CN118082230A - Machine body barrel section assembly type co-curing positioning forming device and positioning forming method - Google Patents
Machine body barrel section assembly type co-curing positioning forming device and positioning forming method Download PDFInfo
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- CN118082230A CN118082230A CN202211493124.9A CN202211493124A CN118082230A CN 118082230 A CN118082230 A CN 118082230A CN 202211493124 A CN202211493124 A CN 202211493124A CN 118082230 A CN118082230 A CN 118082230A
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- 238000000465 moulding Methods 0.000 claims description 23
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- 230000008859 change Effects 0.000 claims description 5
- 238000011946 reduction process Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 description 5
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
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- 230000008602 contraction Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 239000002828 fuel tank Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000009471 action Effects 0.000 description 1
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- 238000005516 engineering process Methods 0.000 description 1
- 235000000396 iron Nutrition 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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Abstract
The invention relates to an assembly type co-curing positioning and forming device and a positioning and forming method for a barrel section of a machine body. The forming device comprises a tool frame, a positioning shaft and at least two frame positioner components; each frame positioner component comprises a frame positioner, a positioning pin and a frame positioner web plate, wherein the frame positioner is fixedly connected with the frame positioner web plate, the frame positioner and the frame positioner web plate are sleeved on the positioning shaft and can slide along the axial direction of the positioning shaft, and the frame positioner web plate are positioned on the positioning shaft through the positioning pin. The invention provides an assembly type co-curing process for a large-size fuselage barrel section oil tank complex structure, which is assembled at normal temperature and high precision and is formed by co-curing high-temperature assemblies.
Description
Technical Field
The invention relates to an assembly type co-curing positioning forming device and a positioning forming method suitable for common-temperature high-precision assembly and high-temperature assembly co-curing forming of complex structures such as large-size fuselage barrel section oil tanks and the like, and belongs to the technical field of composite material assembly and forming.
Background
Co-curing technology for large-size complex structures such as composite fuel tanks has been the goal of overall aircraft fuel tank development work. The sealing of large-scale oil tank is the important difficulty of oil tank manufacturing, has directly influenced the economic cost and the life of oil tank. The integrally formed oil tank has great advantages in tightness and service life, and the inside of the oil tank structure of the barrel section of the machine body is provided with a plurality of structures such as an end frame, a stringer, an embedded metal block and the like, so that the integrally formed oil tank has great difficulty in assembly and forming processes.
The large-size fuselage tank assembly requires that composite parts be assembled into an assembly, and then an outermost skin lay-up is performed on the assembled assembly, followed by high temperature co-curing in an autoclave. The traditional die can not realize high-precision assembly, and the traditional assembly fixture can not realize uniform thermal expansion coefficients and directions of all positioners during high-temperature forming, and can not meet new process requirements.
Disclosure of Invention
Aiming at the problems, the invention realizes an assembly type co-curing positioning and forming device and a positioning and forming method suitable for complex structures such as large-size fuselage barrel section oil tanks, and can realize normal-temperature high-precision assembly and high-temperature assembly co-curing and forming of the complex structures such as large-size fuselage barrel section oil tanks.
The invention can assemble the complex structure composite material components of the frame, the stringer, the embedded metal block and the like at room temperature with high precision, and then spread new product structure on the outer layer of the components by using prepreg, and enter an autoclave or an oven to realize simultaneous co-curing molding. The structural strength of the assembly of the molding process method is obviously improved, the mechanical connection of standard components can be reduced by more than 90%, the tightness of the integral oil tank of the assembly is improved, and the integral appearance precision of the co-cured assembly is ensured. The invention can effectively solve the problem of high-precision assembly of the assembly type frame at room temperature and the problem of deformation along with thermal expansion and contraction of the tool in the process of product molding caused by different thermal expansion coefficients of the tool material and the composite material in the process of temperature change.
