CN115107299B - Vertical-tail integral beam paving method - Google Patents
Vertical-tail integral beam paving method Download PDFInfo
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- CN115107299B CN115107299B CN202210780708.8A CN202210780708A CN115107299B CN 115107299 B CN115107299 B CN 115107299B CN 202210780708 A CN202210780708 A CN 202210780708A CN 115107299 B CN115107299 B CN 115107299B
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- 238000000034 method Methods 0.000 title claims abstract description 28
- 239000002131 composite material Substances 0.000 claims abstract description 52
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 12
- 239000000835 fiber Substances 0.000 claims abstract description 12
- 239000000741 silica gel Substances 0.000 claims abstract description 12
- 229910002027 silica gel Inorganic materials 0.000 claims abstract description 12
- 238000007711 solidification Methods 0.000 claims abstract description 7
- 230000008023 solidification Effects 0.000 claims abstract description 7
- 239000011152 fibreglass Substances 0.000 claims description 12
- 238000003754 machining Methods 0.000 claims description 10
- 230000008569 process Effects 0.000 claims description 9
- 239000011347 resin Substances 0.000 claims description 7
- 229920005989 resin Polymers 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 6
- 239000004917 carbon fiber Substances 0.000 claims description 6
- 238000001514 detection method Methods 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- 238000005259 measurement Methods 0.000 claims description 5
- 238000009825 accumulation Methods 0.000 claims description 3
- 238000004458 analytical method Methods 0.000 claims description 3
- 230000001680 brushing effect Effects 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 230000013011 mating Effects 0.000 claims description 3
- 238000003801 milling Methods 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 5
- 230000007547 defect Effects 0.000 description 7
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000000465 moulding Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229920000832 Cutin Polymers 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 235000015067 sauces Nutrition 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000008961 swelling Effects 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
- 238000004383 yellowing Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/386—Automated tape laying [ATL]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- 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
-
- 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
Abstract
The invention discloses a vertical-tail integral beam paving method, which adopts a mode of singly paving an upper web plate, a lower web plate and a rim strip, and jointly solidifying and forming three components, and comprises the following steps: (a) paving flat plates on the upper die and the lower die to ensure the appearance of the part; (b) The upper die is preformed by a thermal diaphragm forming die, and the lower die is preformed by a thermal diaphragm forming die of a lower die forming tool; (c) combining the upper die and the lower die through positioning pins; (d) removing the upper hot diaphragm forming die; (e) installing a composite stop on the inner surface of the upper die; (f) Filling 0-degree fiber in an R angle area of the upper die and the lower die, paving two side edge strips, and forming by adopting an automatic tape paving machine; (g) And installing composite silica gel soft cover plates on two sides of the upper die and the lower die for assembly and solidification. According to the vertical whole beam, the upper web plate and the edge strips are respectively paved by using the forming die and the composite material cover plate, and the structural design of the composite material cover plate and the silica gel soft die is effectively controlled aiming at thickness deviation and damage to an octagonal area.
Description
Technical Field
The invention relates to the technical field of manufacturing processes of vertical-tail integral beams of aircrafts, in particular to a method for paving vertical-tail integral beams.
Background
At present, the traditional vertical-tail integral beam layering method adopts a mould pressing mode, numerical control machining scribing is adopted on an upper mould body and a lower mould body of a forming mould, layering positions of carbon fiber prepregs are determined, the upper mould body and the lower mould body are separately paved, the upper mould body and the lower mould body are folded after layering is finished, and are fastened by means of bolts and positioning pins, but the upper mould body and the lower mould body are different in shrinkage ratio when being solidified with the prepregs, local materials cannot be compacted, local glue-lacking phenomenon can occur after solidification, and the mode is difficult and troublesome for manual operation.
