CN109228394A - A kind of quick molding method of composite material fuselage reinforcing rib - Google Patents
A kind of quick molding method of composite material fuselage reinforcing rib Download PDFInfo
- Publication number
- CN109228394A CN109228394A CN201810978281.6A CN201810978281A CN109228394A CN 109228394 A CN109228394 A CN 109228394A CN 201810978281 A CN201810978281 A CN 201810978281A CN 109228394 A CN109228394 A CN 109228394A
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- CN
- China
- Prior art keywords
- reinforcing rib
- composite material
- degree
- laying
- material fuselage
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
-
- 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
- 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
- B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Textile Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Road Paving Structures (AREA)
Abstract
The invention belongs to polymer matrix composites field shaping techniques, are related to a kind of quick molding method of composite material fuselage reinforcing rib.The present invention is during the paving of composite material reinforcing rib, the web of 0 degree of laying carries out automatic fiber placement in template, then 0 degree of preform of automatic fiber placement is transferred on forming frock, improve paving efficiency, it is effectively shortened the paving period of 0 degree of laying, the splicing seams of 0 degree of laying of the latter and the splicing seams of previous 0 degree of laying are staggered, and ensure that the surface quality of composite material fuselage reinforcing rib；In composite material fuselage reinforcing rib forming process, soft cover board is eliminated, ensure that the thickness and surface quality of composite material fuselage reinforcing rib.The forming method of composite material fuselage reinforcing rib proposed by the present invention, ensure that the Forming Quality of composite material stopping-off piece, simplifies moulding process, shortens the manufacturing cycle, reduces manufacturing cost.
Description
Technical field
The invention belongs to polymer matrix composites field shaping technique, it is related to a kind of the quick of composite material fuselage reinforcing rib
Forming method.
Background technique
Composite material is led due to its high specific strength, high ratio modulus, designability and a series of features such as antifatigue in aviation
Domain is used widely.Time load-carrying member is expanded to from non-bearing component, and expands to primary load bearing component from secondary load-carrying member.It is multiple
Condensation material fuselage reinforcing rib (including bulkhead and cornual plate) is primary load bearing component, its main feature is that 0 degree of laying direction of component is circumference side
To not being conventional fixed-direction, the thickness uniformity, surface quality and contour tolerance of this feature to composite material reinforcing rib
Propose new challenge.The conventional shaping method of composite material fuselage reinforcing rib is: the manufacture of reinforcing rib forming frock, reinforcing rib work
Skill bogusware paving solidification, the correction of the flank shape of technique bogusware, soft cover board paving solidification and the formal part paving solidification of reinforcing rib.Conventional shaping method
The thickness and surface quality of the composite material reinforcing rib of manufacture are difficult to meet design requirement, and complex process, manufacturing cycle it is long,
Manufacturing cost is high.
The purpose of the present invention is to propose to a kind of forming methods of composite material fuselage reinforcing rib, guarantee composite material reinforcing rib
Forming Quality (especially part thickness and surface quality), while simplifying moulding process, shortening and the manufacturing cycle and reduce manufacture
Cost.
The technical solution of the invention is as follows:
(1) according to the manufacturing technology index Design of composite material fuselage reinforcing rib and reinforcing rib forming frock is manufactured；
(2) prepare prepreg automatic blanking file according to the manufacturing technology index of composite material fuselage reinforcing rib and laser is thrown
Shadow file, the edge strip of composite material fuselage reinforcing rib and the non-zero degree laying of web and 0 degree of laying of edge strip are automatic using prepreg
Blanking, and manual paving is carried out on forming frock under laser projection auxiliary；
The web of (3) 0 degree of layings uses the prepreg of automatic fiber placement technique, carries out in template by automatic fiber placement file certainly
Dynamic piddler, 0 degree of laying preform that automatic fiber placement is formed is transferred on forming frock, the wherein spelling of 0 degree of laying of the latter
The splicing seams of seam and previous 0 degree of laying must be staggered；
(4) step 2 and 3, vacuum of 1~3 layer of every paving pumping are repeated, until all layings complete paving；Then into
Row encapsulation, solidification and following process and detection.
