CN103407175B - A kind of integral forming method of fiber-reinforced resin matrix compound material wing box - Google Patents
A kind of integral forming method of fiber-reinforced resin matrix compound material wing box Download PDFInfo
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- CN103407175B CN103407175B CN201310325658.5A CN201310325658A CN103407175B CN 103407175 B CN103407175 B CN 103407175B CN 201310325658 A CN201310325658 A CN 201310325658A CN 103407175 B CN103407175 B CN 103407175B
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Abstract
An integral forming method for fiber-reinforced resin matrix compound material wing box, it has eight large steps: the structural design scheme one, determining fiber-reinforced resin matrix compound material wing box; Two, according to the structural design scheme determination mould program of fiber-reinforced resin matrix compound material wing box; Three, water-soluble core is prepared; Four, the perform manufacturing of fiber-reinforced resin matrix compound material wing box is prepared; Five, the perform manufacturing of fiber-reinforced resin matrix compound material wing box is put into mould and located matched moulds; Six, vacuumize, resin by injection elevated cure; Seven, the fiber-reinforced resin matrix compound material wing box with water-soluble core is taken out in die sinking; Eight, after being dissolved by water-soluble core from the inner chamber of fiber-reinforced resin matrix compound material wing box with water, fiber-reinforced resin matrix compound material wing box is finally obtained.The present invention is applicable to the global formation of the fiber-reinforced resin matrix compound material wing box with complicated inner cavity structure, and with low cost.
Description
Technical field
The invention provides a kind of integral forming method of fiber-reinforced resin matrix compound material wing box, belong to manufacture technology of composite material field.
Background technology
Wing box is the main load-carrying construction of aircraft, carries to take off, cruise and various load that in landing mission, wing and fuselage transmit.Traditional aircraft wing box is assembled by many metal parts, and thus construction weight is comparatively large, is unfavorable for the loss of weight of aircraft.Comparatively speaking, composite specific strength is high, specific stiffness large, and has designability, and be thus widely applied in aeronautic structure in recent years, as the central wing box made of composite materials of Air Passenger A380, more equal aluminium alloy structure compares nearly 1.5 tons of loss of weight.Composites forming technique then can reduce Standard weight further, is one of inexorable trend of the large-scale component loss of weight designs such as following wing box.Resin transfer molding technique (RTM) cost is low, Forming Quality is higher, the industrial global formation needs that can meet the large-scale components such as composite wing box.But composite wing box is inner usually containing many reinforced structures, cavity shape is complicated, traditional RTM method generally adopts metallic core, be difficult to the demoulding, and some composite wing box structural design scheme is due to cannot the demoulding and cannot realizing in manufacture process, and then have influence on the application of some advanced design schemes, therefore need to make improvement to it.
Summary of the invention
The object of the present invention is to provide a kind of integral forming method of fiber-reinforced resin matrix compound material wing box, to solve the technical problem of the demoulding difficulty when preparation of traditional RTM method has a fiber-reinforced resin matrix compound material wing box of complicated inner cavity structure.
The technical solution adopted in the present invention is as follows:
The integral forming method of a kind of fiber-reinforced resin matrix compound material wing of the present invention box, its step is as follows:
Step one, determine the structural design scheme of fiber-reinforced resin matrix compound material wing box.
Step 2, structural design scheme determination mould program according to fiber-reinforced resin matrix compound material wing box, comprise the mould preparing water-soluble core and the mould preparing fiber-reinforced resin matrix compound material wing box.
Step 3, prepare water-soluble core.
Step 4, according to design laying scheme paving cover fiber cloth, the setting agent of employing between layers of fiber cloth is shaped, and prepares the perform manufacturing of fiber-reinforced resin matrix compound material wing box.
Step 5, the perform manufacturing of the fiber-reinforced resin matrix compound material wing box prepared is put into mould, then locate matched moulds.
Step 6, to vacuumize, when vacuum reaches requirement-0.1, start the gap of perform manufacturing resin by injection fiberfill fibers in mould being strengthened polymer matrix composites wing box, after treating the gap of the perform manufacturing of the full fiber-reinforced resin matrix compound material wing box of resin filling, carry out elevated cure according to the curing process code of resin.
After step 7, solidification, by mold cools down to room temperature, open mould afterwards, take out and have cured shaping fiber-reinforced resin matrix compound material wing box, still with water-soluble core in the inner chamber of now fiber-reinforced resin matrix compound material wing box.
