CN103342167B - Method for making scaled composite material wing model - Google Patents
Method for making scaled composite material wing model Download PDFInfo
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- CN103342167B CN103342167B CN201310187392.2A CN201310187392A CN103342167B CN 103342167 B CN103342167 B CN 103342167B CN 201310187392 A CN201310187392 A CN 201310187392A CN 103342167 B CN103342167 B CN 103342167B
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Abstract
The invention relates to a method for making a scaled composite material wing model and belongs to the field of composite material structure and airplane wind tunnel aeroelastic test model making technologies. According to the method, according to the design size, the scaled coefficient and composite material performance parameters of an actual airplane, a mold similar to the geometric profile of the model is made, and appropriate material parameters and processing technology parameters are chosen; in the process of making the scaled composite material wing model of the airplane, a wing spar and a wing rib are made, then the wing spar and the wing rib are combined and connected to be a skeleton, the skeleton is connected with a metal root rib, and then after the skeleton is filled with foams, shape modification is performed; the mold is used for forming the skeleton filled with the foams after the shape modification, and an upper skin and a lower skin are formed. The method enables the scaled composite material wing model to obtain high rigidity and strength with light weight. Moreover, according to different requirements, anti-bending and torsion resistant rigidity of the scaled composite material wing model can be adjusted.
Description
Technical field
The invention belongs to the manufacturing technology field of composite structure and aircraft wind-tunnel aeroelastic effect test model, relate to a kind of manufacture method of wing composite material scale model, especially for the composite material scale model of wing aerodynamic elasticity wind tunnel test.
Background technology
In aircraft development process, aeroelasticity wind tunnel test must be carried out to the isostructural scale model of wing, with each major part of research aircraft, air dynamic behaviour as isostructural in wing, for the load of aircraft determine, strength check and flutter characteristic research provides important test figures.According to theory of similarity, excellent wing scale model needs to have similarity with former wing structure in geometric shape, Static stiffness feature, weight characteristics etc., so just can better meet the requirement of wing aerodynamic elasticity wind tunnel test, improve the reliability of test figures.The wing scale model that early stage aircraft wing aeroelasticity wind tunnel test many employings all-metal or full solid wood manufacture, this class model generally adopts numerical control machining mode to manufacture, be easy to obtain higher geometric shape precision, but because such scale model is entity structure, thus its elastic characteristic is completely different from the elastic characteristic of Practical Wings structure.At present, a large amount of employing carries out aeroelasticity wind tunnel experiment based on the wing scale model of metal framework structure.This class model is formed primarily of metallic framework, covering and filled and process, and wherein metallic framework is the skeleton structure that single-beam or many beams and floor are formed, and is the main load-carrying member of wing scale model, provides most bending resistance and the torsion stiffness of wing scale model; And covering and filled and process are only for the gentle transmission of power of pneumatic dimension shape, few to the stiffness contribution of wing scale model, thus cause that the structure efficiency of scale model is low, own wt is large, makes wing scale model be difficult to meet and the similarity relation of wing structure in weight characteristics.Simultaneously, metallic framework due to this type of wing scale model adopts bulk metallic materials numerical control machining to obtain, the impact of unrelieved stress in being processed, metallic framework distortion is larger, cause the scale model manufactured to be difficult to obtain higher geometric shape precision, affect wing aerodynamic elasticity wind tunnel test particularity.
Wing composite material scale model is a kind of novel wing scale model form, and it has the structural similitude feature of part in version with former wing structure, form primarily of covering, spar, rib, filled and process and interface toughening layer.The rib being wherein arranged on scale model root is for connecting scale model main body and wind tunnel wall or other supporting constructions; The component such as covering and spar is made by resin base fiber reinforced composite material, and the relative position of each component, bearer properties etc. have similarity with former wing structure; Filled and process is on the one hand used for evacuation of air, bonds together on the other hand with the covering of scale model, spar, rib, and when preventing wind tunnel test, structural instability phenomenon appears in wing scale model.Presence of an interface toughening layer on each bonding interface, to guarantee bonding reliability.Wing composite material scale model utilizes that composite material designability is good, specific modulus is high, the advantage of easy-formation, geometry topological characteristic and the Stiffness Distribution feature of the load-carrying construction such as former aircraft skin and skeleton is simulated in model structure upper part, greatly can not only improve the structure efficiency of scale model, effectively reduce the structural weight of scale model; And also there is similarity on dynamic changes process and rigidity assigned characteristics, make wing scale model and former wing structure be provided with higher similarity, be more conducive to the wind-tunnel investigation of aircraft wing.Due to the complex structure of wing composite material scale model, it manufactures the profile geometric accuracy that not only will ensure wing scale model, and will consider the particularity of wing scale model in elastic characteristic, mass distribution feature etc. under many circumstances.And traditional composite structure manufacture method, how based on by improving technological process and material behavior, improve the Rigidity and strength of structure as far as possible, this does not conform to the manufacturing objective of wing composite material scale model.Thus need a kind of manufacture method of wing composite material scale model, not only can ensure the profile geometric accuracy of wing scale model, but also the particularity of wing scale model in rigidity characteristic, qualitative character etc. can be ensured.
