CN103192527A - Secondary bonding forming method of structural part with curvature - Google Patents
Secondary bonding forming method of structural part with curvature Download PDFInfo
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- CN103192527A CN103192527A CN2013101460690A CN201310146069A CN103192527A CN 103192527 A CN103192527 A CN 103192527A CN 2013101460690 A CN2013101460690 A CN 2013101460690A CN 201310146069 A CN201310146069 A CN 201310146069A CN 103192527 A CN103192527 A CN 103192527A
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Abstract
The invention belongs to the technical field of structural bonded assembly forming, and relates to a secondary bonding forming method of a structural part with curvature. According to the invention, various assemblies are connected without adopting a riveting mode, and various bonded assemblies are integrally formed after being subjected to secondary curing and bonded through the curing of an expanded adhesive film J-99B; and the problem that a butt seam is easy to recess in the pressurizing and curing process of a product is solved through a butt seam unilateral beehive balance discharge process method, so that the product weight is reduced, and the product stability is enhanced.
Description
Technical field
The invention belongs to aircaft configuration bonded part forming technique, relate to a kind of structural member second bonding forming method that has curvature.
Background technology
The structural adhesive bonding tail boom is three deep camber, variable curvature structures that the wallboard butt joint forms.Manufacturing process is that exterior skin, honeycomb sandwich structure, glued membrane in the metal are sealed on the mould with vacuum bag, place autoclave, under vacuum (or antivacuum) state, through heating up → pressurization → insulation (middle temperature or high temperature) → step-down and stress-relief process, make it become needed shape and quality state.
At present, having the process that the structural member of curvature connects on the aircraft has:
1. riveted joint connection method
Each spare part of the deep camber of difference moulding earlier structure glue fitting is riveted connection after pre-assembled is carried out in assembly tooling, each spare part is connected by the riveted joint mode.
This method is mechanical connection, and rivet produces certain destruction to the structural adhesive bonding product, has reduced product service life.
2. second bonding method
Owing to product structure and loss of weight reason, can not connect by riveted joint, adopt the second bonding mode to connect, general second bonding abutment joint bonding mode is: honeycomb (no surplus)+expansion glued membrane J-94+ honeycomb (no surplus), both sides, abutment joint position do not emit the adjustment of honeycomb surplus during each spare part moulding.
This method causes constant product quality poor, and abutment joint is prone to depression defect after the formed product.
Summary of the invention
The purpose of this invention is to provide the structural member second bonding forming method that has curvature that a kind of constant product quality is good, abutment joint is not prone to depression.
Technical solution of the present invention is:
1) respectively glueds joint the spare part moulding
Be that the inside and outside covering of aluminium carries out surface treatment to material: after chromic acid anodizing is handled, internally, exterior skin spray J-100 primer;
Glued joint assembling: 1. first lay exterior skin on the metal forming frock, 2. put hot setting structural film adhesive J-99B on the exterior skin upper berth, 3. lay honeycomb on hot setting structural film adhesive J-99B, honeycomb is after exterior skin abutment joint edge all emits the 1mm-3mm surplus, paste one deck expansion glued membrane J-94,4. lay hot setting structural film adhesive J-99B on honeycomb is 5. at hot setting structural film adhesive J-99B lay inside panel;
Working environment is: operate temperature in air conditioning room: 18-24 ℃, humidity: 40-65%, clean dustless;
Paste vacuum bag: on the metal forming frock, paste vacuum bag at glueing joint spare part;
Solidify: curing oven solidifies, and is warming up to 180 ℃ ± 5 ℃, constant temperature 90 ± 10 minutes, and 1-3 ℃/minute of heating-cooling speed, malleation 0.18 ± 0.02MPa rises maintenance negative pressure 0.06MPa in the malleation process, and operating temperature is lower than below 60 ℃ comes out of the stove;
2) carry out second bonding
Each glueds joint part and glueds joint the inside and outside covering processing of overlap: paste hot setting structural film adhesive J-99B at the relative outer skin inner surface of overlap;
Each glueds joint the part pre-assembled: on the second bonding frock each is gluedd joint part and carry out pre-assembled, measure abutment joint gap and record;
Each glueds joint the part assembling: on the second bonding frock each is gluedd joint part and assemble, select the expansion glued membrane J-94 number of plies to fill according to butt joint gap numerical value and expansion glued membrane J-94 expansion character;
Working environment is: operate temperature in air conditioning room: 18-24 ℃, humidity: 40-65%, clean dustless;
3) solidify: curing oven solidifies, and variations in temperature is: temperature rises to 163 ℃ ± 5 ℃, and heating-cooling speed is 1-3 ℃/minute, constant temperature 240 ± 5 minutes;
Molding and removing surface: constant temperature finishes afterwards to come out of the stove below 60 ℃.
