CN104275810A - Composite structural component fixture model and fixture forming die - Google Patents
Composite structural component fixture model and fixture forming die Download PDFInfo
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- CN104275810A CN104275810A CN201310293432.1A CN201310293432A CN104275810A CN 104275810 A CN104275810 A CN 104275810A CN 201310293432 A CN201310293432 A CN 201310293432A CN 104275810 A CN104275810 A CN 104275810A
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- frock
- model
- fixture
- composite
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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
- 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
- B29C33/3835—Designing moulds, e.g. using CAD-CAM
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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
- 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
- B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
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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
- B29C70/54—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
- 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
- B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
- B29C2033/385—Manufacturing moulds, e.g. shaping the mould surface by machining by laminating a plurality of layers
-
- 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
Abstract
The invention discloses a composite structural component fixture model and a fixture forming die. A main control section of the composite structural component fixture standard model is a section template processed by numerical control wire cutting, a profile part on a wood material serves as a laying surface which is structurally designed as a multi-layer system, a glass reinforced plastic laying layer with thickness of 2-3mm is adjacent to the wood material, an epoxy resin layer with thickness of 4-5mm is formed on glass reinforced plastic, a polyurethane steel grit layer with thickness of 2-4mm is formed on the epoxy resin layer, and a net-shaped cast metal base is adopted by the model. The composite structural component fixture forming die is provided with a welding framework base and a composite surface layer containing reinforced fibers, and additionally comprises clamping plates, a positioning device and a pressing device. According to the scheme, the product manufacturing precision is improved, a fixture can be copied and maintained, and a useful effect is achieved in production of a certain type unmanned aerial vehicle developed in China.
Description
Technical field
The present invention relates to a kind of composite material structural member frock.
Background technology
The composite material structural member of aircraft is adopted more and more due to the series of advantages such as have high specific strength, high specific stiffness, good fatigue resistance, corrosion resistance, lightweight, detectivity is low, stealth is good.Especially the application in light aerocraft, helicopter structure is more extensive.Such as, in some Flight Vehicle Structure, the proportion of composite material structural member accounts for more than 80%.
Composite element is compared with general metal material part, and its design and manufaction has uniqueness, is embodied in following four aspects:
(1) composite element also completes the manufacturing technical feature of material while forming parts, determine the integration that composite element must consider design, material, technique during fabrication simultaneously, three is inseparable, must consider as a whole in composite element manufacture process.
(2) composite is anisotropic material, and its designability feature makes it design on demand, thus the characteristic making component can be designed out metal structure not have.Therefore the ratio etc. shared by laying of resin content, overlay thickness, laying direction and all directions, all can have influence on the mechanical property of composite.The design of composite also relates to the optimization of laying ratio, laying direction and laying arrangement etc., makes it give full play to its anisotropic feature.
(3) composite element good integrity, compared with metal structure, composite element can global formation, add composite designability, therefore composite element design, manufacture opposing metallic material and want complicated, composite structure design be one with the famous work of labor-intensive, need to carry out definition in every possible way to each laying in structure.
(4) composite element workmanship and personnel, equipment, material, method, environment are closely bound up, (4) composite element workmanship and personnel, equipment, material, method, environment are closely bound up, controlled link is many, the small change of each link may affect product quality, be difficult to determine once there is product quality problem reason, often can only lean on micro-judgment.
In current aircraft industry, the aircraft of various advanced person be all be closely connected with the composite technology of advanced person together with, and the manufacture of composite element be unable to do without technological equipment (abbreviation frock), and the quality of its product ensures by frock.The frock of technique for aircraft composite component comprises the special jigs such as shaping (transition) mould, glue (riveting) welding fixture, assembly jig, numerical control trimming (boring).The current domestic main employing environment the same with airplane design designs the production technology equipment of composite element, countlessly for a long time to facts have proved, adopt that the most important condition of composite material structural member is design, technique, material three aspect closely cooperate and mutually promote.Wherein, for the manufacture of composite material structural member design of technological arrangement manufacture how will badly influence product quality.
