 from the 13b position to the 13a position, the resetting is completed, and the next green tire belt layer is wound.
At the position of the two-section shaping drum 11, the composite parts such as a belt ply, a corrugated protection layer, a tire tread and the like and a section of tire tube which is automatically transmitted are pre-shaped, shaped and over-shaped under the driving of the main machine 10 of the shaping drum, and the whole molding process of the tire blank is completed under the action of the combined compression roller 24.
The transfer ring 12 reaches the shaping drum 11 from the transfer ring 12, the shaped complete embryo is taken down from the shaping drum and longitudinally translated to the transfer ring 12, and the embryo is taken up by the gantry suspension type automatic conveying device 8 and is unloaded.
The T +2 type radial aviation tyre forming machine is specially designed and manufactured to adapt to the features of various rubber parts and complicated process in the aviation tyre forming process. The whole layout structure is reasonable, the logistics of semi-finished products is smooth, the functions of matched equipment are complete, and a tire blank forming process is completed at one step from various semi-finished product rubber parts, a first-stage forming process and a second-stage forming process. Machines of this type represent a direction of development for aircraft tire building equipment.
Performance testing
The 49X 19R20 aviation tires developed by the invention have the advantages that the shift yield reaches 8 through trial production, and the detection qualified rate reaches more than 90%.
The aviation tire developed by the invention passes through dynamic simulation tests, and the test result meets the technical standard requirements issued by CAAC (China Central office of civil aviation). The test is passed through the CTSO (China technical Standard Specification) test, which is the airworthiness requirement and safety standard that the CAAC set airborne finished product system must meet. The aviation tire passes through a dynamic simulation test and a GJB test of the national military standard of the aviation tire.
First, performance test data analysis (taking 49 × 19R20 as an example):
1. static balance differential test
The static balance quantity required by the aviation radial tire reaches the standard requirement in GB/T-13655 2004 test method for static balance difference of aviation tire.
The method for testing the static balance difference of the aviation tires by using the dynamic balance testing machine for the FDBRC-6142TB-R type all-steel radial truck tire manufactured by the Japan International policy company extracts 10 aviation tires as testing base numbers, the standard deviation value is not more than 56N cm, the static balance difference of the 10 aviation tires is actually tested and controlled to be 15-34.5N cm, and the testing requirement of the static balance difference is met.
2. Laser nondestructive testing
In the aviation tires GBT9747-2008 'aviation tire test method' and GBJ108B-98 'military aviation tire test method', nondestructive testing is required to be checked. 10 aircraft tires were extracted and subjected to a systematic inspection in a comprehensive manner using INTACT1200 type laser non-destructive inspection equipment manufactured by Steinbichler, germany, wherein 1 of the aircraft tires had bubbles of about 0.2mm2 in the shoulder portion, and the rest were all qualified, with a qualification rate of 90%.
3. Hydraulic bursting test
The aviation tire water pressure burst test is specified in aviation tire GBT9747-2008 aviation tire test method and GBJ108B-98 military aviation tire test method.
A GC-YLY-100 type tire hydraulic bursting test machine produced by Qingdao high-level measurement is used for extracting 1 aircraft tire to carry out a hydraulic bursting test, the actually measured bursting pressure of 4650kPa is nearly 5 times of the standard internal pressure of 950kPa of the aircraft tire, and the performance requirement that the bursting pressure is greater than 4 times of the standard internal pressure is met. The batch of 10 tires adopt the same structural design, the explosion pressure is not large in up-down fluctuation, and the design requirements can be met.
4. Static load performance test
The static load performance test obtains parameters of the tire, such as the outer diameter, the section width, the static load radius, the sinking amount, the sinking rate, the load-deformation curve and the like. The national standard GB9747-2008 aviation tire test method and the national military standard GJB108B-98 military aviation tire test method are specified. Through extracting 1 aircraft tire test, the actual measurement outer diameter, section width, static load radius, sinkage rate and load-deformation curve, etc. satisfy the design requirement.
5. Durability test
According to the provisions of national standard GB9747-2008 aviation tire test method and national military standard GJB108B-98 military aviation tire test method, an aviation tire durability tester is selected according to aviation tire sliding test conditions, rated load or 1.2 times rated load, minimum speed of 64.4km/h, sliding distance of 10668m and the like, and model TJR-2-ORT (Y) engineering tire durability tester produced by Tianjin Jiuliang is selected to simulate aviation tire sliding tests, and all experimental data reach the standard.