The section of composite material fuselage reinforcing rib is Z-shaped, L shape or J-shaped.
The splicing seams of 0 degree of laying of the latter and the splicing seams of previous 0 degree of laying be staggered at a distance from for automatic paving
The half of the prepreg width of silk technique.
The present invention has the advantage that and beneficial effect
The present invention greatly simplifies the forming method of composite material fuselage reinforcing rib, is effectively guaranteed composite material and adds
The Forming Quality of strengthening tendons, simplifies moulding process, by the reinforcing rib forming frock manufacture in conventional shaping method, reinforcing rib technique
The processes such as bogusware paving solidification, the correction of the flank shape of technique bogusware, soft cover board paving solidification and the formal part paving solidification of reinforcing rib are reduced to add
The manufacture of strengthening tendons forming frock and the formal part paving solidification of reinforcing rib, entire manufacturing cycle and workload greatly reduce；In composite wood
During the paving for expecting reinforcing rib, the web of 0 degree of laying carries out automatic fiber placement in template, then pre- by 0 degree of automatic fiber placement
Formed body is transferred on forming frock, improves paving efficiency, is effectively shortened the paving period of 0 degree of laying, and 0 degree of the latter
The splicing seams of laying and the splicing seams of previous 0 degree of laying are staggered, and ensure that the surface quality of composite material fuselage reinforcing rib；?
In composite material fuselage reinforcing rib forming process, soft cover board is eliminated, ensure that the thickness and table of composite material fuselage reinforcing rib
Face quality.The forming method of composite material fuselage reinforcing rib proposed by the present invention ensure that the molding matter of composite material stopping-off piece
Amount, simplifies moulding process, shortens the manufacturing cycle, reduces manufacturing cost.
Detailed description of the invention
Fig. 1 is the forming method schematic diagram of conventional composites materials fuselage reinforcing rib；
Fig. 2 is the forming method schematic diagram of composite material fuselage reinforcing rib proposed by the present invention；
Fig. 3 is the Z-shaped structural schematic diagram of composite material fuselage reinforcing rib；Wherein, Fig. 3 a zero degree direction schematic diagram, Fig. 3 b abdomen
Plate and edge strip position view；
Fig. 4 is composite material fuselage reinforcing rib L-shaped structure schematic diagram；Wherein, Fig. 4 a zero degree direction schematic diagram, Fig. 4 b abdomen
Plate and edge strip position view；
Fig. 5 is the forming frock structural schematic diagram of composite material fuselage reinforcing rib.
Specific embodiment
(1) according to manufacturing technology index (shape requirement, internal soundness and the matching requirements of composite material fuselage reinforcing rib
Deng), design (material, selection tool structure form and determining manufacturing tolerance of selection tooling etc.) simultaneously manufactures reinforcing rib molding work
Dress；
(2) edge strip of non-zero degree laying and 0 degree of laying requires (laying according to the manufacturing technology of composite material fuselage reinforcing rib
The repetition arrangement of angle tolerance, opposite joint processing mode and same laying angle), with composite plys software (as: CATIA
Composites Design module, FiberSIM) generate prepreg automatic blanking file and laser projection file；0 degree of laying
Web requires to prepare automatic fiber placement file according to the manufacturing technology of composite material fuselage reinforcing rib, wherein the latter 0 degree of laying
Splicing seams and the splicing seams of previous 0 degree of laying must be staggered, and must not be overlapped, it is proposed that the automatic fiber placement technique prepreg that is staggered is wide
The half of degree；
(3) prepreg automatic blanking file is imported into prepreg automatic blanking machine (such as: GEBER cutter, the blanking of love section
Machine), laser projection file is imported into laser-projector (such as: Virtek laser-projector, LAP projector)；Non-zero degree laying and 0
The edge strip for spending laying carries out prepreg blanking by automatic blanking file, and carries out on reinforcing rib forming frock according to laser projection
Prepreg craft paving；Automatic fiber placement file is imported into automatic fiber placement machine, the web that automatic paving goes out 0 degree of laying in template is pre-
Then the web preform of 0 degree of laying of automatic fiber placement is transferred on forming frock by formed body.