The prior art mainly has the following defects: (1) the formation of the octagonal area is difficult to control, and is easy to fold and bulge; (2) All surfaces of the vertical-tail integral beam web and the L-shaped side edges and R angles (fillets) are required to ensure the molding quality, and the molding quality is difficult to control.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provide a vertical-tail integral beam paving method, wherein a forming die and a composite material cover plate are respectively used for paving a web plate, an upper web plate and a rim strip on the vertical-tail integral beam, and the structural designs of the composite material cover plate and a silica gel soft die are effectively controlled aiming at thickness deviation and damage of an octagonal region; when the forming die is paved, the laser positioning instrument is used, so that the operation of workers is simplified, and the probability of human defects is reduced.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
the method for paving the vertical whole beam adopts the mode of singly paving an upper web plate, a lower web plate and a rim strip, and three components are jointly solidified and molded, and comprises the following steps:
(a) The upper die and the lower die are paved and pasted with flat plates, so that the appearance of the part is ensured;
(b) The upper C and the lower C are preformed through a thermal diaphragm forming die;
(c) The upper die and the lower die are combined through a locating pin;
(d) Removing the upper mould thermal diaphragm forming mould;
(e) A composite material stop block is arranged on the inner surface of the upper die;
(f) Filling 0-degree fiber in an R angle area where the upper die and the lower die are combined, paving two side edge strips, and forming by adopting an automatic tape paving machine;
(g) And installing composite silica gel soft cover plates on two sides of the upper die and the lower die for assembly and solidification.
Further, for the thickness deviation and the lossless control of the octagonal region, the thickness deviation problem is solved by designing an independent composite stop block, and the glass fiber reinforced plastic cover plate for the octagonal region is optimized, and the method further comprises the following steps:
(1) Designing a composite material stop block forming die: the composite material stop block forming die is manufactured by adopting Q235 numerical control machining, and according to analysis of a post Liang Lingjian three-coordinate detection result, the outward expansion deformation of the part is avoided in the process of Liang Lingjian after the subsequent forming, the rebound angle is increased, and the scaling factor is increased;
(2) The composite upper die still adopts the original left and right split die form, so that the die is convenient to be removed, the middle is matched with an inclined plane and made into a spigot form, a plurality of connecting band plates, positioning holes and threaded holes are added in the length direction, pre-buried metal blocks are positioned according to laser when a composite upper die stop block is paved, and after solidification is finished, the positions of the connecting band plates are subjected to numerical control brushing/milling, and the threaded holes are manufactured;
(3) Positioning the composite material stop block: the two ends of the die are positioned by using precision holes, the positioning holes are oblong holes, and the corresponding lower die metal tool is provided with positioning holes;
(4) The middle of the composite material stop block is opened at the protruding part of the product, the opening is opened to be single-side 5mm, and silica gel is placed at the opening part when the product is solidified, so that partial under-pressure of the product is prevented;
(5) Lossless control of octagon areas: the octagonal area is changed into the glass fiber reinforced plastic cover plate with the thickness of 0.3mm, and the glass fiber reinforced plastic cover plate is polished into a slope at the front edge of the glass fiber reinforced plastic cover plate, so that the quality influence on the product caused by overlarge step difference in the curing process of the product is avoided.
Further, as the vertical whole beam is mainly constructed by bearing the aircraft wallboard, the precision requirements of the carbon fiber laying position and angle are quite high, and the vertical whole beam also adopts the following technical method:
checking thickness of the composite part: at least 5 measuring points are arranged in the same thickness area, the 5 measuring points all need to meet the thickness tolerance requirement, and the measuring data keep two decimal places; the ply transition region does not require measurement of part thickness, for an assembled thickness t tolerance of + -8%
Tolerance of 10% for thickness of non-critical structural areas without mating relationship; the tolerance of the thickness of the R angle area of the composite material part is +/-10%, or the tolerance of the R angle size is measured, wherein the tolerance is +/-0.25 t, and t is the corner/R angle theoretical thickness;
machining surface profile is not more than 0.2mm, damage to the basic layering is forbidden during machining, and the part profile is 0.75mm;
the surface of the composite material part should be smooth and flat, unidirectional tape and fabric fibers are clearly visible, the surface fibers are uniformly covered by resin, and no obvious resin accumulation is allowed.
According to the method for paving the vertical whole beam, disclosed by the invention, the upper web plate and the edge strips of the vertical whole beam are respectively paved by using the forming die and the composite material cover plate, and the structural design of the composite material cover plate and the silica gel soft die is effectively controlled aiming at thickness deviation and damage of an octagonal region; when the forming die is used for layering, a laser positioning instrument is used, so that the operation of workers is simplified, and the probability of human defects is reduced.
