CN109849351B - Composite material wing wall plate and metal wing rib sealing method based on co-bonding process - Google Patents
Composite material wing wall plate and metal wing rib sealing method based on co-bonding process Download PDFInfo
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- CN109849351B CN109849351B CN201811445382.3A CN201811445382A CN109849351B CN 109849351 B CN109849351 B CN 109849351B CN 201811445382 A CN201811445382 A CN 201811445382A CN 109849351 B CN109849351 B CN 109849351B
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- stringer
- stop block
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- wing
- sealing stop
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- 238000007789 sealing Methods 0.000 title claims abstract description 144
- 238000000034 method Methods 0.000 title claims abstract description 26
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 20
- 239000002184 metal Substances 0.000 title claims abstract description 20
- 239000002131 composite material Substances 0.000 title claims abstract description 10
- 239000003365 glass fiber Substances 0.000 claims abstract description 22
- 239000011347 resin Substances 0.000 claims abstract description 12
- 229920005989 resin Polymers 0.000 claims abstract description 12
- 239000003292 glue Substances 0.000 claims abstract description 11
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 6
- 239000000853 adhesive Substances 0.000 claims description 13
- 238000007598 dipping method Methods 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 3
- 230000001070 adhesive effect Effects 0.000 claims description 2
- 239000000565 sealant Substances 0.000 abstract description 8
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 230000000694 effects Effects 0.000 abstract description 6
- 238000012423 maintenance Methods 0.000 abstract description 2
- SPJMAPNWDLIVRR-UHFFFAOYSA-M sodium;3-chloro-2-phenylphenolate Chemical compound [Na+].[O-]C1=CC=CC(Cl)=C1C1=CC=CC=C1 SPJMAPNWDLIVRR-UHFFFAOYSA-M 0.000 abstract 1
- 230000000903 blocking effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000007731 hot pressing Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000011208 reinforced composite material Substances 0.000 description 1
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Abstract
The invention relates to the technical field of aircraft body manufacturing, and provides a method for sealing a composite material wing panel and a metal wing rib based on a co-bonding process, wherein a gap formed by a stringer flange strip of the wing panel and the metal wing rib is filled with glass fibers, and the glass fibers form a sealing stop block; the stringer flange strip and the sealing stop block are simultaneously in adhesive-sharing connection with the skin, the resin between the sealing stop block and the stringer flange strip is naturally filled in a flowing manner after being heated before being cured, and no gap is left after being cured; the stringer, the sealing stop block and the skin form an integrated structure; the sealing stop block and the matching surface of the metal wing rib are sealed by gluing. Compared with the prior art, the invention does not need to separately manufacture a conformal mold with the skin theoretical internal surface characteristic for the stop block, only keeps the maintenance of the glue stop mold, does not need to separately enter the autoclave for curing, and reduces the cost; sealant does not need to be smeared around the stop block, and only the glue is needed to be smeared at the matching surface of the stop block and the wing rib, so that the assembly procedures are reduced, the sealing effect is improved, the method is simple and practical, and the application prospect is wide.
Description
Technical Field
The invention relates to the technical field of aircraft body manufacturing, in particular to a method for sealing a composite material wing wallboard and a metal wing rib based on a co-bonding process.
Background
At present, the carbon fiber reinforced composite material has the properties of high specific strength, high specific stiffness, designability, fatigue resistance, corrosion resistance, less maintenance and the like, and is widely applied to the most advanced international large civil aircraft, the most typical application is a wing panel structure, and at present, the large civil aircraft generally adopts a double-beam multi-rib structure. Due to the partition requirement of the wing tank, part of the rib is used as a tank interface and needs to be sealed, as shown in fig. 1. In addition, because of the bearing and structural form of the wing rib, the aluminum alloy material is still mainly used at present.
The sealing problem needs to be solved between the longpurlin flanges of the wing panels, below the sealing ribs and above the skin. The existing machine type adopts a structural form of a glass fiber filling sealing stop block, the height of the sealing stop block is equal to that of a stringer flange strip, the width of the sealing stop block is slightly smaller than the distance between the stringer flange strips, and the structural form is shown in figure 2. The specific installation steps are that the periphery of the glass fiber block which is cured separately is coated with the sealant, and then the glass fiber block is plugged into a gap formed by the wall plate and the wing rib, so that the sealing effect is achieved.