(4) step 2 and 3, vacuum of 1~3 layer of every paving pumping are repeated, until all layings complete paving；
(5) it is packaged and is solidified by technological specification；
(6) to after solidification composite material fuselage reinforcing rib demoulding, machining, internal soundness detection, Thickness sensitivity and
The follow-up works such as surface quality detection.
Embodiment
The section of certain composite material fuselage reinforcing rib be it is Z-shaped, be made of edge strip 2 and web 3, length is about 5000mm, wide
Degree is about 150mm, and height is about 100mm, and thickness is about 2.24mm, is formed by 12 layers of one-way tape prepreg paving, wing flapping
Degree are as follows: [+45/+45/0/0/-45/90]S, 0 degree of direction 1 is along the circumferential direction, it is desirable that the thickness of Z-shaped composite material reinforcing rib is equal
Even, surface is smooth.
By implementation of the invention are as follows:
(1) according to the manufacturing technology index of composite material fuselage reinforcing rib: mold degree, surface quality and part thickness requirement
It is higher, it is contemplated that the factors such as the uniformity in temperature field, the craftsmanship of paving and outer dimension, reinforcing rib forming frock 4 select Yin
Steel material designs two occupy-places 5 using tower structure on each forming frock.
(2) edge strip 2 of the non-zero degree laying and 0 degree of laying of composite material fuselage reinforcing rib is reinforced according to composite material fuselage
(laying angle tolerance is ± 3 degree, the width direction of one-way tape prepreg is docked and 0 degree of laying direction for the manufacturing technology requirement of muscle
Definition etc.), prepreg automatic blanking file and laser projection file are generated with composite plys software FiberSIM, according to can
The blanking width of prepreg is set to 140mm by manufacturing ability, the convenience actually manufactured, and the blanking of 0 degree of laying prepreg is wide
Degree by the width of edge strip 2 adds surplus blanking, with composite plys software FiberSIM generate prepreg automatic blanking file and
Laser projection file requires to prepare 0 degree of laying web 3 with CADFiber according to the manufacturing technology of composite material fuselage reinforcing rib
Automatic fiber placement file, wherein the splicing seams of the splicing seams of 0 degree of laying of the latter and previous 0 degree of laying are staggered about 3.2mm, must not
It is overlapped；
(3) it is pre- to import prepreg automatic blanking machine GERBER cutter for the prepreg automatic blanking file for generating step 2
Laser projection file is imported laser-projector Virtek by leaching material automatic blanking machine (U.S. Gerber Technology)
LaserEdge, non-zero degree laying (+45 degree, -45 degree and 90 degree of layings) and the edge strip 2 of 0 degree of laying are carried out by automatic blanking file
Prepreg blanking, and prepreg craft paving is carried out on reinforcing rib forming frock according to laser projection；By automatic fiber placement file
Import automatic fiber placement machine, automatic paving goes out 3 preform of web of 0 degree of laying in template, then by automatic fiber placement it is pre- at
Type body is transferred on forming frock；
(4) step 2 and 3, vacuum of 1~3 layer of every paving pumping are repeated, until all layings complete paving and transfer；
(5) the auxiliary material such as non-porous release film, airfelt and vacuum bag is put on fuselage reinforcing rib after evacuation respectively
Material, the auxiliary materials such as non-porous release film, airfelt and vacuum bag must not build bridge；
(6) to after solidification composite material fuselage reinforcing rib demoulding, machining, internal soundness detection, Thickness sensitivity and
The follow-up works such as surface quality detection.
Claims (3)
1. a kind of quick molding method of composite material fuselage reinforcing rib, characterized in that
(1) according to the manufacturing technology index Design of composite material fuselage reinforcing rib and reinforcing rib forming frock is manufactured；
(2) prepare prepreg automatic blanking file and laser projection text according to the manufacturing technology index of composite material fuselage reinforcing rib
Under part, the edge strip of composite material fuselage reinforcing rib and the non-zero degree laying of web and 0 degree of laying of edge strip use prepreg automatic
Material, and manual paving is carried out on forming frock under laser projection auxiliary；
The web of (3) 0 degree of layings uses the prepreg of automatic fiber placement technique, is spread automatically in template by automatic fiber placement file
0 degree of laying preform that automatic fiber placement is formed is transferred on forming frock, wherein the splicing seams of 0 degree of laying of the latter by silk
It must be staggered with the splicing seams of previous 0 degree of laying；
(4) step 2 and 3, vacuum of 1~3 layer of every paving pumping are repeated, until all layings complete paving；Then it is sealed
Dress, solidification and following process and detection.