The advantage that the present invention has with beneficial effect is: each spare part among the present invention is not connected by the riveted joint mode, it is one-body molded behind regelate that each glueds joint spare part, glued joint by expansion glued membrane J-99B curing, the process of putting surplus by the one-sided honeycomb of abutment joint has been avoided in the product cure under pressure process the easily problem of depression of abutment joint simultaneously, has alleviated product weight and has improved product stability.
Description of drawings
Fig. 1 is that the present invention glueds joint design of part figure.
Fig. 2 is that the present invention glueds joint part second bonding structure chart.
The specific embodiment
Below in conjunction with accompanying drawing the present invention is described in further details.Referring to Fig. 1, Fig. 1 is for glueing joint design of part figure.1 is the expansion glued membrane after solidifying, and 2 is inside panel, and 3 are the expansion glued membrane after solidifying, and 4 is honeycomb, and 5 is exterior skin.
Participate in Fig. 2, Fig. 2 is for glueing joint part second bonding structure chart.6, the 7th, glued joint part, the 8, the 9th, the expansion glued membrane that has solidified, the 10th, the J-94 expansion glued membrane that adds when the second bonding butt joint is closed up.
1) respectively glueds joint the spare part moulding
Inside and outside covering (aluminium) 2 and 5 surface treatments: inside and outside covering (aluminium) 2 and 5 carries out chromic acid anodizing to be handled, to the inside and outside covering of chromic acid anodizing (aluminium) spray J-100 primer.
Glued joint assembling: 1. first lay exterior skin 5 on the metal forming frock, 2. lay hot setting structural film adhesive J-99B on exterior skin 5,3. lay honeycomb 4 on hot setting structural film adhesive J-99B, honeycomb 4 is after exterior skin 2 abutment joint edges all emit the 1mm-3mm surplus, paste one deck expansion glued membrane J-94,4. lay hot setting structural film adhesive J-99B on honeycomb 4 is 5. at hot setting structural film adhesive J-99B lay inside panel 2;
Working environment is: operate temperature in air conditioning room: 18-24 ℃, humidity: 40-65%, clean dustless.
Paste vacuum bag: on the metal forming frock, paste vacuum bag at glueing joint spare part.
Solidify: curing oven solidifies, be warming up to 180 ℃ ± 5 ℃, constant temperature 90 ± 10 minutes, 1-3 ℃/minute of heating-cooling speed, malleation 0.18 ± 0.02MPa rises maintenance negative pressure 0.06MPa in the malleation process, and operating temperature is lower than below 60 ℃ comes out of the stove, after expansion glued membrane J-94 solidifies, the expansion glued membrane 1 and 3 after the structural member abutment joint place after the moulding first time forms curing.
2) carry out second bonding
Each glueds joint part and glueds joint the inside and outside covering 2 of overlap and 5 processing: inside and outside covering 2 and 5 inner surfaces in the relative outside of covering overlap paste hot setting structural film adhesive J-99B,
Each glueds joint the part pre-assembled: on the second bonding frock each is gluedd joint part 6 and 7 and carry out pre-assembled, the expansion glued membrane 8 that has solidified between the measurement abutment joint and 9 gap and record.