The existing stringer and skin co-bonding technology is to bond a preformed stringer and a cured skin, and a stringer curing mold is provided with a flanging at a stringer flange to prevent resin from flowing out after temperature rise and ensure stringer curing quality, as shown in fig. 3.
As shown in fig. 2, the inner surface of the skin is shown as a plane and the actual inner surface is a hyperboloid, and the curvatures of the inner surfaces of the skin are different at each location where the sealing stop is placed. The prior art has the following defects: when the glass fiber stop block is manufactured, the glass fiber stop blocks on different positions of the skin are required to be separately manufactured into a conformal mold with the theoretical inner shape characteristic of the skin, generally an egg-box type mold, so that the cost is higher, and the independent curing is required, so that the production cost is increased; when the glass fiber stop block is assembled, the glass fiber stop block is respectively coated with sealant on four surfaces of a skin matching surface, the end surfaces of the two stringer flanges of the wallboard and the lower surface of the wing rib, so that the assembly time is prolonged, and the sealing difficulty is improved.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a method for sealing a composite material wing wallboard and a metal wing rib based on a co-cementing process, wherein a set of die is shared by the composite material wing wallboard and a stringer during the manufacturing of a sealing stop block by cementing, so that the use frequency of a hot-pressing tank is reduced, and the manufacturing cost of the sealing stop block is reduced; when the sealing stop block is assembled, glue is only required to be applied to the matching surfaces of the stop block and the wing ribs, so that the assembling time of the stop block is shortened, and the sealing effect is improved.
The invention relates to a method for sealing a composite material wing wallboard and a metal wing rib based on a co-bonding process, which comprises the following steps of:
filling a gap formed by a stringer of a wing panel and a metal wing sealing rib with glass fiber, wherein the glass fiber is presoaked and cured to form a sealing stop block;
the wing wallboard stringer and the sealing stop block are simultaneously in adhesive joint with the skin, and no gap exists between the sealing stop block and the wing wallboard stringer after curing; the wing wallboard stringer, the sealing stop block and the skin form an integrated structure;
the matching surface of the sealing stop block and the metal wing rib is coated with glue for sealing, and the sealing stop block is connected with the lower end of the metal wing sealing rib in a sealing mode.
Furthermore, when the stringer flange strips and the sealing check blocks of the wing wallboard are simultaneously connected with the skin in a co-adhesive mode, the stringer flange strips and the sealing check blocks of the wing wallboard are pre-impregnated in prepreg, the prepreg between the stringer flange strips and the sealing check blocks of the wing wallboard is filled in gaps (after resin is heated up, the prepreg naturally flows to fill the gaps and then is cured), the prepreg is resin, and the stringer flange strips and the sealing check blocks of the wing wallboard form an integrated structure after being cured.
Further, when the stringer edge strips of the wing wall boards, the sealing stop blocks and the skin are in co-adhesive connection, a co-adhesive mould is adopted; the co-cementing mould comprises a stringer part and a sealing stop block part; the stringer part is communicated with the adjacent part of the sealing stop block part, so that the prepreg of the stringer edge strip of the wing wallboard and the sealing stop block can be ensured to fill the gap between the stringer edge strip of the wing wallboard and the sealing stop block together.
The invention also provides a co-cementing mould, which is used for co-cementing connection between the stringer tape of the wing panel and the skin as well as between the sealing stop block and the skin; the co-cementing mould comprises a stringer part and a sealing stop block part;
the cross section of the stringer part is 2L-shaped corresponding to the wing panel stringer, and the L-shaped comprises a first part and a second part corresponding to the wing panel stringer edge strip; the second portion being slightly shorter than the wing panel stringer tape;
the sealing stop block part is of a flat plate structure;
the sealing stop block part and the second part are arranged in parallel and level, so that the sealing stop block is as high as the stringer tape of the wing panel;
a gap is reserved between the sealing stop block part and the second part.
Furthermore, the gap between the sealing stop block part and the second part is consistent with the precision requirement of the stringer web station line, and the gap is filled with a glue blocking strip during curing.