Summary of the invention
The technical barrier that the present invention will solve is the defect overcoming prior art, invent a kind of manufacture method of wing composite material scale model, particularly for a manufacture method for the wing scale model of aeroelasticity wind tunnel test, comprise scale model main body and the metal root for being connected wind tunnel wall and scale model main body.This model obtains larger Rigidity and strength with less weight, and according to different needs, can regulate bending resistance and the torsion stiffness of wing composite material scale model, bending resistance model being reached specify and torsion stiffness.
The technical solution used in the present invention is: a kind of manufacture method of wing composite material scale model of aircraft: according to the version of above-mentioned wing composite material scale model, it manufactures according to first manufacturing spar 1 and rib 2, then spar 1 and rib 2 are connected and become skeleton, skeleton is connected with metal root 3, and then filled and process 5 is installed on skeleton, then correction of the flank shape is carried out to filled and process, finally use the common shaping upper and lower covering 4,6 of skeleton containing foam after mould and correction of the flank shape, and upper and lower covering and the skeleton containing foam are connected in one simultaneously.Concrete manufacture method is as follows:
One, mould manufacturing method
(1) manufacture method of covering die: covering has upper and lower covering 4,6, to the manufacture that should have upper and lower covering die, material selection metal alloy, job operation is numerical control machining, and requirement is the requirement that mould inner surface shape face meets resin transfer molding (RTM) process; Mould processes the device of location skeleton, fluting or with locating piece, on mould, discrepancy cast gate is processed after upper and lower covering die mold closing, the selection of discrepancy gate location obtains after RTM-Worx software optimization runner, and the principle of optimization ensures that resin can be good at impregnation of fibers reinforcing material as far as possible;
(2) manufacture method of spar mold: the mould of spar adopts the metal alloy mould of numerical control machining or turn over the fiber reinforced plastic mold of system on formpiston basis, spar and end of rib multi-processing go out one section of locating piece, the groove processed with covering die cooperatively interacts for locating, and guarantees that skeleton and covering die keep position relationship accurately;
Two, the manufacture method of spar 1 and rib 2
The version of spar 1 is the beam with variable cross-section of free form surface, and beam section is rectangle, I-shape or C font; The manufacturing process of spar adopts resin transfer molding (RTM) process, first fortifying fibre is arranged in definite shape, then worked-out spar mold is put into, after spar mold is closed and locked, by pressure by die cavity airtight for resin injection, air is driven out of by resin while impregnating reinforcing fiber, after mould is full of resin, by room temperature or heating cure, curing reaction carries out completely, opens mould and takes out component; Rib 2 is equal thickness plate structure, and its manufacturing forming process is by metallic material numerical control machining or be processed into by wood materials, or is made up of resin base fiber reinforced composite material material, manufacture shaping after, use saw blade cutting to go out to meet the contours profiles of designing requirement;
Three, the manufacture method of metal root 3
Adopt numerical control machining, metal root localization method adopts finger setting, has the function that can be connected with other supporting constructions;
Four, framework location assembly method
The assembling of skeleton adopts manual wet therapy forming process and coordinates vacuum bag, heats or normal temperature cure;
Five, foam-filled adhering method
Foam-filled assembling adopts composite material wet method to connect, and smears unsaturated polyester resin putty and foam exit orifice is closed, skeleton is installed filled and process 5, then carries out correction of the flank shape to filled and process;
Six, interface toughness reinforcing raising Joint strenght method is increased
Bonding way is adopted to link together between spar 1, rib 2 and filled and process 5, all parts bonding interface applies unsaturated polyester resin, then uniform spreading spills the Chopped fiber of 3 ~ 8mm in the above, increases interface toughening layer to improve Joint strenght with this;
Seven, covering forming resin transfer moulding method
The manufacturing process of covering also adopts resin transfer molding technique, first in lower covering die, the fortifying fibre forming structure is arranged in definite shape on request, place the skeleton and foam core that have assembled, compacting compresses, then in upper covering die, fortifying fibre is laid by identical method, finally that mould is closed and locked, by pressure by resin injection closed mold, be full of after resin until mould, by room temperature or heating cure, curing reaction carries out completely, opens mould, carries out correction of the flank shape to the covering of forming; Also complete covering and the assembling between skeleton and foam core in the process simultaneously, be finally connected in one; This technique makes assembling between skeleton and covering more tight, connection better.
