CN104669641A - Multi-directional pressure forming method of double-enclosed-cavity part - Google Patents
Multi-directional pressure forming method of double-enclosed-cavity part Download PDFInfo
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- CN104669641A CN104669641A CN201310628288.2A CN201310628288A CN104669641A CN 104669641 A CN104669641 A CN 104669641A CN 201310628288 A CN201310628288 A CN 201310628288A CN 104669641 A CN104669641 A CN 104669641A
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- Prior art keywords
- silicon rubber
- vacuum bag
- bag
- forming method
- enclosed
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention belongs to the aircraft manufacturing technology and relates to a multi-directional pressure forming method of a double-enclosed-cavity part. The multi-directional pressure forming method comprises the following steps: (1.1) laying a bottom skin of the part on a lower mold of a tool; (1.2) locating a front beam by taking the lower mold of the tool as a working face through an aluminum dowel pin after the bottom skin is laid; (1.3) arranging a reinforced layer at the tip end of the part; (1.4) arranging silicone rubber A and silicone rubber B at the positions of small circular beads of inner cavities at two ends of an enclosed cavity I formed by the reinforced layer of the part and the front beam; (1.5) arranging a 100mm tubular vacuum bag between the silicone rubber A and the silicone rubber A in a folding manner; (1.6) arranging a 75mm tubular vacuum bag in an enclosed cavity II of the front beam and the circular bead of the part in a folding manner, and arranging a silicon sheet between the 75mm tubular vacuum bag and the circular bead of the part in a folding manner; (1.7) overturning a top skin of the part to realize laying; (1.8) making an integral vacuum bag of the outer layer after mold closing; and (1.9) stripping the mold. The multi-directional pressure forming method of the double-enclosed-cavity part has strong operability and high molding quality.
Description
Technical field
The invention belongs to aircraft manufacturing technology, relate to the multidirectional extrusion forming method of a kind of double-enclosure chamber part.
Background technology
Double-enclosure chamber overall co-curing trimmer class part mostly is the main operation rudder face of aircraft, in aircraft flight rolling, play important corrective action.Its profile is long and narrow, complex structure, and in enclosed cavity, operating space is little, and interior profile matching requirements precision is high, and counterweight is accurate, and manufacturing technology difficulty is large.Home products quality is more unstable, FAQs mostly is inner chamber small round corner (R angle) gum deposit, inner surface pressurized is not enough, concavo-convex rough, be difficult to ensure to coordinate requirement, folder cloth problem common in technical process often solves with prefabricated board method, easily causes product surface to sink or the intensity effect of fiber bending, there is the problem opening mould difficulty simultaneously.
Summary of the invention
Technical problem to be solved by this invention is: provide a kind of workable, multidirectional extrusion forming method of double-enclosure chamber part that Forming Quality is high.
Technical scheme of the present invention is: the multidirectional extrusion forming method of a kind of double-enclosure chamber part, is characterized by and said method comprising the steps of:
1.1) part lower surface covering is covered on frock counterdie upper berth;
1.2) select aluminum shop bolt, with frock counterdie for working face, after paving has covered Lower Half covering, complete front-axle beam location;
1.3) enhancement Layer is placed at part tip;
1.4) silicon rubber A and silicon rubber B is put into respectively at the inner chamber small round corner place, two ends of enclosed cavity I of part enhancement Layer and front-axle beam composition;
1.5) between silicon rubber A and silicon rubber B, 100 millimeters of tubulose vacuum bags are put into folding gimmick;
1.6) in the enclosed cavity II that front-axle beam and part fillet are formed, put into 75 millimeters of tubulose vacuum bags with folding gimmick, then silica gel piece is put between 75 millimeters of tubulose vacuum bags and part fillet with folding gimmick;
1.7) part upper surface covering has been turned down laying, ensured that part fillet place highest point is 2 ~ 3mm to frock gap;
1.8) the bag operation of outer overall vacuum bag is carried out after matched moulds, by bonding with external vacuum bag for tubular vacuum bag in enclosed cavity with the protection composite bag compression system forming multidirectional pressurization;
1.9) open silicon rubber and tubular bag in modulo operation to take out in extraction mode, the aluminum shop bolt in part is knocked out locating hole, and the mould mode that indirectly opens that part is loosened by aluminum pin comes off, and completes Qi Mo.