Because multiple material component must complete the recombination process of material and the forming process of component by the frock of specialized designs manufacture simultaneously, almost no longer need after part solidified forming to do any processing, its internal structure, mechanical property just can reach designing requirement, surface quality, physical dimension should meet assembly coordination requirement simultaneously, do not allow to force assembling, thus the quality of molding composite material frock completes in frock the shaping that the profile of goods and internal soundness play the multiple material of decisive role, and various forming technology has respective requirement to fixture for forming.The basic demand of molding composite material component frock:
1) required precision of product design is met.Frock size is accurate, and frock material matches with the thermal coefficient of expansion of component as far as possible, little to ensure the deformation of products produced, good stability of the dimension.Frock smooth surface, smooth, closely knit, free from flaw, without pinprick, ensure product quality;
2) enough Rigidity and strengths to be had.The compound action of vibrations in deadweight, product weight, production process and external applied load can be born.For large product, except meeting except requirement of strength, rigidity requirement is also very important, to prevent frock profile benchmark to be out of shape, affects product quality and frock service life;
3) good heat conductivity and heat endurance.Frock will have enough heat resistances, prevents the distortion that is heating and curing, and ensures product quality.Frock heating is fast, can shorten frock and the cure cycle of part in autoclave, economize energy;
4) lightweight, material source is abundant.The design of frock and selection have enough Rigidity and strengths, also will consider its easy transportation simultaneously;
5) cost low, be easy to processing.The economic benefit of frock and the technical difficulty of processing are also the indispensable factors of Fixture Design;
6) safeguard and keep in repair easy.Extend the service life of frock, it is important means that frock can be keeped in repair.
In the multiple material production process of aircraft, frock technology to the shortening product release time, reduce multiple material production cost, to enhance productivity and forming accuracy has more and more important meaning.With the structural material aborning existing tentative application of multiple material as frock, but multiple material Fixture Design has himself difficult point:
1) the multiple material part of aircraft much adopts vacuum bag autoclave forming technology solidified forming under high-temperature pressurizing, and forming quality and the frock thermal coefficient of expansion of multiple material part are closely related, and 20 steel frock thermal coefficient of expansions are 8 times of multiple material part, and forming quality is poor; INVAR steel frock is mated substantially with Thermal expansion coefficient of composites, but due to the anisotropy of multiple material part, also cannot meet production requirement, ensure multiple material tool mold ensure to match with multiple material part all directions thermal coefficient of expansion become multiple material part produce in major issue.
2) the multiple material accessory size of aircraft is large, profile is complicated, in order to improve forming quality, first trial-production testpieces is carried out, according to the difference correction frock profile of testpieces and theoretical profile, so repeatedly, obtain preferably again material part forming quality, carrying out being that finding a kind of method fast and effectively becomes the urgent bottleneck problem solved with a large amount of man-hour and material consumption for cost in repetition test.
3) answer material fixture for forming constantly to change because answering temperature in section product forming process, due to the structure of frock itself, cause the temperature field of the multiple material template directly contacted with product also in continuous change, template each point temperature is different, multiple material part solidification is asynchronous, finally affect product quality, in traditional design, only rely on experience, cannot ensure frock evenly, heating, cooling rapidly.
The fixture for forming of the multiple material of hot setting in being shaped for autoclave, except meeting the basic demand of frock, air-tightness, the resistance to pressure of frock etc. are also design principal elements.The frock being applicable to the multiple material of warm working in autoclave at present mainly contains following several: the multiple material frock of aluminium frock, steel frock, INVAR steel frock, carbon fiber/epoxy resin:
1) aluminum frock: lightweight, processing technology is good, and manufacturing dimension precision is high, frock advantage of lower cost, and has good thermal conductivity when multiple material component forming, and frock programming rate is fast.But because the thermal coefficient of expansion of aluminium is relatively large, the multiple material accessory size poor stability be shaped with it.Moreover, for the larger frock of size, in its casting process, often occur that some are as the casting flaw such as sand holes, fine cracks, and then cause it in use can produce gas leak phenomenon, and autoclave molding composite material technique is a vacuum pressed system, require that frock must have good air-tightness, otherwise vacuum system is leaked, multiple material component inside quality can be caused to reduce, time serious, cause part rejection.
2) steel frock: good endurance, its weight is large, intensification performance is low, temperature distributing disproportionation is even, easily produces stress, can not for the production of high-precision multiple material products.Simultaneously because its density is large, thus frock is from great, uses carrying not too convenient, and frock profile difficulty of processing is corresponding comparatively large simultaneously, and the manufacturing cycle is longer.
Multiple material tool structure material is numerous, and its performance is each variant, as: serviceability temperature, thermal coefficient of expansion, intensity etc.Select, will select to follow following principle according to multiple section product material therefor kind, thermal coefficient of expansion, cure parameter etc. during material:
1) the carbon fiber frock material that material parts information model thermal coefficient of expansion matches answered by carbon fiber, and the heat distortion temperature of frock material must higher than multiple section product solidification temperature more than 20 DEG C;
2) precuring temperature of frock is little as far as possible, and serviceability temperature is high, to improve frock forming quality, reduces cost;
3) air-tightness meets production requirement, can repeatedly use;
4) frock material not only will have good rigidity but also will have suitable viscosity, good laying;
Tool mold is the basis of advanced multiple material molding component, and it plays the effect of transmitting temperature and pressure, location and guarantee appearance and size precision.In Fixture Design, need emphasis it is considered that tool structure material and Fixture Design scheme, multiple material tool mold as a special multiple material part, usually consider in design because have:
1) select low temperature moulding, the frock material of applied at elevated temperature, not only avoid or reduce to produce thermal deformation in solidification process, and frock manufacturing cost can be reduced;
2) can meet in multiple material solidified forming process the requirement of frock strength and stiffness;
3) rational tool structure ensures the multiple material part necessary condition of frock Accurate Shaping;
4) frock has service life long as far as possible;
The frock profile of multiple material is generally laminated plate structure, utilizes the designability feature of multiple material, mainly comprises selection, Lay up design, Rigidity and strength etc., design.Under the prerequisite that frock material is selected, according to behaviour in service and the requirement of the reality of frock, Lay up design is carried out to frock shape face, mainly comprises the following aspects;
1) suitable laying angle is selected;
2) suitable overlay thickness is selected;
3) rational stacking sequence is provided.