Resin transfer molding manufacture technics covering and spar resin used are epoxy resin or vinylite or unsaturated polyester resin; Fortifying fibre used is by one or both chopped mats made in glass fibre, carbon fiber, aramid fiber or the fabric with plane knitting structure; Filled and process is ester class or amine organic matter closed-cell foam, in the space that existence and covering, spar and rib surround.
The another kind of method manufacturing covering and spar adopts vacuum bag to assist according to demand, is enclosed between vacuum bag and mould by the fortifying fibre that laying is good, then vacuumizes formation negative pressure and impel resin-dipping reinforcing fiber materials.Vacuum-assisted can improve the flowing power of resin further, makes fiber content higher, and the dipping of resin to fiber is better.
Effect of the present invention and benefit are: this manufacture method can not only ensure the profile geometric accuracy of wing scale model, but also can ensure the particularity of wing scale model in rigidity characteristic, qualitative character etc.Wing composite material scale model and the former wing structure of this technology manufacture have higher similarity, are more conducive to the wind-tunnel investigation of aircraft wing.
Accompanying drawing explanation
Fig. 1 is the skeleton structure schematic diagram of certain machine wing composite material scale model, in figure: 1 is spar; 2 is ribs.
Fig. 2 is covering forming and model entirety assembling schematic diagram, in figure: 3 is metal roots; 4 is upper coverings; 5 is filled and process; 6 is lower coverings.
Detailed description of the invention
Below in conjunction with technical scheme and accompanying drawing, the specific embodiment of the invention is described in further detail.The present invention have employed fiber-reinforced resin matrix compound material on material, by adjusting type and the percentage composition of matrix resin and fortifying fibre, can obtain the composite material of the mechanical property met design requirement.So in the fabrication process, everyly relate to the shaping process of resin solidification, all will after curing molding, whether suitable by the resin fibre ratio of weight method preliminary test component, then by Performance Detection, determined by model experiment object.General survey component flexibility or model frequency, whether the performance of detection means reaches requirement.
This wing composite material scale model geometric shape be the geometry contracting of true wing than profile, at least comprise: upper and lower covering, one along exhibition to continuously spar, three along tangential installation and the rib crossing with spar, for connect wind tunnel wall and scale model main body metal root, for fill internal cavities filled and process and for strengthening the interface toughening layer be connected.Upper and lower covering and spar are made up of resin base fiber reinforced composite material, resin can be epoxy resin, vinylite or unsaturated polyester resin, and fortifying fibre can be by one or both chopped mats made in glass fibre, carbon fiber, aramid fiber or the fabric with plane knitting structure.The fortifying fibre type that each parts use, fortifying fibre lay direction, fortifying fibre and resin ratio and overlay thickness all can regulate on gross area or in local area.Covering comprise at least one deck have the first machine direction gross area laying and at least one deck there is the gross area laying of the second machine direction.Rib can be made up of metallic material or wood materials, also can be made up of resin base fiber reinforced composite material material.The rib sections being arranged on root in rib claims root, all adopts metal to make, and has the function that can be connected with other supporting constructions.Filled and process is ester class or amine organic matter closed-cell foam, is filled in space that covering, spar and rib surround.Adopt bonding way to link together between covering, spar, rib and filled and process, on all parts bonding interface, Presence of an interface toughening layer is to improve Joint strenght.