2. a kind of forming method of composite material fuselage reinforcing rib according to claim 1, characterized in that composite machine
The section of body reinforcing rib is Z-shaped, L shape or J-shaped.
3. a kind of forming method of composite material fuselage reinforcing rib according to claim 1, characterized in that described is latter
The splicing seams of a 0 degree of laying and the splicing seams of previous 0 degree of laying be staggered at a distance from be automatic fiber placement technique prepreg width
Half.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810978281.6A CN109228394B (en) | 2018-08-24 | 2018-08-24 | Rapid forming method for composite material fuselage reinforcing rib |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810978281.6A CN109228394B (en) | 2018-08-24 | 2018-08-24 | Rapid forming method for composite material fuselage reinforcing rib |
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| Publication Number | Publication Date |
|---|---|
| CN109228394A true CN109228394A (en) | 2019-01-18 |
| CN109228394B CN109228394B (en) | 2020-12-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810978281.6A Active CN109228394B (en) | 2018-08-24 | 2018-08-24 | Rapid forming method for composite material fuselage reinforcing rib |
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| CN (1) | CN109228394B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110978561A (en) * | 2019-12-30 | 2020-04-10 | 中国航空制造技术研究院 | Preparation method of fiber preform of composite material cover body with full-layering structure |
| CN111361179A (en) * | 2020-03-30 | 2020-07-03 | 西安交通大学 | Thermoplastic composite material forming process suitable for complex large curvature |
| CN112810182A (en) * | 2020-12-29 | 2021-05-18 | 江苏新扬新材料股份有限公司 | Forming method of composite material cylindrical support |
| CN114646923A (en) * | 2022-01-04 | 2022-06-21 | 威海光威复合材料股份有限公司 | Radar part that inside and outside structure switches on |
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| CN104484516A (en) * | 2014-12-04 | 2015-04-01 | 江苏恒神纤维材料有限公司 | Method of laying prepreg by aid of trajectory planning software |
| CN105172161A (en) * | 2015-08-21 | 2015-12-23 | 航天材料及工艺研究所 | Automatic fiber placement forming method for grid skin structure with part concave structure |
| CN106239941A (en) * | 2016-08-29 | 2016-12-21 | 中国航空工业集团公司基础技术研究院 | The projection of a kind of material prepreg and laying method |
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2018
- 2018-08-24 CN CN201810978281.6A patent/CN109228394B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104484516A (en) * | 2014-12-04 | 2015-04-01 | 江苏恒神纤维材料有限公司 | Method of laying prepreg by aid of trajectory planning software |
| CN105172161A (en) * | 2015-08-21 | 2015-12-23 | 航天材料及工艺研究所 | Automatic fiber placement forming method for grid skin structure with part concave structure |
| CN106239941A (en) * | 2016-08-29 | 2016-12-21 | 中国航空工业集团公司基础技术研究院 | The projection of a kind of material prepreg and laying method |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110978561A (en) * | 2019-12-30 | 2020-04-10 | 中国航空制造技术研究院 | Preparation method of fiber preform of composite material cover body with full-layering structure |
| CN111361179A (en) * | 2020-03-30 | 2020-07-03 | 西安交通大学 | Thermoplastic composite material forming process suitable for complex large curvature |
| CN112810182A (en) * | 2020-12-29 | 2021-05-18 | 江苏新扬新材料股份有限公司 | Forming method of composite material cylindrical support |
| CN112810182B (en) * | 2020-12-29 | 2021-11-30 | 江苏新扬新材料股份有限公司 | Forming method of composite material cylindrical support |
| CN114646923A (en) * | 2022-01-04 | 2022-06-21 | 威海光威复合材料股份有限公司 | Radar part that inside and outside structure switches on |
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| Publication number | Publication date |
|---|---|
| CN109228394B (en) | 2020-12-29 |
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