The invention relates to an assembly type co-curing positioning and forming device for a barrel section of a machine body, which comprises a tool frame, a positioning shaft and at least two frame positioner assemblies, wherein the positioning shaft is fixedly arranged on the tool frame; each frame positioner component comprises a frame positioner, a positioning pin and a frame positioner web plate, wherein the frame positioner is fixedly connected with the frame positioner web plate, the frame positioner and the frame positioner web plate are sleeved on the positioning shaft and can slide along the axial direction of the positioning shaft, and the frame positioner web plate are positioned on the positioning shaft through the positioning pin.
Further, when high-precision assembly of the composite material product to be molded is performed at room temperature, all the positioning pins are locked to fix the frame positioner and the web plate of the frame positioner on the positioning shaft; during high-temperature molding, only one positioning pin is reserved, and all other positioning pins are removed or loosened, so that the frame positioner and the frame positioner web plate for removing or loosening the positioning pins can slide along the axial direction of the positioning shaft, and the axial deformation of the composite material product caused by inconsistent expansion coefficients of the tooling material and the composite material product to be molded is eliminated.
Further, the frame locator web is made of the same composite material as the composite material product to be molded, so that the composite material product is not deformed in the circumferential direction during the temperature change of the molding process.
Further, the outer diameter of the frame locator web is matched with the inner diameter of the composite material product to be molded, so that the composite material product to be molded is positioned.
Further, the frame locator web is disc-shaped, and a hole is formed in the middle of the frame locator web and used for penetrating a locating shaft.
Further, a sliding rail orientation pin and a sliding rail groove matched with the sliding rail orientation pin are arranged between the frame positioner and the positioning shaft, the sliding rail groove is arranged along the axial direction of the positioning shaft, and the sliding rail orientation pin can slide along the sliding rail groove, so that the frame positioner only moves along the axial direction of the positioning shaft on the positioning shaft.
Further, the sliding rail groove is formed in the frame positioner, and the sliding rail orientation pin is arranged on the positioning shaft.
The invention relates to a method for forming an assembled co-curing positioning of a barrel section of a machine body, which adopts the assembled co-curing positioning forming device of the barrel section of the machine body to realize a forming process, and comprises the following steps:
when the high-precision assembly of the composite material product to be molded is carried out at room temperature, locking all positioning pins so as to fix the frame positioner and the web plate of the frame positioner on the positioning shaft;
During high-temperature molding, only one positioning pin is reserved, and all other positioning pins are removed or loosened, so that a frame positioner and a frame positioner web plate for removing or loosening the positioning pins can slide along the axial direction of a positioning shaft, and the axial deformation of a composite material product caused by inconsistent expansion coefficients of a tooling material and the composite material product to be molded is eliminated;
The frame locator web is made of the same composite material as the composite material product to be molded, so that the composite material product is not deformed in the circumferential direction in the temperature change process of the molding process.
Further, in the temperature rising process, the tool frame and the positioning shaft can thermally expand along the axial direction of the positioning shaft, the frame positioner of the locking positioning pin takes the positioning pin of the tool frame and the positioning shaft as a positioning reference, the thermal expansion coefficient of the composite material product is close to 0, the frame positioner of the dismantling or loosening positioning pin takes the composite material product as the positioning reference, and the frame positioner of the dismantling or loosening positioning pin and the web plate of the frame positioner slide along the axial direction of the positioning shaft through the sliding rail positioning pin and the sliding rail groove, so that the tool frame and the web plate stay at the theoretical assembly position in the normal temperature state, and meanwhile, the forming strength support of the circumferential direction of the product is completed.
Further, in the temperature reduction process, the tool frame and the positioning shaft undergo cold shrinkage along the axial direction of the positioning shaft, and the frame positioner web plate for dismantling or loosening the positioning pin slide along the axial direction of the positioning shaft through the slide rail orientation pin and the slide rail groove, so that the tool frame and the positioning shaft stay at an assembly theoretical position in a normal temperature state; and after the temperature is restored to the room temperature state, the removed or loosened positioning pin is locked again, and repositioning of the product is completed.