For the composite material scale model of certain machine wing aerodynamic elasticity wind tunnel test by reference to the accompanying drawings, the present invention is further illustrated.Fig. 1 is the skeleton structure schematic diagram of certain machine wing composite material scale model, wherein comprises many horizontal spars 1 and horizontal rib 2.Fig. 2 is covering forming and model entirety assembling schematic diagram, and the shaping and skeleton and the covering that wherein comprise covering 4 and lower covering 6 are assembled into one.Manufacturing process is divided into that spar 1 manufactures, rib 2 manufactures, and spar 1, rib 2 are assembled into skeleton, and metal root 3 is connected with skeleton, filled and process 5, and upper covering 4 manufactures with lower covering 6 and entirety is assembled.For relating to the shaping process of resin solidification, all need after component manufacture to carry out Performance Detection and error compensation, it is qualified to guarantee.
According to real aircraft design size, contract than coefficient and composite property parameter, manufacture the mould meeting model geometric appearance similar, select suitable material parameter and working process parameter.The material selection metal alloy of upper and lower covering die, job operation is numerical control machining, covering die processes registration device groove and cast gate of coming in and going out.The material selection metal alloy of spar mold, job operation is numerical control machining.Spar and end of rib multi-processing go out one section of locating piece, and the groove processed with covering die cooperatively interacts for locating.
Spar 1 cross section is C type, and material is carbon fiber and epoxy resin, and adopt the RTM forming process that metal positive and vacuum bag are assisted, ensure pressurization froth breaking and heating cure, temperature is 60 ~ 80 DEG C.Rib 2 is equal thickness plate structure, and material is wood materials, goes out required contours profiles with saw blade cutting.Root 3 material is metal alloy, adopts numerical control machining, and location adopts finger setting.
Under being assemblied in of skeleton, covering die carries out, during assembling, first on lower covering die, make auxiliary positioning covering, this covering is mainly placed in the junction of beam rib and covering, for spar, rib provide location.Adopt epoxy resin by spar, the bonding rear heating cure of rib, temperature is 60 ~ 80 DEG C.Filled and process between skeleton, bonds filled and process and skeleton with unsaturated polyester resin putty, heating cure, and temperature is 60 ~ 80 DEG C, correction of the flank shape after solidification.
The manufacture of upper covering 4 and lower covering 6 and the assembling of model entirety are carried out simultaneously, according to performance need, upper covering 4 and lower covering 6 are Varying-thickness covering, be fully ensure model geometric profile accurate time shaping, based on following covering die, fortifying fibre is laid above, then place and assemble and skeleton after correction of the flank shape and filled and process 5, compacting compresses, liner Chopped fiber between fortifying fibre and skeleton, for covering Varying-thickness region, ensures that top layer and bottom are whole fiber, transitional region is clipped in the middle, and forms surface smoothing transition.Then in upper covering die, fortifying fibre is laid by identical method, finally that mould is closed and locked, by pressure by upper and lower for resin injection covering closed mold, be full of after resin until mould, by room temperature or heating cure, curing reaction carries out completely, opens mould, correction of the flank shape is carried out to the covering of forming, completes the manufacture of wing scale model.
Wing composite material scale model of the present invention obtains larger Rigidity and strength with less weight, and can according to different needs, regulate bending resistance and the torsion stiffness of wing composite material scale model, make wing composite material scale model reach the bending resistance and torsion stiffness of specifying.