Drawings
FIG. 1 is a schematic view of a vertical tail integral beam structure of the present invention;
FIG. 2 is a schematic view of the vertical integral beam structure of the present invention;
FIG. 3 is a schematic view of the composite stopper according to the present invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention is described in further detail below with reference to the accompanying drawings.
The method for paving the vertical whole beam adopts the mode of singly paving an upper web plate, a lower web plate and a rim strip, and three components are jointly solidified and molded, and comprises the following steps:
(a) The upper die and the lower die are paved and pasted with flat plates, so that the appearance of the part is ensured;
(b) The upper C and the lower C are preformed through a thermal diaphragm forming die;
(c) The upper die and the lower die are combined through a locating pin;
(d) Removing the upper mould thermal diaphragm forming mould;
(e) A composite material stop block is arranged on the inner surface of the upper die;
(f) Filling 0-degree fiber in an R angle area where the upper die and the lower die are combined, paving two side edge strips, and forming by adopting an automatic tape paving machine;
(g) And installing composite silica gel soft cover plates on two sides of the upper die and the lower die for assembly and solidification.
Further, according to the invention, the problem of thickness deviation is solved by designing an independent composite material stop block aiming at the thickness deviation and the nondestructive control of an octagonal area, and the glass fiber reinforced plastic cover plate in the octagonal area is optimized. The method comprises the following steps:
(1) Designing a composite material stop block forming die: the composite material stop block forming die is manufactured by adopting Q235 numerical control machining, and according to analysis of a post Liang Lingjian three-coordinate detection result, the outward expansion deformation of the part is avoided in the process of Liang Lingjian after the subsequent forming, the rebound angle is increased, and the scaling factor is increased;
(2) The composite upper die still adopts the original left and right split die form, so that the die is convenient to be removed, the middle is matched with an inclined plane and made into a spigot form, a plurality of connecting band plates, positioning holes and threaded holes are added in the length direction, pre-buried metal blocks are positioned according to laser when a composite upper die stop block is paved, and after solidification is finished, the positions of the connecting band plates are subjected to numerical control brushing/milling, and the threaded holes are manufactured;
(3) Positioning the composite material stop block: the two ends of the die are positioned by using precision holes, the positioning holes are oblong holes, and the corresponding lower die metal tool is provided with positioning holes;
(4) The middle of the composite material stop block is opened at the protruding part of the product, the opening is opened to be single-side 5mm, and silica gel is placed at the opening part when the product is solidified, so that partial under-pressure of the product is prevented;
(5) Lossless control of octagon areas: the octagonal area is changed into the glass fiber reinforced plastic cover plate with the thickness of 0.3mm, and the glass fiber reinforced plastic cover plate is polished into a slope at the front edge of the glass fiber reinforced plastic cover plate, so that the quality influence on the product caused by overlarge step difference in the curing process of the product is avoided.
The damage to the octagonal area, fiber wrinkling, yellowing, swelling and resin enrichment of the R angle are effectively solved, and the product quality is excellent.
Further, as the vertical whole beam is mainly constructed by bearing the aircraft wallboard, the precision requirements of the carbon fiber laying position and angle are very high, and the vertical whole beam also adopts the following technical process:
checking thickness of the composite part: at least 5 measuring points are arranged in the same thickness area, the 5 measuring points all need to meet the thickness tolerance requirement, and the measuring data keep two decimal places; the ply transition region does not require measurement of part thickness, for an assembled thickness t tolerance of + -8%
Tolerance of 10% for thickness of non-critical structural areas without mating relationship; the tolerance of the thickness of the R angle area of the composite material part is +/-10%, or the tolerance of the R angle size is measured, wherein the tolerance is +/-0.25 t, and t is the corner/R angle theoretical thickness;
machining surface profile is not more than 0.2mm, damage to the basic layering is forbidden during machining, and the part profile is 0.75mm;
the surface of the composite material part should be smooth and flat, unidirectional tape and fabric fibers are clearly visible, the surface fibers are uniformly covered by resin, and no obvious resin accumulation is allowed.
After the new product trial production of the vertical whole beam paving method is finished, the detection department detects the size, thickness, profile, tyre pasting degree and the like, the detection result is qualified, and the surface appearance quality is smooth; detecting the internal quality of the product by an ultrasonic flaw detector, wherein the detection result is qualified; the qualification rate of small-batch trial production is excellent.