Each glueds joint part assembling: on the second bonding frock each is gluedd joint part 6 and 7 and assemble, according to gap and the expansion glued membrane 10(J-94 of the expansion glued membrane 8 that has solidified between abutment joint and 9) expansion character selects expansion glued membrane 10(J-94) number of plies fills.
Working environment is: operate temperature in air conditioning room: 18-24 ℃, humidity: 40-65%, clean dustless.
3) solidify: curing oven solidifies, and variations in temperature is: temperature rises to 163 ℃ ± 5 ℃, and heating-cooling speed is 1-3 ℃/minute, constant temperature 240 ± 5 minutes.
4) molding and removing surface: constant temperature finishes afterwards to come out of the stove below 60 ℃.
Claims (1)
1. a structural member second bonding forming method that has curvature is characterized in that,
1) respectively glueds joint the spare part moulding
Be that the inside and outside covering of aluminium carries out surface treatment to material: after chromic acid anodizing is handled, internally, exterior skin spray J-100 primer;
Glued joint assembling: 1. first lay exterior skin on the metal forming frock, 2. put hot setting structural film adhesive J-99B on the exterior skin upper berth, 3. lay honeycomb on hot setting structural film adhesive J-99B, honeycomb is after exterior skin abutment joint edge all emits the 1mm-3mm surplus, paste one deck expansion glued membrane J-94,4. lay hot setting structural film adhesive J-99B on honeycomb is 5. at hot setting structural film adhesive J-99B lay inside panel;
Working environment is: operate temperature in air conditioning room: 18-24 ℃, humidity: 40-65%, clean dustless;
Paste vacuum bag: on the metal forming frock, paste vacuum bag at glueing joint spare part;
Solidify: curing oven solidifies, and is warming up to 180 ℃ ± 5 ℃, constant temperature 90 ± 10 minutes, and 1-3 ℃/minute of heating-cooling speed, malleation 0.18 ± 0.02MPa rises maintenance negative pressure 0.06MPa in the malleation process, and operating temperature is lower than below 60 ℃ comes out of the stove;
2) carry out second bonding
Each glueds joint part and glueds joint the inside and outside covering processing of overlap: paste hot setting structural film adhesive J-99B at the relative outer skin inner surface of overlap;
Each glueds joint the part pre-assembled: on the second bonding frock each is gluedd joint part and carry out pre-assembled, measure abutment joint gap and record;
Each glueds joint the part assembling: on the second bonding frock each is gluedd joint part and assemble, select the expansion glued membrane J-94 number of plies to fill according to abutment joint gap numerical value and expansion glued membrane J-94 expansion character;
Working environment is: operate temperature in air conditioning room: 18-24 ℃, humidity: 40-65%, clean dustless;
3) solidify: curing oven solidifies, and variations in temperature is: temperature rises to 163 ℃ ± 5 ℃, and heating-cooling speed is 1-3 ℃/minute, constant temperature 240 ± 5 minutes;
4) molding and removing surface: constant temperature finishes afterwards to come out of the stove below 60 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2013101460690A CN103192527A (en) | 2013-04-24 | 2013-04-24 | Secondary bonding forming method of structural part with curvature |
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| CN2013101460690A CN103192527A (en) | 2013-04-24 | 2013-04-24 | Secondary bonding forming method of structural part with curvature |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104861884A (en) * | 2015-05-15 | 2015-08-26 | 湖北三江航天江河化工科技有限公司 | Method for bonding carbon fiber/phenolic-nitrile rubber materials |