Claims (3)
1. the manufacture method of the composite material scale model of an aircraft wing, it is characterized in that, according to real aircraft design size, contract than coefficient and composite property parameter, manufacture the mould meeting model geometric appearance similar, select suitable material parameter and working process parameter; Manufacture in the composite material scale model of aircraft wing, according to first manufacturing spar (1) and rib (2), again spar (1) and rib (2) are connected and become skeleton, skeleton is connected with metal root (3), and then on skeleton after filled and process (5), carry out correction of the flank shape; Finally, use mould by the skeleton forming containing filled and process after correction of the flank shape, form upper and lower covering (4,6), and upper and lower covering (4,6) and the skeleton containing filled and process are connected in one; The concrete steps of molds, methods of making are as follows:
One, covering die manufacture method
(1) manufacture method of covering die: covering has upper and lower covering (4,6), to the manufacture that should have upper and lower covering die, material selection metal alloy, job operation is numerical control machining, and requirement is the requirement that mould inner surface shape face meets resin transfer molding (RTM) process; Mould processes the device of location skeleton, fluting or with locating piece, on mould, discrepancy cast gate is processed after upper and lower covering die mold closing, the selection of discrepancy gate location obtains after RTM-Worx software optimization runner, and the principle of optimization ensures that resin can be good at impregnation of fibers reinforcing material as far as possible;
(2) manufacture method of spar mold: the mould of spar adopts the metal alloy mould of numerical control machining or turn over the fiber reinforced plastic mold of system on formpiston basis, spar and end of rib multi-processing go out one section of locating piece, the groove processed with covering die cooperatively interacts for locating, and guarantees that skeleton and covering die keep position relationship accurately;
Two, spar and rib manufacture method
The version of spar (1) is the beam with variable cross-section of free form surface, and beam section is rectangle, I-shape or C font; The manufacturing process of spar adopts resin transfer molding (RTM) process, first fortifying fibre is arranged in definite shape, then worked-out spar mold is put into, after spar mold is closed and locked, by pressure by die cavity airtight for resin injection, air is driven out of by resin while impregnating reinforcing fiber, after mould is full of resin, by room temperature or heating cure, curing reaction carries out completely, opens mould and takes out component; Rib is equal thickness plate structure, and its manufacturing forming process is by metallic material numerical control machining or be processed into by wood materials, or is made up of resin base fiber reinforced composite material material, manufacture shaping after, use saw blade cutting to go out to meet the contours profiles of designing requirement;
Three, metal root (3) manufacture method
Metal root (3) manufacture method adopts numerical control machining, and root localization method adopts finger setting, can be connected with other supporting constructions;
Four, framework location assembly method
The assembling of skeleton adopts manual wet therapy forming process, and coordinates vacuum bag, heats or normal temperature cure; Spar, rib form being assemblied on covering former of skeleton part and carry out, and before assembling, are fixed on covering shaping dies, carry out correction of the flank shape according to skeleton profile to foam, adopt the Minute pores on filler enclosing foam surface by metal root location; First on covering former, groove is used for the location of floor stringer, the auxiliary positioning covering made between beam rib and covering former is spar, rib provides location, adopt epoxy resin that beam, rib is bonding and adopt connection gusset plate to reinforce in beam rib junction, heating cure after skeleton root bonded metal inserts;
Five, filled and process and adhering method
Filled and process assembling adopts composite material wet method to connect, and smears unsaturated polyester resin putty and foam exit orifice is closed, skeleton installs filled and process, then carries out correction of the flank shape to filled and process;
Six, interface toughness reinforcing raising Joint strenght method is increased
Adopt bonding way to link together between spar, rib and filled and process, all parts bonding interface applies unsaturated polyester resin, then uniform spreading spills the Chopped fiber of 3 ~ 8mm in the above, increases interface toughening layer to improve Joint strenght with this;
Seven, the forming process of upper and lower covering (4,6)
The manufacturing process of upper and lower covering adopts resin transfer molding technique, upper and lower covering comprise at least one deck have the first machine direction gross area laying and at least one deck there is the gross area laying of the second machine direction, formation fortifying fibre structure; First will be formed in lower covering die in fortifying fibre structure, place the skeleton and filled and process that have assembled, compacting compresses, and then in upper covering die, lays fortifying fibre by identical method, finally that mould is closed and locked, by pressure by resin injection closed mold, be full of after resin until mould, by room temperature or heating cure, curing reaction carries out completely, open mould, correction of the flank shape is carried out to the covering of forming; Complete covering and the assembling between skeleton and filled and process, be connected in one.
2. the manufacture method of the composite material scale model of aircraft wing according to claim 1, is characterized in that: manufacturing covering and spar resin used is epoxy resin or vinylite or unsaturated polyester resin; Fortifying fibre used is by one or both chopped mats made in glass fibre, carbon fiber, aramid fiber or the fabric with plane knitting structure; Filled and process is ester class or amine organic matter closed-cell foam, in the space that existence and covering, spar and rib surround.
3. the manufacture method of the composite material scale model of aircraft wing according to claim 1 and 2, it is characterized in that: the another kind of method manufacturing covering and spar adopts vacuum bag to assist according to demand, be enclosed between vacuum bag and mould by the fortifying fibre that laying is good, then vacuumize formation negative pressure and impel resin-dipping reinforcing fiber materials.
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