6. Other tests
Other aspects of aircraft tire performance testing also include: static electricity conduction test, inflation outer edge test, weight detection, air tightness test, sealing pressure test, tensile property of tread rubber and sidewall rubber, interlaminar adhesion strength test and the like. These are not relevant to the present invention and are not described in detail.
Secondly, analyzing performance test data:
the dynamic simulation test result of the aircraft tire meets the technical standard requirement issued by CAAC (China Central aviation administration). The CTSO (China technical Standard regulation) is the minimum airworthiness requirement and the minimum safety standard which must be met by an airborne finished product system set by CAAC, and the CTSO dynamic test is of great importance. The dynamic simulation test method truly simulates various operating conditions of the aircraft tire on the runway according to the regulations of the national standard GB9747-2008 'aircraft tire test method' and the national military standard GJB108B-98 'military aircraft tire test method', and analyzes and researches the ground dynamic performance of the tire.
The aircraft tire developed by the invention adopts an aircraft tire testing machine produced by TS Testingservice GmbH German aachen test service GmbH as testing equipment. Through dynamic simulation tests, test results meet the technical standard requirements issued by CAAC (China civil aviation administration), and meanwhile, the performance technical requirements are tested through GJB of national military standards of aviation tires.
Claims (7)
1. The radial aircraft tire forming process is characterized by sequentially comprising the following steps of: the method comprises the following steps of first section cloth tube fitting, first section forming, second section belt bundle drum fitting and second section forming drum forming.
2. The radial aircraft tire building process of claim 1, wherein said length of cloth drum fit comprises: 4, laminating the air-tight layer sheets; 1 layer of isolation rubber sheet is attached, 1 layer of fiber carcass cord is attached, and 1 layer of carcass is attached by coating rubber; coating glue on the 2 nd layer of fiber carcass cord and the 2 nd layer of carcass for gluing; coating rubber on the 3 rd layer of fiber carcass cord and the 3 rd layer of carcass for gluing; and (3) laminating the 1 layer of two symmetrical steel wire ring reinforcing layers and the rubber sheets to obtain a cloth cylinder laminating assembly.
3. The radial aircraft tire building process of claim 2, wherein said applying of the 4-ply air barrier laminate comprises crimping said air barrier laminate having a width of 560-600mm and continuously winding the laminate on a flat drum laminator head for 4 cycles.
4. The radial aircraft tire building process of claim 1 wherein said one segment of building comprises: mounting the cloth tube fitting assembly on a section of machine head of a section of forming machine, sequentially carrying out centering, expanding and rolling on a rubber component, positively wrapping a circular steel wire ring and a triangular rubber core assembly by a finger-shaped sheet, reversely wrapping a capsule, coating 1 layer of fiber carcass cord fabric and positively wrapping, coating 1 layer of carcass with rubber, and rolling; and then 1 layer of fiber carcass ply and forward wrapping, 1 layer of carcass coating rubber, rolling, using a capsule reverse wrapping method to attach 2 symmetrical wear-resistant rubbers, 2 symmetrical shoulder pad rubbers, 2 symmetrical filling rubbers and 2 symmetrical sidewall rubbers, and rolling to obtain a section of carcass.
5. The radial aircraft tire building process of claim 4, wherein said applying 2 strips of symmetrical wear-resistant glue using a bladder turn-up method comprises: and attaching the wear-resistant glue on a turn-up capsule, connecting the wear-resistant glue with the turn-up capsule, and turning over the wear-resistant glue layer in a capsule inflation turn-up mode to enable the wear-resistant glue layer to be tightly attached to the specified position of the opening of the green tire.
6. The radial aircraft tire building process of claim 1 wherein the two-stage belt drum application comprises: a layer of cushion rubber sheet is firstly pasted on a belt drum (13), 2 layers in 1 period are completed on the cushion rubber sheet layer by layer, 6-8 layers of belt layers are wound in an S-shaped continuous mode in total, 1 layer of retreading base rubber is pasted after winding is completed, then a corrugated protective layer assembly and a tire tread are pasted, rolling is carried out layer by layer, and belt layer winding, a corrugated protective layer and a tire tread assembly are completed.
7. The radial aircraft tire building process of claim 1 wherein the two-stage sizing drum sizing comprises: and combining the first-section green tire, the tire tread, the belted layer and the corrugated protection layer assembly on a two-section forming machine, and completing the forming process of the whole aircraft tire green tire through the links of pre-forming, super-forming and post-pressing combined rolling.
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| CN113619173A (en) * | 2021-07-26 | 2021-11-09 | 厦门洪海机械有限公司 | One-section main machine structure of light truck tire forming machine and forming method |
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