| CN105599416A (en) * | 2015-09-02 | 2016-05-25 | 哈尔滨飞机工业集团有限责任公司 | Large curvature metal panel sandwich part forming dent prevention method |
| CN105799162A (en) * | 2016-04-18 | 2016-07-27 | 江西洪都航空工业集团有限责任公司 | Application method of protective film-shaped primer of aluminum alloy cementing surface |
| CN106275379A (en) * | 2015-06-05 | 2017-01-04 | 哈尔滨飞机工业集团有限责任公司 | A kind of composite big thickness deep camber honeycomb parts forming method |
| CN109291459A (en) * | 2018-08-02 | 2019-02-01 | 哈尔滨飞机工业集团有限责任公司 | Composite plys process |
| CN109555860A (en) * | 2018-11-23 | 2019-04-02 | 中航通飞华南飞机工业有限公司 | A kind of full composite material second bonding wing tank encapsulating method |
| CN111706585A (en) * | 2020-05-15 | 2020-09-25 | 成都飞机工业（集团）有限责任公司 | Reverse gluing method for sheet aluminum alloy basin-shaped part |
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| CN101422964A (en) * | 2008-12-18 | 2009-05-06 | 中国航空工业第一集团公司北京航空材料研究院 | Forming method of composite material of ultra-large size special honeycomb structure |
| CN102225703A (en) * | 2011-04-12 | 2011-10-26 | 江西洪都航空工业集团有限责任公司 | Manufacturing method of integral glass fiber reinforced plastic unmanned aerial vehicle wing |
| CN102848579A (en) * | 2012-03-09 | 2013-01-02 | 昌河飞机工业（集团）有限责任公司 | Manufacturing method of double-sided honeycomb sandwich composite material product |
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2013
- 2013-04-24 CN CN2013101460690A patent/CN103192527A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101422964A (en) * | 2008-12-18 | 2009-05-06 | 中国航空工业第一集团公司北京航空材料研究院 | Forming method of composite material of ultra-large size special honeycomb structure |
| CN102225703A (en) * | 2011-04-12 | 2011-10-26 | 江西洪都航空工业集团有限责任公司 | Manufacturing method of integral glass fiber reinforced plastic unmanned aerial vehicle wing |
| CN102848579A (en) * | 2012-03-09 | 2013-01-02 | 昌河飞机工业（集团）有限责任公司 | Manufacturing method of double-sided honeycomb sandwich composite material product |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104861884A (en) * | 2015-05-15 | 2015-08-26 | 湖北三江航天江河化工科技有限公司 | Method for bonding carbon fiber/phenolic-nitrile rubber materials |
| CN104861884B (en) * | 2015-05-15 | 2017-03-01 | 湖北三江航天江河化工科技有限公司 | A kind of adhering method of carbon fiber/phenolic aldehyde nitrile rubber |
| CN106275379A (en) * | 2015-06-05 | 2017-01-04 | 哈尔滨飞机工业集团有限责任公司 | A kind of composite big thickness deep camber honeycomb parts forming method |
| CN106275379B (en) * | 2015-06-05 | 2018-10-12 | 哈尔滨飞机工业集团有限责任公司 | A kind of big thickness deep camber honeycomb parts forming method of composite material |
| CN105599416A (en) * | 2015-09-02 | 2016-05-25 | 哈尔滨飞机工业集团有限责任公司 | Large curvature metal panel sandwich part forming dent prevention method |
| CN105599416B (en) * | 2015-09-02 | 2018-03-02 | 哈尔滨飞机工业集团有限责任公司 | A kind of big curvature metal decking interlayer part shaping indenture prevention method |
| CN105799162A (en) * | 2016-04-18 | 2016-07-27 | 江西洪都航空工业集团有限责任公司 | Application method of protective film-shaped primer of aluminum alloy cementing surface |
| CN105799162B (en) * | 2016-04-18 | 2017-09-08 | 江西洪都航空工业集团有限责任公司 | A kind of aluminium alloy glue surfaces protect the application method of membranaceous primer |
| CN109291459A (en) * | 2018-08-02 | 2019-02-01 | 哈尔滨飞机工业集团有限责任公司 | Composite plys process |
| CN109555860A (en) * | 2018-11-23 | 2019-04-02 | 中航通飞华南飞机工业有限公司 | A kind of full composite material second bonding wing tank encapsulating method |
| CN111706585A (en) * | 2020-05-15 | 2020-09-25 | 成都飞机工业（集团）有限责任公司 | Reverse gluing method for sheet aluminum alloy basin-shaped part |
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Application publication date: 20130710 |