Traditional process is according to the complete wooden original mold of sample plate manufacture, then turns over according to original mold and makes pattern.The surface of shaping mould adopts the fiberglass laying that 5 ~ 8mm is thick, and base is welded frame, and its advantage is: Fixture Design manufacture is simple, with short production cycle, low cost of manufacture.Shortcoming is: the frock accuracy of manufacture is low, and in use procedure by temperature, effects of humidity change greatly, be easily out of shape, frock cannot copy and overhaul.Low for flying speed, shape requirement is not high, and output is few, adopts the aircraft of normal temperature cure composite material structural member, and choosing is feasible in this way.
In current domestic air mail industry, the design of mould have employed the method for Design of digital, and Fixture Design personnel apply CATIA three-dimensional software and carry out Design of digital to mould, and its concrete grammar is as follows:
The product parts digital-to-analogue that Fixture Design department provides according to product design department, extracts shaping curved surface, carries out hole repair, surface extending, according to the outline polygon of product digital-to-analogue boundary design mold; Curved surface is carried out equidistantly, create stretching entity according to mold outline polygon, then go to shear entity with shaping curved surface and equidistant surface, namely obtain the digital model of the mold of composite element mould;
Mold is chosen the datum plane of several establishment support, create gripper shoe sketch on this plane to stretch the plate entity that is supported, and make it to fit completely with the lower surface of mold with equidistant surface shear support plate, then louvre feature is created in the position skeletonizing that gripper shoe surface is suitable, although the whole support Design above-mentioned method for designing that well bamboo product is crisscross afterwards meets the digitized requirement of frock substantially, but there is certain deficiency, such as: the design of mould relies on the knowledge and experience that designer grasps, product model designed by the designer of different background is widely different, the standardization of product design and normative requirement can not be met,
Design cycle is long, and the most of the time is all expended in support and chassis design process, and the work that these two parts are just repeated, the creative work achievement of designer can not be embodied.
The support fixing for planform and underframe two parts, do not have too many creative but but occupy a large amount of design time of designer in design process, the design efficiency seriously constraining mould, the Operational preparation cycle extending product, the production cost that adds product; Objectively require to adopt new method for designing and design means to realize the rapid Design of composite element mould.
In recent years, along with applying of various high-performance composite materials, vacuum bag, autoclave is generally adopted to heat pressurization in production process, not only require that forming temperature is high, briquetting pressure large, and the time dependent process need of composite material structural member heating and cooling aborning is strictly controlled.Tradition is wooden or cannot meet technological requirement by the frock of the poor nonmetallic materials shaping methods manufacture of other heat conduction, not only shaping mould surface non-refractory, and due to thermal coefficient of expansion different, make to mould and easily to ftracture between layer and metal structure and come off.
Summary of the invention
The object of the invention is to propose a kind of composite material structural member frock.
For reaching this object, the present invention by the following technical solutions:
A kind of composite element frock model, it is characterized in that the major control tangent plane of model is the tangent plane model of Numerical Control Wire Cutting, middle edge spells timber, mould surface portion above timber is laying, ply angles is designed to multilayer system, adjacent with timber for being the fiberglass laying that 2-3mm is thick, fiberglass is the thick epoxy resin layer of 4-5mm, epoxy resin layer is the polyurethane steel layer of sand that 2-4mm is thick, adopts the netted base in cast metal.
Also comprise a kind of composite material structural member frock shaping mould, it is characterized in that adopting welded frame base and the composite surface layer containing fortifying fibre, add clamp, locator, compactor.
Further: polyurethane steel layer of sand is apply after steel sand and polyurethane stir to obtain, and the weight ratio of steel sand is 5-20%, and particle diameter is 10-20 micron.