Compared with the prior art, the invention has the beneficial effects that:
(1) According to the invention, the influence on the product caused by the longitudinal thermal expansion of the tool is eliminated in a unique way, and the tool positioner is enabled to keep static under the action of the slide block in the thermal expansion process through the directional slide block, so that the product cannot deform along with the tool. Meanwhile, the positioning precision of the product and the strength required during molding can be ensured.
(2) Aiming at the characteristic that the thermal expansion coefficient of the composite material is close to 0, the invention adopts the composite material as the manufacturing material of the circumferential positioner of the assembly tool, and ensures that the product cannot be thermally expanded and deformed in the high-temperature forming process.
(3) The invention solves the technological problem that the tooling can assemble composite material components and then co-cure the composite material components to form integrally, and the outline of the product and the assembly air tightness meet the design requirements.
(4) The invention is hopeful to become a main process mode for integrally forming the large-size composite material oil tank assembly in the future. The method has good universality in the production process of other products, can reduce the processing cost and time, and increases the product income;
(5) By adopting the method, the plurality of forming tools and the plurality of assembling tools are combined into one tool, so that the product manufacturing can be completed, the waste part rate is reduced while a large amount of production time is saved, and the added value of the product is improved;
(6) The invention has good popularization and application value, and can effectively promote the development and application of the co-curing molding of the integral large-size composite material oil tank of the composite material in the aerospace field.
Drawings
FIG. 1 is a front view of an assembled co-curing positioning and molding device for a large-size fuselage tank of the present invention; wherein 1-6 are frame locators, 7-12 are locating pins, 13-18 are frame locator webs, 19 are locating shafts, and 20 are tool frames.
Fig. 2 is a schematic view of the frame positioner 1, the positioning pin 7, and the frame positioner web 13 mounted on the positioning shaft 19.
FIG. 3 is a front view of a frame locator web of the present invention;
FIG. 4 is a cross-sectional view of a slide rail slot of the present invention; wherein 22 is a slide rail orientation pin, and 21 is a slide rail groove;
Detailed Description
The present invention will be described in detail with reference to specific examples and drawings.
The principle of the invention is as follows: the first step, the frock is in product length direction, and all locators all adopt slide rail device, and when the high accuracy assembly of room temperature, adopt locating pin location lock to die, and when high temperature shaping, only remain one end locating pin, demolish all remaining locating pins, let the locator be in can follow the state of locating axial high accuracy slip, can eliminate the condition that the combined material axial deformation that leads to because of the factor of expansion of frock material and combined material product thermal expansion coefficient inconsistent like this. And secondly, when the materials of the tool circumferential positioner are selected, the composite materials with the same resin system as the product are adopted for molding and machining, and as the composite material positioner and the composite material product are made of the same materials, the thermal expansion coefficients are matched, so that the circumferential deformation condition of the composite material product is eliminated.
In one embodiment of the invention, an assembled co-curing positioning and forming device suitable for a large-size fuselage barrel section oil tank is provided, and as shown in fig. 1, the assembled co-curing positioning and forming device comprises a frame positioner 1-6, a positioning pin 7-12, a frame positioner web 13-18, a positioning shaft 19 and a tool frame 20. The left and right sides of the positioning shaft 19 are respectively provided with a handle for rotating the positioning shaft. The tool frame 20 is a base and a supporting structure below the positioning shaft 19, and may include a supporting seat at the bottom, angle irons for reinforcement, brackets for preventing deformation of the positioning shaft, and the like, and is mainly used for supporting and fixing the positioning shaft 19.
Wherein one frame locator, one locating pin, one frame locator web constitutes one frame locator assembly, e.g. frame locator 1, locating pin 7, frame locator web 13 constitutes one frame locator assembly, fig. 1 totaling 6 frame locator assemblies. Each frame retainer comprises a sleeve structure that fits over the retainer shaft 19. Taking the frame positioner 1 as an example, a positioning pin 7 is arranged on the frame positioner. When the positioning pin 7 is locked, the frame positioner 1 can be positioned on the positioning shaft 19.