Step 8, with water, water-soluble core is dissolved from the inner chamber of fiber-reinforced resin matrix compound material wing box after, finally obtain fiber-reinforced resin matrix compound material wing box.
Wherein, " structural design scheme " described in step one needs to design according to technical indicator, the structure of fiber-reinforced resin matrix compound material wing box is made up of one or more cavity, and each cavity can be designed to prismatic or variable cross-section as required, the shape of cross section of each cavity can be the closed outline shape of trapezoidal, parallelogram, triangle, change radian, generally speaking the shape of each cavity can be arbitrary, and fiber-reinforced resin matrix compound material wing box local has or without strengthening rib strip and ribs.
Wherein, " water-soluble core " described in step 2 is made up of the water-soluble material of one, this material is Powdered, be poured into after adding mixing in dies cavity, the water-soluble core the same with mold shape can be obtained after being dried by water, water-soluble core has stable physical property and chemical property under room temperature and hot environment, when preparing fiber-reinforced resin matrix compound material wing box, under the hot environment of resin curing process, water-soluble core can keep designing external form, core can not decompose or damage, after resin solidification, after being cooled to room temperature, water-soluble core can by water-soluble solution.
Wherein, the laying scheme of " the laying scheme of design " described in step 4 normally balance and symmetry, the index that the concrete laying number of plies, laying angle and laying ratio will realize as required designs; " setting agent " described in step 4 is a kind of macromolecular material, need the compatibility had with the resin for the preparation of fiber-reinforced resin matrix compound material wing box, can styling be played by applying a small amount of setting agent between scrim cloth, making the perform manufacturing of fiber-reinforced resin matrix compound material wing box have certain globality.In the one that the fiber of " fiber cloth " described in step 4 can be in carbon fiber, glass fibre, Kevlar fiber, boron fibre and string;
Wherein, refer to the regulation to resin related process parameters in whole solidification process in " the curing process code " described in step 6, the resin of often kind of model is all to there being the curing process code matched with it.Can be the one in epoxy resin, polyimides, thermoplastic polyurethane, polyamide, polyphenylene sulfide, PAEK and polyvinyl alcohol at " resin " described in step 6.For RTM integral forming technique, in mould, the Stress control of resin by injection is at more than 0.5MPa.
The integral forming method of a kind of fiber-reinforced resin matrix compound material wing of the present invention box, its beneficial effect is the global formation of the fiber-reinforced resin matrix compound material wing box being applicable to having complicated inner cavity structure, and with low cost.
Accompanying drawing explanation
Fig. 1 is the FB(flow block) of the method for the invention.
Fig. 2 is the geometric configuration schematic diagram of composite wing box.
Fig. 3 prepares the mould and core that composite wing box uses.
Fig. 4 is the mould preparing water-soluble core.
In Fig. 2: 1. left C-shaped beam, 2. go up covering, 3. right C-shaped beam, 4. descends covering, 5. inner rectangular box beam, 6. trigonum
In Fig. 3: 7. patrix, 8. left C-shaped core, 9. counterdie, 10. right C-shaped core, 11. sealing strips, 12. central water-soluble cores, 13. left end caps, 14. right end caps.
In Fig. 4: 15. rear end caps, 16. central rigid skeletons, 17. drive end bearing brackets, 18. epipleurals, 19. left plates, 20. lower side panels, 21. right plates.
Detailed description of the invention
Below in conjunction with accompanying drawing and embodiment, the present invention is made further instructions.
Flow chart of the present invention as shown in Figure 1, first the structural design scheme of fiber-reinforced resin matrix compound material wing box is determined, then according to the structural design scheme determination mould program of fiber-reinforced resin matrix compound material wing box, ready mould is utilized to prepare water-soluble core, on this basis, prepare the perform manufacturing of fiber-reinforced resin matrix compound material wing box, the perform manufacturing of the fiber-reinforced resin matrix compound material wing box prepared is put into mould and located matched moulds, vacuumize afterwards, note resin and elevated cure, after to be solidified, the fiber-reinforced resin matrix compound material wing box with water-soluble core is taken out in die sinking, after finally water-soluble core being dissolved from the inner chamber of fiber-reinforced resin matrix compound material wing box with water, finally obtain fiber-reinforced resin matrix compound material wing box.Specific embodiment of the invention step is as follows:
Step one, determine the structural design scheme of fiber-reinforced resin matrix compound material wing box.