According to the method for paving the vertical whole beam, disclosed by the invention, the upper web plate and the edge strips of the vertical whole beam are respectively paved by using the forming die and the composite material cover plate, and the structural design of the composite material cover plate and the silica gel soft die is effectively controlled aiming at thickness deviation and damage of an octagonal region; when the forming die is paved, the laser positioning instrument is used, so that the operation of workers is simplified, and the probability of human defects is reduced.
According to the method for paving the vertical whole beam, disclosed by the invention, the carbon fiber unidirectional tape is paved on the vertical whole beam by utilizing the paving die and the composite cover plate, so that the appearance quality, the profile contour degree and the technical level of the cured product are effectively ensured to reach the domestic leading level; the vertical-tail integral beam adopts a mode of co-curing after being singly paved and pasted, and the positioning is assisted by positioning pins at two ends and laser projection in the folding process, so that the position degree is ensured, and the process technology also reaches the domestic leading level; the carbon fiber unidirectional tape layering adopts optical instrument to assist, ensures the accuracy of layering position and angle.
Main technical performance index
| Main technique Performance index | The invention is that | Domestic XXX Co | Foreign XXX public Sauce |
| Layering mould | Adopting a forming die, paving the composite material cover plate with a paving die and paving the composite material cover plate with a paving thickness High accuracy and convenient paving. | Carbon is produced by only one up-down molding mode Fiber layering and curing to make the R cutin appear in the product The amount and thickness dimensions are subject to defects. | Paving mould Is a forming die. |
| Measurement aspect | Matching a laser positioning instrument with a three-coordinate detecting machine The use saves the turnover time and reduces the cost. | The three-coordinate measuring machine has higher cost. | Three-dimensional measurement Measuring machine, cost Higher. |
According to the method for paving the vertical whole beam, disclosed by the invention, the upper web plate and the edge strips of the vertical whole beam are respectively paved by using the forming die and the composite material cover plate, and the structural design of the composite material cover plate and the silica gel soft die is effectively controlled aiming at thickness deviation and damage of an octagonal region; when the forming die is paved, the laser positioning instrument is used, so that the operation of workers is simplified, and the probability of human defects is reduced.
The above-described embodiments are illustrative of the present invention and are not intended to be limiting, and it is to be understood that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the spirit and scope of the present invention as defined by the appended claims and their equivalents.
Claims (1)
1. The method for paving the vertical whole beam adopts the mode of singly paving an upper web plate, a lower web plate and a rim strip, and three components are jointly solidified and molded, and comprises the following steps:
(a) The upper die and the lower die are paved and pasted with flat plates, so that the appearance of the part is ensured;
(b) The upper die is preformed by a thermal diaphragm forming die, and the lower die is preformed by a thermal diaphragm forming die of a lower die forming tool;
(c) Combining the upper die and the lower die;
(d) Removing the upper mould thermal diaphragm forming mould;
(e) A composite material stop block is arranged on the inner surface of the upper die;
(f) Filling 0-degree fiber in an R angle area where the upper die and the lower die are combined, paving two side edge strips, and forming by adopting an automatic tape paving machine;
(g) Mounting composite silica gel soft cover plates on two sides of the upper die and the lower die, assembling and solidifying;
the method aims at the nondestructive control of thickness deviation and an octagonal region, solves the problem of thickness deviation by designing an independent composite stop block, optimizes a glass fiber reinforced plastic cover plate of the octagonal region, and further comprises the following steps:
(1) Designing a composite material stop block forming die: the composite material stop block forming die is manufactured by adopting Q235 numerical control machining, and according to analysis of a post Liang Lingjian three-coordinate detection result, the outward expansion deformation of the part is avoided in the process of Liang Lingjian after the subsequent forming, the corresponding rebound angle is increased, and the scaling factor is increased;