Taking the frame positioner 1 as an example, the frame positioner web 13 is fixed to one side of the frame positioner 1 by bolts or the like, as shown in fig. 1 and 2. The frame positioner web 13 is disc-shaped, as shown in fig. 3, and has a hole in the middle for passing through the positioning shaft 19, and in addition, positioning holes, such as positioning holes for positioning a product frame, tool ball positioning holes of a laser tracker, and the like, may be further provided on the frame positioner web 13. The outer diameter of the frame locator web 13 is designed to match the inner diameter of the composite product to be formed to locate the composite product to be formed.
Wherein the frame retainer webs 13-18 are of the same composite material as the product to be formed and have an expansion coefficient approaching 0 so that the product will not deform in the circumferential direction during the temperature change (increase or decrease) of the forming process.
In the embodiment shown in fig. 1, after locking the locating pins 7-12, the frame locator 1-6, the frame locator web 13-18, may be positioned on the locating shaft 19. The positioning shaft 19 ensures the positioning precision of the whole product, and simultaneously ensures that the product can keep high precision in the axial direction and cannot be deformed due to expansion and contraction of the tool. The high-precision locating pins 7-12 can ensure the fixture to be located, and can be used for locating again with high precision even if the fixture is repeatedly disassembled, and the high-precision location can be maintained before and after the product and the fixture enter the autoclave.
In order to enable the frame positioner 1-6 to move on the positioning shaft only along the axial direction of the positioning shaft, the frame positioner 1-6 is prevented from rotating on the positioning shaft so as to accurately position a product to be formed, and a slide rail orientation pin and a slide rail groove matched with the slide rail orientation pin are arranged between the frame positioner 1-6 and the positioning shaft 19. As shown in fig. 4, the right side is a cross-sectional view of the positioning shaft 19, the slide rail groove 21 is disposed on the frame positioner (e.g., the frame positioner 1), the slide rail orientation pin 22 is disposed on the positioning shaft 19, and in other embodiments, the slide rail groove may be disposed on the positioning shaft, and the slide rail orientation pin is disposed on the frame positioner. The slide rail groove 21 is arranged along the axial direction of the positioning shaft 19, and the slide rail orientation pin 22 can slide along the slide rail groove 20, so that the frame positioner is ensured not to rotate when sliding along the positioning shaft 19.
In one embodiment of the present invention, a molding method implemented by the above-mentioned fabricated co-curing positioning molding device is provided, which specifically includes the following steps:
1) The locating pins 7-12 are locked to locate the frame locators 1-6 and frame locator webs 13-18 on the locating shafts 19.
2) The frame of the composite material product to be formed (i.e., the product skeleton, such as carbon fiber preform, etc.) is positioned on the frame positioner No. 1-6 assemblies and the frame positioner webs 13-18, i.e., the frame of the composite material product to be formed (such as carbon fiber preform, etc.) is sleeved outside the frame positioner webs 13-18, and the frame of the composite material product is positioned by the frame positioner webs 13-18.
3) And (3) dismantling or loosening the No. 8-12 locating pins, only keeping the No. 7 locating pins (in a locking state), and then enabling the frame of the composite material product and the assembled co-curing locating and forming mechanism to enter an autoclave for high-temperature treatment.
4) During the temperature rise, the tool frame and the positioning shaft undergo thermal expansion (for example, expansion coefficient is 1mmx10 -5) in the axial direction, that is, elongation displacement occurs. At this time, the frame positioner 1 uses the No. 7 positioning pin as a positioning reference, the thermal expansion coefficient of the composite material product is close to 0, the frame positioner 2-6 uses the composite material product as a positioning reference, and the frame positioner 2-6 and the frame positioner web 14-18 slide along the axial direction of the positioning shaft through the slide rail orientation pin 22 and the slide rail groove 21, so that the frame positioner stays at the assembly theoretical position in the normal temperature state, and meanwhile, the support of the forming strength in the circumferential direction of the product is completed.