The invention also provides a method for carrying out co-adhesive connection by using the co-adhesive mould, which is characterized in that the stringer edge strip of the wing panel and the glass fiber with the size of the sealing stop block are simultaneously pre-impregnated, and the pre-impregnated material is resin;
simultaneously placing presoaked stringer strips of the wing panels and glass fibers on set positions of a skin;
the stringer part of the co-cementing mould is applied to the stringer of the wing panel, and the sealing stop block part is applied to the sealing stop block; wherein the second part of the stringer is compressed against the edge strip of the wing panel stringer; a gap is reserved between the second part of the stringer part and the sealing stop block part;
the wing wallboard stringer, the sealing stop block and the skin form an integrated structure after being heated and cured.
The invention has the beneficial effects that: compared with the prior art, the shape-following die with the theoretical internal shape surface characteristic of the skin does not need to be manufactured separately for the stop blocks at different positions of the skin, only the glue-blocking die needs to be maintained, and the hot pressing tank does not need to be independently filled for curing, so that the production cost is greatly reduced; sealant does not need to be smeared around the stop block, and only the glue is needed to be smeared at the matching surface of the stop block and the wing rib, so that the assembly procedures are reduced, the sealing effect is improved, the method is simple and practical, the sealing effect is good, and the application prospect is wide.
Drawings
Fig. 1 shows a sealing rib distribution schematic diagram of a civil aircraft.
Fig. 2 is a schematic view showing a sealing structure between the lower end of a sealing rib and a wall plate in the prior art.
FIG. 3 is a schematic view of a prior art stringer to skin bonding scheme.
Fig. 4 is a schematic view showing a sealing structure between the lower end of the sealing rib and the wall plate according to the embodiment of the present invention.
FIG. 5 is a schematic illustration of a stringer to skin bonding scheme as proposed in an embodiment of the present invention.
Wherein: 1-a sealing rib; 2-sealing the rib edges; 3-stringer tape; 4-four sides of sealant; 5-sealing stop blocks cured separately; 6-covering; 7-single-sided sealant; 8-sealing stop blocks of co-glued joint; 9-existing stringer co-cementing molds; 10-stringer (modified stringer co-cementing mold); 11-sealing the stop block part; 101-a first portion; 102-second part.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that technical features or combinations of technical features described in the following embodiments should not be considered as being isolated, and they may be combined with each other to achieve better technical effects. In the drawings of the embodiments described below, the same reference numerals appearing in the respective drawings denote the same features or components, and may be applied to different embodiments.
The invention aims to solve the problems of complicated working procedures and low efficiency caused by the fact that the sealing stop block needs to be manufactured independently and needs to be coated with glue at four sides during sealing in the prior art.
As shown in fig. 4 and 5, a method for sealing a composite wing panel and a metal rib based on a co-bonding process according to an embodiment of the present invention includes the following steps: filling a gap formed by a stringer of a wing panel and a metal wing rib with glass fiber, wherein the glass fiber is presoaked and cured to form a sealing stop block; the wing wallboard stringer and the sealing stop block are simultaneously connected with the skin in a co-adhesive manner, the sealing stop block and the wing wallboard stringer are connected by resin curing (formed between the sealing stop block and the stringer after glass fiber and the stringer are presoaked and cured), and no gap is formed in the middle; the wing wallboard stringer, the sealing stop block and the skin form an integrated structure; the matching surfaces of the sealing stop block and the metal wing rib are coated with glue (sealant) for sealing, so that the sealing stop block is connected with the lower end of the metal wing sealing rib in a sealing manner.
Preferably, when the stringer flange strips of the wing wall panels and the sealing check blocks are simultaneously connected with the skin in a co-gluing mode, the stringer flange strips of the wing wall panels and the sealing check blocks are pre-impregnated in prepreg, the prepreg between the stringer flange strips of the wing wall panels and the sealing check blocks is filled with the prepreg between the stringer flange strips of the wing wall panels and the sealing check blocks, the prepreg is resin, and the stringer flange strips of the wing wall panels and the sealing check blocks form an integrated structure after being cured.
When the stringer edge strips of the wing wall boards, the sealing stop blocks and the skin are in co-adhesive connection, a co-adhesive mould is adopted; the co-cementing mould comprises a stringer part and a sealing stop block part; the stringer part is communicated with the adjacent part of the sealing stop block part, so that the prepreg of the stringer edge strip of the wing wallboard and the sealing stop block can be ensured to fill the gap between the stringer edge strip of the wing wallboard and the sealing stop block together.