Accompanying drawing illustrates:
Fig. 1 is the shaping mould of certain type unmanned plane wing:
Detailed description of the invention
Embodiment 1
This example is low for the composite traditional handicraft frock accuracy of manufacture, be subject to temperature, effects of humidity change large in use procedure, easy distortion, the shortcoming that frock cannot copy and overhaul is improved, this composite material structural member frock shaping mould 1 adopts welded frame base and the composite surface layer containing fortifying fibre, adds clamp 2, locator 3, compactor; A kind of composite element frock model, it is characterized in that the major control tangent plane of model is the tangent plane model of Numerical Control Wire Cutting, middle edge spells timber, mould surface portion above timber is laying, ply angles is designed to multilayer system, adjacent with timber for being the fiberglass laying that 2-3mm is thick, fiberglass is the thick epoxy resin layer of 4-5mm, epoxy resin layer is the polyurethane steel layer of sand that 2-4mm is thick, adopts the netted base 4 in cast metal.
Improve the integral rigidity of forming frock.
Embodiment 2
Polyurethane steel layer of sand is apply after steel sand and polyurethane stir to obtain, and the weight ratio of steel sand is 5-20%, and particle diameter is 10-20 micron.All the other are with embodiment 1.
Claims (3)
1. a composite element frock model, it is characterized in that the major control tangent plane of model is the tangent plane model of Numerical Control Wire Cutting, middle edge spells timber, mould surface portion above timber is laying, ply angles is designed to multilayer system, adjacent with timber for being the fiberglass laying that 2-3mm is thick, fiberglass is the thick epoxy resin layer of 4-5mm, epoxy resin layer is the polyurethane steel layer of sand that 2-4mm is thick, adopts the netted base in cast metal.
2. a composite material structural member frock shaping mould, is characterized in that adopting welded frame base and the composite surface layer containing fortifying fibre, adds clamp, locator, compactor.
3. model according to claim 1, is characterized in that: polyurethane steel layer of sand is apply after steel sand and polyurethane stir to obtain, and the weight ratio of steel sand is 5-20%, and particle diameter is 10-20 micron.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310293432.1A CN104275810A (en) | 2013-07-12 | 2013-07-12 | Composite structural component fixture model and fixture forming die |
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| CN201310293432.1A CN104275810A (en) | 2013-07-12 | 2013-07-12 | Composite structural component fixture model and fixture forming die |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104690981A (en) * | 2015-02-13 | 2015-06-10 | 哈尔滨新科锐工艺装备制造有限公司 | Composite material precision molding tool for airplane and precision molding manufacturing method |
| CN105467950A (en) * | 2015-10-12 | 2016-04-06 | 无锡清杨机械制造有限公司 | Design method of composite material shaping die |
| CN109176069A (en) * | 2018-10-10 | 2019-01-11 | 北京京科兴业科技发展有限公司 | A kind of model small lot processing tool and processing method |
| CN109583114A (en) * | 2018-12-07 | 2019-04-05 | 江西洪都航空工业集团有限责任公司 | A kind of fitting of aircraft complex type face and curing method |
| CN113011014A (en) * | 2021-03-03 | 2021-06-22 | 西北工业大学 | Composite material layering optimization method and system |
| CN113458260A (en) * | 2021-06-28 | 2021-10-01 | 成都飞机工业（集团）有限责任公司 | Accurate preforming method for large-curvature metal thick plate |
| RU2797954C1 (en) * | 2022-07-18 | 2023-06-13 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | Method for manufacturing aerodynamic controls for unmanned aerial vehicles |
-
2013
- 2013-07-12 CN CN201310293432.1A patent/CN104275810A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104690981A (en) * | 2015-02-13 | 2015-06-10 | 哈尔滨新科锐工艺装备制造有限公司 | Composite material precision molding tool for airplane and precision molding manufacturing method |
| CN105467950A (en) * | 2015-10-12 | 2016-04-06 | 无锡清杨机械制造有限公司 | Design method of composite material shaping die |
| CN109176069A (en) * | 2018-10-10 | 2019-01-11 | 北京京科兴业科技发展有限公司 | A kind of model small lot processing tool and processing method |
| CN109583114A (en) * | 2018-12-07 | 2019-04-05 | 江西洪都航空工业集团有限责任公司 | A kind of fitting of aircraft complex type face and curing method |
| CN113011014A (en) * | 2021-03-03 | 2021-06-22 | 西北工业大学 | Composite material layering optimization method and system |
| CN113011014B (en) * | 2021-03-03 | 2023-02-24 | 西北工业大学 | Composite material layering optimization method and system |
| CN113458260A (en) * | 2021-06-28 | 2021-10-01 | 成都飞机工业（集团）有限责任公司 | Accurate preforming method for large-curvature metal thick plate |
| CN113458260B (en) * | 2021-06-28 | 2022-10-25 | 成都飞机工业（集团）有限责任公司 | Accurate preforming method for large-curvature metal thick plate |
| RU2797954C1 (en) * | 2022-07-18 | 2023-06-13 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | Method for manufacturing aerodynamic controls for unmanned aerial vehicles |
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Application publication date: 20150114 |