In the process of temperature rise, the frame positioners 2-6 are in a state capable of sliding along the positioning axial direction with high precision, so that the situation that the composite material is deformed axially due to the fact that the expansion coefficient of the tooling material is inconsistent with the thermal expansion coefficient of the composite material product can be eliminated.
5) In the process of temperature rise, the frame positioner webs 13-18 are made of the same composite material as the product to be formed, and the expansion coefficient of the composite material is close to 0, so that the product cannot deform in the circumferential direction.
6) After the product is formed, the temperature starts to be reduced, the tooling frame and the positioning shaft shrink in the axial direction of the positioning shaft, namely shortening displacement is generated, and the frame positioner 2-6 and the frame positioner web 14-18 slide along the axial direction of the positioning shaft through the slide rail orientation pin 22 and the slide rail groove 21, so that the tooling frame and the positioning shaft stay at the assembly theoretical position in the normal temperature state.
In the temperature reduction process, the frame positioners 2-6 are in a state capable of sliding along the positioning axial direction with high precision, so that the situation that the composite material is deformed axially due to the fact that the expansion coefficient of the tooling material is inconsistent with the thermal expansion coefficient of the composite material product can be eliminated.
7) During the temperature decrease, the frame retainer webs 13-18 are such that the product will not deform in the circumferential direction due to the coefficient of expansion approaching 0.
8) And (3) recovering the temperature to the room temperature, reinserting the positioning pins 8-12 into the lock, and completing repositioning of the product and ending of the assembly.
In the embodiment shown in fig. 1, the frame locator web is secured by only one side of the frame locator. In other embodiments, a frame positioner may be disposed on two sides of the frame positioner web, where the structures of the two frame positioners may be symmetrically designed to clamp the frame positioner web therebetween, so as to better fix the frame positioner web.
In the embodiment shown in fig. 1, there are a total of 6 frame locator assemblies (one frame locator assembly includes one frame locator, one locating pin, one frame locator web). In other embodiments, other numbers of frame locator assemblies may be provided, such as 4, 5, 8, 10, etc., depending on the configuration, size, etc. of the product to be formed.
In summary, the invention provides an assembly type co-curing process for large-size fuselage barrel section oil tanks and other complex structures, which are formed by co-curing components at normal temperature and high precision. The high-temperature linear expansion deformation device is designed and released in the longitudinal length direction and the circumferential direction of the tool, meanwhile, the part materials at the key positions of the tool are made of the same composite material as the molded product, and the expansion coefficient of the assembly type frame is matched with the molded product by combining the above methods.
The invention is not described in detail in a manner known to those skilled in the art.
The above-disclosed embodiments of the present invention are intended to aid in understanding the contents of the present invention and to enable the same to be carried into practice, and it will be understood by those of ordinary skill in the art that various alternatives, variations and modifications are possible without departing from the spirit and scope of the invention. The invention should not be limited to what has been disclosed in the examples of the specification, but rather by the scope of the invention as defined in the claims.
Claims (10)
1. The machine body barrel section assembly type co-curing positioning and forming device is characterized by comprising a tool frame, a positioning shaft and at least two frame positioner assemblies, wherein the positioning shaft is fixedly arranged on the tool frame, and the frame positioner assemblies are arranged on the positioning shaft; each frame positioner component comprises a frame positioner, a positioning pin and a frame positioner web plate, wherein the frame positioner is fixedly connected with the frame positioner web plate, the frame positioner and the frame positioner web plate are sleeved on the positioning shaft and can slide along the axial direction of the positioning shaft, and the frame positioner web plate are positioned on the positioning shaft through the positioning pin.
2. The fabricated co-curing alignment molding device of the fuselage barrel section of claim 1, wherein all alignment pins are locked to secure the frame aligners and frame aligner webs on the alignment shaft when high precision assembly of the composite product to be molded is performed at room temperature; during high-temperature molding, only one positioning pin is reserved, and all other positioning pins are removed or loosened, so that the frame positioner and the frame positioner web plate for removing or loosening the positioning pins can slide along the axial direction of the positioning shaft, and the axial deformation of the composite material product caused by inconsistent expansion coefficients of the tooling material and the composite material product to be molded is eliminated.