(2) The composite upper die still adopts the original left and right split die form, so that the die is convenient to be removed, the middle is matched with an inclined plane and made into a spigot form, a plurality of connecting band plates, positioning holes and threaded holes are added in the length direction, pre-buried metal blocks are positioned according to laser when a composite upper die stop block is paved, and after solidification is finished, the positions of the connecting band plates are subjected to numerical control brushing/milling, and the threaded holes are manufactured;
(3) Positioning the composite material stop block: the two ends of the die are positioned by using 2-phi 12H7 precision holes, the positioning holes are oblong holes, and the corresponding lower die metal tool is provided with positioning holes;
(4) The middle of the composite material stop block is opened at the protruding part of the product, the opening is opened to be single-side 5mm, and silica gel is placed at the opening part when the product is solidified, so that partial under-pressure of the product is prevented;
(5) Lossless control of octagon areas: the octagonal area is changed into a 0.3mm glass fiber reinforced plastic cover plate, and the glass fiber reinforced plastic cover plate is ground into a slope at the front edge of the glass fiber reinforced plastic cover plate, so that the quality influence on the product caused by overlarge step difference in the curing process of the product is avoided;
because the vertical whole beam is mainly constructed by bearing the aircraft wallboard, the precision requirement of the carbon fiber laying position and angle is quite high, and the following measures are adopted for the vertical whole beam:
checking thickness of the composite part: at least 5 measuring points are arranged in the same thickness area, the 5 measuring points all need to meet the thickness tolerance requirement, and the measuring data keep two decimal places; the layering transition area does not require measurement of part thickness, and the tolerance of thickness t for assembly relation is + -8%;
tolerance of 10% for thickness of non-critical structural areas without mating relationship; the tolerance of the thickness of the R angle area of the composite material part is +/-10%, or the tolerance of the R angle size is measured, wherein the tolerance is +/-0.25 t, and t is the corner/R angle theoretical thickness;
machining surface profile is not more than 0.2mm, damage to the basic layering is forbidden during machining, and the part profile is 0.75mm; the surface of the composite material part should be smooth and flat, unidirectional tape and fabric fibers are clearly visible, the surface fibers are uniformly covered by resin, and no obvious resin accumulation is allowed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210780708.8A CN115107299B (en) | 2022-07-05 | 2022-07-05 | Vertical-tail integral beam paving method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210780708.8A CN115107299B (en) | 2022-07-05 | 2022-07-05 | Vertical-tail integral beam paving method |
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| CN115107299B true CN115107299B (en) | 2024-02-09 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5981023A (en) * | 1995-06-21 | 1999-11-09 | Japan Aircraft Development Corporation | Fiber-reinforced composite structural element and method of manufacturing the same |
| CN104669637A (en) * | 2013-12-02 | 2015-06-03 | 昌河飞机工业（集团）有限责任公司 | Laying moulding method for cylindrical composite part |
| CN105082565A (en) * | 2015-09-15 | 2015-11-25 | 沈阳飞机工业（集团）有限公司 | Automatic lay-up forming method of I-shaped beam made from composite materials |
| CN111391361A (en) * | 2020-03-30 | 2020-07-10 | 江西昌兴航空装备股份有限公司 | C-shaped frame paving method |
| WO2022107109A1 (en) * | 2020-11-23 | 2022-05-27 | Leonardo S.P.A. | Method and device for manufacturing a structural element in composite material with a z-shaped profile |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8632653B2 (en) * | 2005-05-03 | 2014-01-21 | The Boeing Company | Method of manufacturing curved composite structural elements |
| GB201218720D0 (en) * | 2012-10-18 | 2012-12-05 | Airbus Operations Ltd | Fibre orientation optimisation |
| US10960612B2 (en) * | 2015-07-08 | 2021-03-30 | Mitsubishi Chemical Corporation | Method for manufacturing fiber-reinforced composite material and fiber-reinforced composite material |
-
2022
- 2022-07-05 CN CN202210780708.8A patent/CN115107299B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5981023A (en) * | 1995-06-21 | 1999-11-09 | Japan Aircraft Development Corporation | Fiber-reinforced composite structural element and method of manufacturing the same |
| CN104669637A (en) * | 2013-12-02 | 2015-06-03 | 昌河飞机工业（集团）有限责任公司 | Laying moulding method for cylindrical composite part |
| CN105082565A (en) * | 2015-09-15 | 2015-11-25 | 沈阳飞机工业（集团）有限公司 | Automatic lay-up forming method of I-shaped beam made from composite materials |
| CN111391361A (en) * | 2020-03-30 | 2020-07-10 | 江西昌兴航空装备股份有限公司 | C-shaped frame paving method |
| WO2022107109A1 (en) * | 2020-11-23 | 2022-05-27 | Leonardo S.P.A. | Method and device for manufacturing a structural element in composite material with a z-shaped profile |
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