Wherein, " structural design scheme " described in step one needs to design according to technical indicator, the structure of fiber-reinforced resin matrix compound material wing box is made up of one or more cavity, and each cavity can be designed to prismatic or variable cross-section as required, the shape of cross section of each cavity can be trapezoidal, parallelogram, triangle, become the closed outline shape of radian, generally speaking the shape of each cavity can be arbitrary, fiber-reinforced resin matrix compound material wing box local has or without strengthening rib strip and ribs, in the present embodiment, selected fiber-reinforced resin matrix compound material wing box design as shown in Figure 2, it is the uiform section structure of single cavity, cavity geometry is rectangle, fiber-reinforced resin matrix compound material wing box is by left C-shaped beam 1, upper covering 2, right C-shaped beam 3, lower covering 4, inner rectangular box beam 5 and trigonum 6 form.
Step 2, design determination mould program according to fiber-reinforced resin matrix compound material wing box, comprise the mould preparing fiber-reinforced resin matrix compound material wing box and the mould preparing water-soluble core.
Wherein, " water-soluble core " described in step 2 is made up of the water-soluble material of one, this material is Powdered, be poured into after adding mixing in dies cavity, the water-soluble core the same with mold shape can be obtained after being dried by water, water-soluble core has stable physical property and chemical property under room temperature and hot environment, when preparing fiber-reinforced resin matrix compound material wing box, under the hot environment of resin curing process, water-soluble core can keep designing external form, core can not decompose or damage, after resin solidification, after being cooled to room temperature, water-soluble core can by water-soluble solution, " preparing the mould of fiber-reinforced resin matrix compound material wing box " described in step 2 as shown in Figure 3, by patrix 7, left C-shaped core 8, counterdie 9, right C-shaped core 10, sealing strip 11, central authorities' water-soluble core 12, left end cap 13 and right end cap 14 form, patrix 7 and upper covering are fitted, left C-shaped core 8 and left C-shaped beam 1 are fitted, counterdie 9 and lower covering 4 are fitted, right C-shaped core 10 and right C-type beam 3 are fitted, central authorities' water-soluble core 12 is fitted with inner rectangular box beam 5 inner surface, patrix 7 and counterdie 9 can by left C-shaped cores 8, right C-shaped core 10, left end cap 13 and right end cap 14 are located, central water-soluble core 12 can be located by left end cap 13 and right end cap 14, sealing strip 11 is made up of silica gel material, there is sealing and elasticity relatively preferably, whole set of die is sealed, " preparing the mould of water-soluble core " described in step 2 as shown in Figure 4, by rear end cap 15, central rigid skeleton 16, drive end bearing bracket 17, epipleural 18, left plate 19, lower side panel 20 and right plate 21, wherein epipleural 18, left plate 19, lower side panel 20 and right plate 21 assemble up formed rectangular enclosure can be used to prepare central water-soluble core 12, central rigid skeleton 16 plays booster action to central water-soluble core 12, prevent by the conquassation of central water-soluble core 12 in matched moulds process, central rigid skeleton 16 is located by rear end cap 15 and drive end bearing bracket 17.
Step 3, prepare water-soluble core.
Wherein, after " water-soluble core " described in step 4 completes core processing according to the moulding process of water-soluble core; be coated with last layer nano material diaphragm on its surface and carry out sealing pores; and stick one deck poly tetrafluoroethylene; ensure whose surfaces fineness, prevent resin from infiltrating water-soluble core simultaneously.
Step 4, according to design laying scheme paving cover fiber cloth, the setting agent of employing between layers of fiber cloth is shaped, and prepares the perform manufacturing of fiber-reinforced resin matrix compound material wing box.