3. The fuselage barrel section assembled co-cure location molding apparatus of claim 1, wherein the frame locator web is of the same composite material as the composite material product to be molded such that the composite material product does not deform in the circumferential direction during temperature changes in the molding process.
4. The fabricated co-curing positioning and molding device for a fuselage barrel section according to claim 1, wherein the outer diameter of the frame locator web is designed to match the inner diameter of the composite product to be molded to position the composite product to be molded.
5. The fabricated co-curing alignment molding device of a fuselage barrel section of claim 1, wherein the frame locator web is disc-shaped with a hole in the middle for passing through an alignment shaft.
6. The fabricated co-curing positioning and molding device for the barrel section of the machine body according to claim 1, wherein a slide rail orientation pin and a slide rail groove matched with the slide rail orientation pin are arranged between the frame positioner and the positioning shaft, the slide rail groove is arranged along the axial direction of the positioning shaft, and the slide rail orientation pin can slide along the slide rail groove so that the frame positioner can move on the positioning shaft only along the axial direction of the positioning shaft.
7. The fabricated co-curing alignment molding device of claim 6, wherein the slide rail slot is disposed on the frame alignment and the slide rail orientation pin is disposed on the alignment shaft.
8. A method for forming a barrel section of a fuselage by assembling co-curing and positioning, characterized in that the method adopts the barrel section of the fuselage according to any one of claims 1 to 7 to realize the forming process, and comprises the following steps:
when the high-precision assembly of the composite material product to be molded is carried out at room temperature, locking all positioning pins so as to fix the frame positioner and the web plate of the frame positioner on the positioning shaft;
During high-temperature molding, only one positioning pin is reserved, and all other positioning pins are removed or loosened, so that a frame positioner and a frame positioner web plate for removing or loosening the positioning pins can slide along the axial direction of a positioning shaft, and the axial deformation of a composite material product caused by inconsistent expansion coefficients of a tooling material and the composite material product to be molded is eliminated;
The frame locator web is made of the same composite material as the composite material product to be molded, so that the composite material product is not deformed in the circumferential direction in the temperature change process of the molding process.
9. The method according to claim 8, wherein during the temperature rise process, the tool frame and the positioning shaft are thermally expanded along the axial direction of the positioning shaft, the frame positioner of the locking positioning pin takes the positioning pin as a positioning reference, the thermal expansion coefficient of the composite material product is approximately 0, the frame positioner of the dismantling or loosening positioning pin takes the composite material product as a positioning reference, and the frame positioner of the dismantling or loosening positioning pin and the frame positioner web slide along the axial direction of the positioning shaft through the slide rail positioning pin and the slide rail groove, so that the tool frame and the positioning shaft are stopped at the assembly theoretical position in the normal temperature state, and meanwhile, the support of the forming strength of the product in the circumferential direction is completed.
10. The method according to claim 8, wherein during the temperature reduction process, the tooling frame and the positioning shaft undergo cold shrinkage along the axial direction of the positioning shaft, and the frame positioner web for removing or releasing the positioning pin slide along the axial direction of the positioning shaft through the slide rail orientation pin and the slide rail groove, so as to stay at the theoretical assembly position at the normal temperature; and after the temperature is restored to the room temperature state, the removed or loosened positioning pin is locked again, and repositioning of the product is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211493124.9A CN118082230A (en) | 2022-11-25 | 2022-11-25 | Machine body barrel section assembly type co-curing positioning forming device and positioning forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211493124.9A CN118082230A (en) | 2022-11-25 | 2022-11-25 | Machine body barrel section assembly type co-curing positioning forming device and positioning forming method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118082230A true CN118082230A (en) | 2024-05-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211493124.9A Pending CN118082230A (en) | 2022-11-25 | 2022-11-25 | Machine body barrel section assembly type co-curing positioning forming device and positioning forming method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118082230A (en) |
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- 2022-11-25 CN CN202211493124.9A patent/CN118082230A/en active Pending
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