The double-enclosure chamber of the present invention multidirectional extrusion forming method of part utilizes metallic combination tool structure feature, adopts vacuum bag-mold pressing-silicon rubber associating pressuring method, has following beneficial effect:
One, the gap-fill after utilizing primary and secondary vacuum bag support silicon rubber to complete matched moulds, die closing operation is simple, and soft mode pressurization and the comprehensive function of metallic combination frock, improve operability;
Two, different parts adopts different pressure, meets pressure and the profile control overflow of privileged site, ensure that part curing performance and physical dimension;
Three, have employed aluminium pin accurately to locate and part removal, optimize mould structure;
Four, protection composite bag has been innovated in conjunction with pressure structure hollow in the enclosed cavity of silicon rubber and has been opened mold technique, solves the problem opening mould difficulty in silicon rubber assistant formation technique.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of a kind of detailed description of the invention of double-enclosure chamber part of the present invention multidirectional extrusion forming method;
Wherein, 1-part fillet, 2-silica gel piece, 3-75 millimeter tubulose vacuum bag, 4-front-axle beam, 5-silicon rubber A, 6-100 millimeter tubulose vacuum bag, 7-silicon rubber B, 8-enhancement Layer, 9-frock counterdie, 10-aluminum shop bolt, 11-lower surface covering.
Detailed description of the invention
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described further.
See Fig. 1, it is the schematic diagram of a kind of detailed description of the invention of double-enclosure chamber part of the present invention multidirectional extrusion forming method.The specific embodiment of the present invention step is as follows:
1.1) part lower surface covering 11 is covered on frock counterdie 9 upper berth;
1.2) by selecting aluminum shop bolt 10, with frock counterdie 9 for working face, completing front-axle beam 4 after paving has covered lower surface covering and locating;
1.3) enhancement Layer 8 is placed at part tip;
1.4) in the enclosed cavity I that part enhancement Layer 8 and front-axle beam 4 form, put into silicon rubber A5 and silicon rubber B7, object is that auxiliary pressurized improves R angle (two ends inner chamber small round corner) quality in chamber.
1.5) between silicon rubber A5 and silicon rubber B7,100 millimeters of tubulose vacuum bags 6 are put into folding gimmick, object is by the vacuum of 100 millimeters of tubulose vacuum bags 6 in subsequent process, both the location of auxiliary silicon rubber A5 and silicon rubber B7, and suitable pressure can be provided to reach the thickness requirement of part in conjunction with the expansion of silicon rubber.
1.6) in the enclosed cavity II that front-axle beam 4 and part fillet 1 are formed, 75 millimeters of tubulose vacuum bags 3 and silica gel piece 2 is put into folding gimmick, object is the support by completing in the vacuum of 75 millimeters of tubulose vacuum bags 3 in subsequent process silica gel piece 2, silica gel piece 2 along part fillet place in the curing process expandable pressurized to form good fillet surfaces externally and internally quality.
1.7) part upper surface covering has been turned down laying, ensure that part fillet place highest point is 2 ~ 3mm to frock gap, die closing operation is simplified by this gap, completely avoid folder cloth problem.
1.8) the bag operation of outer overall vacuum bag is carried out after matched moulds, by bonding with external vacuum bag with the protection composite bag compression system forming multidirectional pressurization for the tubular vacuum bag (comprising 75 millimeters of tubulose vacuum bag tubular vacuum bags 3 and 100 millimeters of tubulose vacuum bags 6) in enclosed cavity.This operation utilizes tubular vacuum bag external support silicon rubber A5, silicon rubber B7 and silica gel piece 2 in subsequent cure process, complete inner chamber pressurization, reaches the second best in quality object of exocoel in closed molding processes.
1.9) open silicon rubber A5 in modulo operation, silicon rubber B7, silica gel piece 2 and tubular vacuum bag to take out in extraction mode, the aluminum shop bolt 10 in part will be knocked out locating hole, and the mould mode that indirectly opens that part is loosened by aluminum pin comes off, and completes Qi Mo.