As shown in fig. 5, the co-cementing mould is used for co-cementing connection between the stringer tape of the wing panel and the sealing stop block and the skin at the same time; the co-cementing mould comprises a stringer part and a sealing stop block part; the cross section of the stringer part is 2L-shaped corresponding to the wing wallboard stringer, and the L-shaped comprises a first part corresponding to a wing wallboard web and a second part corresponding to a wing wallboard stringer edge strip; the second portion being slightly shorter than the wing panel stringer tape; the sealing stop block part is of a flat plate structure; the sealing stop block part and the second part are arranged in parallel and level, so that the sealing stop block is as high as the stringer tape of the wing panel; a gap is reserved between the sealing stop block part and the second part. The gap between the sealing stop block part and the second part is consistent with the station line precision requirement of the stringer web, and the gap is filled with a glue blocking strip during curing.
The co-cementing mould in the embodiment of the invention can be simply reformed by the conventional stringer co-cementing mould: when a traditional stringer co-cementing mould (as shown in figure 4) is improved, at the position where a sealing stop block needs to be arranged, flanging of the stringer mould is locally cancelled, so that resin in prepreg of a stringer can flow out, and a gap between the sealing stop block and a stringer flange strip is filled with the resin of the prepreg in the sealing stop block; in addition, a sealing stopper curing mold (sealing stopper portion) needs to be manufactured to play a role of maintaining the shape and stopping the glue.
The method for carrying out co-gluing connection by adopting the co-gluing mould comprises the following steps: simultaneously pre-dipping the stringer edge strip of the wing panel and the glass fiber with the size of the sealing stop block, wherein the pre-dipping material is resin; simultaneously placing presoaked stringer strips of the wing panels and glass fibers on set positions of a skin; the stringer part of the co-cementing mould is applied to the stringer of the wing panel, and the sealing stop block part is applied to the sealing stop block; wherein the second part of the stringer is pressed tightly against the stringer tape of the wing panel; a gap is reserved between the second part of the stringer part and the sealing stop block part; the wing wallboard stringer, the sealing stop block and the skin form an integrated structure after being heated and cured.
Compared with the prior art, the difference mainly lies in that:
the sealing stop blocks and the stringers are solidified on the skin together, and the traditional stop blocks are not manufactured independently and then are installed in a matching mode;
when sealing is carried out, sealant only needs to be coated on the matching surfaces of the stop block and the wing ribs, and other three surfaces do not need to be sealed.
While several embodiments of the present invention have been presented herein, it will be appreciated by those skilled in the art that changes may be made to the embodiments herein without departing from the spirit of the invention. The above examples are merely illustrative and should not be taken as limiting the scope of the invention.
Claims (4)
1. A method for sealing a composite material wing wall plate and a metal wing rib based on a co-bonding process is characterized by comprising the following steps:
filling a gap formed by a stringer of a wing panel and a metal wing sealing rib with glass fiber, wherein the glass fiber is presoaked and cured to form a sealing stop block;
the wing wallboard stringer and the sealing stop block are simultaneously in adhesive joint with the skin, and no gap exists between the sealing stop block and the wing wallboard stringer after curing; the wing wallboard stringer, the sealing stop block and the skin form an integrated structure; when the stringer flange strip of the wing panel and the sealing stop block are simultaneously connected with the skin in a co-adhesive manner, the stringer flange strip of the wing panel and the sealing stop block are pre-impregnated in prepreg, the prepreg of the stringer flange strip of the wing panel and the prepreg of the sealing stop block are jointly filled in a gap between the stringer flange strip of the wing panel and the sealing stop block, the prepreg is resin, and the stringer flange strip of the wing panel and the sealing stop block form an integrated structure after being cured;
the matching surfaces of the sealing stop block and the metal wing sealing rib are respectively coated with glue for sealing, so that the sealing stop block is connected with the lower end of the metal wing sealing rib in a sealing manner;
when the stringer edge strips of the wing wall boards, the sealing stop blocks and the skin are in co-adhesive connection, a co-adhesive mould is adopted; the co-cementing mould comprises a stringer part and a sealing stop block part; the stringer part is communicated with the adjacent part of the sealing stop block part, so that the prepreg of the stringer edge strip of the wing wallboard and the sealing stop block can be ensured to fill the gap between the stringer edge strip of the wing wallboard and the sealing stop block together.