Wherein, the laying scheme of " the laying scheme of design " described in step 4 normally balance and symmetry, the index that the concrete laying number of plies, laying angle and laying ratio will realize as required designs; The fiber of " fiber cloth " described in step 4 can be carbon fiber, glass fibre, Kevlar fiber, boron fibre or string; " setting agent " described in step one is a kind of macromolecular material, need the compatibility had with the resin for the preparation of fiber-reinforced resin matrix compound material wing box, can styling be played by applying a small amount of setting agent between scrim cloth, making the perform manufacturing of fiber-reinforced resin matrix compound material wing box have certain globality; Because fiber-reinforced resin matrix compound material wing box is made up of left C-shaped beam 1, upper covering 2, right C-shaped beam 3, lower covering 4, inner rectangular box beam 5 and trigonum 6, when preparing the perform manufacturing of the fiber-reinforced resin matrix compound material wing box needs first prepare respectively left C-type beam 1, on covering 2, right C-type beam 3, lower covering 4, inner rectangular box beam 5 and trigonum 6 perform manufacturing, they assemble again afterwards, finally obtain the perform manufacturing of fiber-reinforced resin matrix compound material wing box.
Step 5, the perform manufacturing of the fiber-reinforced resin matrix compound material wing box prepared is put into mould, then locate matched moulds.
Step 6, to vacuumize, when vacuum reaches requirement-0.1, start the gap of perform manufacturing resin by injection fiberfill fibers in mould being strengthened polymer matrix composites wing box, after treating the gap of the perform manufacturing of the full fiber-reinforced resin matrix compound material wing box of resin filling, carry out elevated cure according to the curing process code of resin.
Wherein, " resin " described in step 6 can be epoxy resin, polyimides, thermoplastic polyurethane, polyamide, polyphenylene sulfide, PAEK or polyvinyl alcohol; Refer to the regulation to resin related process parameters in whole solidification process in " the curing process code " described in step 6, the resin of often kind of model is all to there being the curing process code matched with it.For RTM integral forming technique, in mould, the Stress control of resin by injection is at more than 0.5MPa.
After step 7, solidification, by mold cools down to room temperature, open mould afterwards, take out and have cured shaping fiber-reinforced resin matrix compound material wing box, still with central water-soluble core 12 in the inner chamber of now fiber-reinforced resin matrix compound material wing box.
Step 8, with water, central water-soluble core 12 is dissolved from the inner chamber of fiber-reinforced resin matrix compound material wing box after, finally obtain fiber-reinforced resin matrix compound material wing box.
Claims (1)
1. the integral forming method of a fiber-reinforced resin matrix compound material wing box, it is characterized in that: the structural design scheme first determining fiber-reinforced resin matrix compound material wing box, then according to the structural design scheme determination mould program of fiber-reinforced resin matrix compound material wing box, ready mould is utilized to prepare water-soluble core, prepare the perform manufacturing of fiber-reinforced resin matrix compound material wing box, the perform manufacturing of the fiber-reinforced resin matrix compound material wing box prepared is put into mould and located matched moulds, vacuumize afterwards, note resin and elevated cure, after to be solidified, the fiber-reinforced resin matrix compound material wing box with water-soluble core is taken out in die sinking, after finally water-soluble core being dissolved from the inner chamber of fiber-reinforced resin matrix compound material wing box with water, finally obtain fiber-reinforced resin matrix compound material wing box, concrete implementation step is as follows:
Step one, determine the structural design scheme of fiber-reinforced resin matrix compound material wing box:
Wherein, structural design scheme described in step one needs to design according to technical indicator, the structure of fiber-reinforced resin matrix compound material wing box is made up of one or more cavity, and each cavity is designed to prismatic or variable cross-section as required, the shape of cross section of each cavity is trapezoidal, parallelogram, triangle or the closed outline shape becoming radian, the shape of each cavity is arbitrary, and fiber-reinforced resin matrix compound material wing box local has or without strengthening rib strip and ribs; The fiber-reinforced resin matrix compound material wing box chosen is the uiform section structure of single cavity, and cavity geometry is rectangle, and fiber-reinforced resin matrix compound material wing box is made up of left C-shaped beam, upper covering, right C-shaped beam, lower covering, inner rectangular box beam and trigonum;
Step 2, design determination mould program according to fiber-reinforced resin matrix compound material wing box, prepare the mould of fiber-reinforced resin matrix compound material wing box and prepare the mould of water-soluble core:
Wherein, water-soluble core described in step 2 is made up of the water-soluble material of one, this material is Powdered, be poured into after adding mixing in dies cavity, the water-soluble core the same with mold shape can be obtained after being dried by water, water-soluble core has stable physical property and chemical property under room temperature and hot environment, when preparing fiber-reinforced resin matrix compound material wing box, under the hot environment of resin curing process, water-soluble core can keep designing external form, core can not decompose or damage, after resin solidification, after being cooled to room temperature, water-soluble core can by water-soluble solution, the mould preparing fiber-reinforced resin matrix compound material wing box described in step 2 is by patrix, left C-shaped core, counterdie, right C-shaped core, sealing strip, central authorities' water-soluble core, left end cap and right end cap composition, patrix and upper covering are fitted, left-handed form core and left C-shaped beam are fitted, counterdie and lower covering are fitted, right C-shaped core and right C-type beam are fitted, central authorities' water-soluble core and inner rectangular box beam inner surface are fitted, upper die and lower die can by left C-shaped core, right C-shaped core, left end cap and right end cap location, central water-soluble core can be located by left end cap and right end cap, sealing strip is made up of silica gel material, there is sealing and elasticity relatively preferably, whole set of die is sealed, the mould preparing water-soluble core described in step 2 is by rear end cap, central rigid skeleton, drive end bearing bracket, epipleural, left plate, lower side panel and right plate, wherein epipleural, left plate, lower side panel and right plate assemble up formation rectangular enclosure, be used for preparing central water-soluble core, central rigid skeleton plays booster action to central water-soluble core, prevent by central water-soluble core conquassation in matched moulds process, central rigid skeleton is by rear end cap and drive end bearing bracket location,
Step 3, prepare water-soluble core:
Wherein, after the water-soluble core described in step 4 completes core processing according to the moulding process of water-soluble core, be coated with last layer nano material diaphragm on its surface and carry out sealing pores, and stick one deck poly tetrafluoroethylene, ensure whose surfaces fineness, prevent resin from infiltrating water-soluble core simultaneously;
Step 4, according to design laying scheme paving cover fiber cloth, the setting agent of employing between layers of fiber cloth is shaped, and prepares the perform manufacturing of fiber-reinforced resin matrix compound material wing box:
Wherein, the laying scheme of the design described in step 4 is the laying scheme of balance and symmetry, and the index that the concrete laying number of plies, laying angle and laying ratio will realize as required designs; The fiber of the fiber cloth described in step 4 is carbon fiber, glass fibre, Kevlar fiber, boron fibre or string; Setting agent described in step one is a kind of macromolecular material, need the compatibility had with the resin for the preparation of fiber-reinforced resin matrix compound material wing box, playing styling by applying a small amount of setting agent between scrim cloth, making the perform manufacturing of fiber-reinforced resin matrix compound material wing box have certain globality; Because fiber-reinforced resin matrix compound material wing box is made up of left C-shaped beam, upper covering, right C-shaped beam, lower covering, inner rectangular box beam and trigonum, when preparing the perform manufacturing of the fiber-reinforced resin matrix compound material wing box needs first prepare respectively left C-type beam, on covering, right C-type beam, lower covering, inner rectangular box beam and trigonum perform manufacturing, they assemble again afterwards, finally obtain the perform manufacturing of fiber-reinforced resin matrix compound material wing box;
Step 5, the perform manufacturing of the fiber-reinforced resin matrix compound material wing box prepared is put into mould, then locates matched moulds:
Step 6, to vacuumize, when vacuum reaches requirement-0.1, start the gap of perform manufacturing resin by injection fiberfill fibers in mould being strengthened polymer matrix composites wing box, after treating the gap of the perform manufacturing of the full fiber-reinforced resin matrix compound material wing box of resin filling, carry out elevated cure according to the curing process code of resin;
Wherein, the resin described in step 6 is epoxy resin, polyimides, thermoplastic polyurethane, polyamide, polyphenylene sulfide, PAEK or polyvinyl alcohol; Refer to the regulation to resin related process parameters in whole solidification process in the curing process code described in step 6, the resin of often kind of model is all to there being the curing process code matched with it; For RTM integral forming technique, in mould, the Stress control of resin by injection is at more than 0.5MPa;
After step 7, solidification, by mold cools down to room temperature, open mould afterwards, take out and have cured shaping fiber-reinforced resin matrix compound material wing box, still with central water-soluble core in the inner chamber of now fiber-reinforced resin matrix compound material wing box;
Step 8, with water, central water-soluble core is dissolved from the inner chamber of fiber-reinforced resin matrix compound material wing box after, finally obtain fiber-reinforced resin matrix compound material wing box.
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