Claims (1)
1. the multidirectional extrusion forming method of double-enclosure chamber part, is characterized by and said method comprising the steps of:
1.1) part lower surface covering is covered on frock counterdie upper berth;
1.2) select aluminum shop bolt, with frock counterdie for working face, after paving has covered Lower Half covering, complete front-axle beam location;
1.3) enhancement Layer is placed at part tip;
1.4) silicon rubber A and silicon rubber B is put into respectively at the inner chamber small round corner place, two ends of enclosed cavity I of part enhancement Layer and front-axle beam composition;
1.5) between silicon rubber A and silicon rubber B, 100 millimeters of tubulose vacuum bags are put into folding gimmick;
1.6) in the enclosed cavity II that front-axle beam and part fillet are formed, put into 75 millimeters of tubulose vacuum bags with folding gimmick, then silica gel piece is put between 75 millimeters of tubulose vacuum bags and part fillet with folding gimmick;
1.7) part upper surface covering has been turned down laying, ensured that part fillet place highest point is 2 ~ 3mm to frock gap;
1.8) the bag operation of outer overall vacuum bag is carried out after matched moulds, by bonding with external vacuum bag for tubular vacuum bag in enclosed cavity with the protection composite bag compression system forming multidirectional pressurization;
1.9) open silicon rubber and tubular bag in modulo operation to take out in extraction mode, the aluminum shop bolt in part is knocked out locating hole, and the mould mode that indirectly opens that part is loosened by aluminum pin comes off, and completes Qi Mo.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310628288.2A CN104669641A (en) | 2013-12-02 | 2013-12-02 | Multi-directional pressure forming method of double-enclosed-cavity part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310628288.2A CN104669641A (en) | 2013-12-02 | 2013-12-02 | Multi-directional pressure forming method of double-enclosed-cavity part |
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| CN104669641A true CN104669641A (en) | 2015-06-03 |
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| CN201310628288.2A Pending CN104669641A (en) | 2013-12-02 | 2013-12-02 | Multi-directional pressure forming method of double-enclosed-cavity part |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106965464A (en) * | 2016-01-13 | 2017-07-21 | 哈尔滨飞机工业集团有限责任公司 | A kind of shaping pressure method of solution R angles gum deposit |
| CN110877463A (en) * | 2018-09-05 | 2020-03-13 | 中航贵州飞机有限责任公司 | Low-cost forming method of V-shaped composite material part |
| CN111016224A (en) * | 2019-11-25 | 2020-04-17 | 中国运载火箭技术研究院 | Partitioned pressure forming method for closed airfoil structure |
| CN115056510A (en) * | 2022-07-06 | 2022-09-16 | 航天海鹰(镇江)特种材料有限公司 | Method for forming propeller blades by using double yellow bags and assisted autoclave |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001047507A (en) * | 1999-08-06 | 2001-02-20 | Sakura Gomme Kk | Bagging method in autoclave molding of composite material |
| CN202156039U (en) * | 2011-01-10 | 2012-03-07 | 江西昌河航空工业有限公司 | Vacuum bag for forming hollow tubular beams made of composite materials |
| CN102555231A (en) * | 2011-12-29 | 2012-07-11 | 成都飞机工业（集团）有限责任公司 | Method for manufacturing hollow box type element with non-circular section from carbon fiber composite |
| CN103042700A (en) * | 2012-12-27 | 2013-04-17 | 中国科学院工程热物理研究所 | Integrated forming method and device for segmented blade |
-
2013
- 2013-12-02 CN CN201310628288.2A patent/CN104669641A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001047507A (en) * | 1999-08-06 | 2001-02-20 | Sakura Gomme Kk | Bagging method in autoclave molding of composite material |
| CN202156039U (en) * | 2011-01-10 | 2012-03-07 | 江西昌河航空工业有限公司 | Vacuum bag for forming hollow tubular beams made of composite materials |
| CN102555231A (en) * | 2011-12-29 | 2012-07-11 | 成都飞机工业（集团）有限责任公司 | Method for manufacturing hollow box type element with non-circular section from carbon fiber composite |
| CN103042700A (en) * | 2012-12-27 | 2013-04-17 | 中国科学院工程热物理研究所 | Integrated forming method and device for segmented blade |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106965464A (en) * | 2016-01-13 | 2017-07-21 | 哈尔滨飞机工业集团有限责任公司 | A kind of shaping pressure method of solution R angles gum deposit |
| CN110877463A (en) * | 2018-09-05 | 2020-03-13 | 中航贵州飞机有限责任公司 | Low-cost forming method of V-shaped composite material part |
| CN111016224A (en) * | 2019-11-25 | 2020-04-17 | 中国运载火箭技术研究院 | Partitioned pressure forming method for closed airfoil structure |
| CN111016224B (en) * | 2019-11-25 | 2022-06-03 | 中国运载火箭技术研究院 | Partitioned pressure forming method for closed airfoil structure |
| CN115056510A (en) * | 2022-07-06 | 2022-09-16 | 航天海鹰(镇江)特种材料有限公司 | Method for forming propeller blades by using double yellow bags and assisted autoclave |
| CN115056510B (en) * | 2022-07-06 | 2024-02-13 | 航天海鹰(镇江)特种材料有限公司 | Method for forming propeller blade by using double yellow bags to assist autoclave |
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Application publication date: 20150603 |
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