2. A co-cementing mould for a method of sealing a composite wing panel to a metal rib according to claim 1, based on a co-cementing process, wherein the co-cementing mould is used for co-cementing connection between a wing panel stringer, a sealing stop and a skin at the same time; the co-cementing mould comprises a stringer part and a sealing stop block part;
the cross section of the stringer part is 2L-shaped corresponding to the wing panel stringer, and the L-shaped comprises a first part and a second part corresponding to the wing panel stringer edge strip; the second portion being slightly shorter than the wing panel stringer tape;
the sealing stop block part is of a flat plate structure;
the sealing stop block part and the second part are arranged in parallel and level, so that the sealing stop block is as high as the stringer tape of the wing panel;
a gap is reserved between the sealing stop block part and the second part.
3. A co-cementing mold according to claim 2, wherein the gap between said sealing stop portion and said second portion conforms to the stringer web station line accuracy requirements, and wherein upon curing the gap is filled with a dam bar.
4. A method of co-gluing joints using a co-gluing mould according to claim 2 or 3,
simultaneously pre-dipping the stringer edge strip of the wing panel and the glass fiber with the size of the sealing stop block, wherein the pre-dipping material is resin;
simultaneously placing presoaked stringer strips of the wing panels and glass fibers on set positions of a skin;
the stringer part of the co-cementing mould is applied to the stringer of the wing panel, and the sealing stop block part is applied to the sealing stop block; wherein the second part of the stringer is pressed tightly against the stringer tape of the wing panel; a gap is reserved between the second part of the stringer part and the sealing stop block part;
the wing wallboard stringer, the sealing stop block and the skin form an integrated structure after being heated and cured.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811445382.3A CN109849351B (en) | 2018-11-29 | 2018-11-29 | Composite material wing wall plate and metal wing rib sealing method based on co-bonding process |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811445382.3A CN109849351B (en) | 2018-11-29 | 2018-11-29 | Composite material wing wall plate and metal wing rib sealing method based on co-bonding process |
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| CN109849351B true CN109849351B (en) | 2021-11-23 |
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| CN111476786B (en) | 2020-04-22 | 2022-02-01 | 南京航空航天大学 | Automatic gluing and quality detection method for stringer based on measured data |
| CN118560734B (en) * | 2024-08-05 | 2024-12-06 | 中航(成都)无人机系统股份有限公司 | Unmanned aerial vehicle wing integral oil tank structure and manufacturing method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102006045635A1 (en) * | 2006-09-27 | 2008-04-03 | Airbus Deutschland Gmbh | Pre-hardened stringer tying method for e.g. spacecraft, involves tying stringers at structural component in pressure loaded manner, using foils, sealing unit and strips, and arranging stringers parallel to each other on component |
| CN103341987A (en) * | 2013-06-17 | 2013-10-09 | 沈阳飞机工业（集团）有限公司 | Co-curing process for omega-stringer vertical and horizontal reinforcement composite integral wallboard |
| CN105034405A (en) * | 2015-08-31 | 2015-11-11 | 江苏恒神股份有限公司 | One-time solidifying and forming device and method for T-shaped stiffened wall plate |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10146898A (en) * | 1996-11-15 | 1998-06-02 | Honda Motor Co Ltd | Molding method of fiber reinforced composite material |
| US7993479B2 (en) * | 2006-09-27 | 2011-08-09 | Airbus Deutschland Gmbh | Method for joining precured or cured stringers to at least one structural component of an aircraft or spacecraft |
| ES2383424B1 (en) * | 2009-09-29 | 2013-05-03 | Airbus Operations S.L. | AIRCRAFT NOTEBOOK AND METHOD OF OBTAINING THE SAME |
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2018
- 2018-11-29 CN CN201811445382.3A patent/CN109849351B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102006045635A1 (en) * | 2006-09-27 | 2008-04-03 | Airbus Deutschland Gmbh | Pre-hardened stringer tying method for e.g. spacecraft, involves tying stringers at structural component in pressure loaded manner, using foils, sealing unit and strips, and arranging stringers parallel to each other on component |
| CN103341987A (en) * | 2013-06-17 | 2013-10-09 | 沈阳飞机工业（集团）有限公司 | Co-curing process for omega-stringer vertical and horizontal reinforcement composite integral wallboard |
| CN105034405A (en) * | 2015-08-31 | 2015-11-11 | 江苏恒神股份有限公司 | One-time solidifying and forming device and method for T-shaped stiffened wall plate |
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