CN110712324B - Integrated die for molding and assembling composite material wings - Google Patents
Integrated die for molding and assembling composite material wings Download PDFInfo
- Publication number
- CN110712324B CN110712324B CN201911041141.7A CN201911041141A CN110712324B CN 110712324 B CN110712324 B CN 110712324B CN 201911041141 A CN201911041141 A CN 201911041141A CN 110712324 B CN110712324 B CN 110712324B
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- wing
- pressing plate
- rib
- front edge
- die
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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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
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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
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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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
Abstract
The invention provides a composite material wing forming and assembling integrated die which comprises an airfoil profile surface die, a root clamping plate, an end clamping plate, a front edge pressing plate, a rear edge forming pressing plate, a rib positioning pressing plate, a main wing spar limiting block and a wing rib fixing rod. The invention realizes the integration of assembly and curing of all components, can also realize the manufacture of the trailing edge in the assembly, and finishes the assembly, the preparation of the trailing edge and the co-curing by one set of dies.
Description
Technical Field
The invention relates to a composite material wing forming and assembling integrated die, and belongs to the technical field of die manufacturing.
Background
Composite structures are used more and more in the aerospace field due to their higher specific strength and modulus than metallic materials. Composite materials, particularly wings which are used as main bearing parts, are successfully adopted from military airplanes to civil airplanes, and higher strength and rigidity are needed to ensure the performance requirement and the safety requirement of the flight process, so that the carbon fiber composite materials become the main materials of wing structures.
The composite material is applied as a structural material, and internal defects of the material, such as glue shortage, gaps, layering and the like, must be avoided as much as possible, so that the currently common manufacturing process for ensuring the product quality is autoclave and die pressing. Wings tend to be large in size and difficult to manufacture as a unitary part using a molding process, autoclaves of greater size than wings are required if using autoclave technology, and autoclaves are expensive and therefore tend to be manufactured in small parts and then assembled, for example requiring a large number of trusses, skin structures. Therefore, a large number of parts need to be manufactured respectively and then assembled, gluing and riveting are adopted in the assembly process, the process is complicated, the manufacturing time is long, huge workload needs to be consumed, and high production cost is directly caused. To unmanned aerial vehicle need realize low-cost manufacturing, the demand that low-cost manufacturing can't be satisfied to above-mentioned manufacturing approach.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide the composite material wing forming and assembling integrated die which can realize high-quality, low-cost and high-precision manufacturing and assembling, reduce the manufacturing cost and realize trailing edge forming in assembling.
The technical solution of the invention is as follows: a composite material wing forming and assembling integrated die comprises a main wing beam, a plurality of wing ribs, a front edge and a rear edge, the forming and assembling integrated die comprises an airfoil surface die, a root clamping plate, an end clamping plate, a front edge pressing plate, a rear edge forming pressing plate, a rib positioning pressing plate, main wing beam limiting blocks and wing rib fixing rods, the forming surface of the airfoil surface die is consistent with the outer surface of a composite material wing and comprises a front edge profile, a main wing beam profile and a rear edge profile, the airfoil surface die is provided with the main wing beam limiting blocks in the wingspan direction, the main wing beam is placed on the main wing beam profile of the airfoil surface die and is positioned on the airfoil surface die by the main wing beam limiting blocks, the root clamping plate and the end clamping plate, a front edge preform is placed on the front edge profile of the airfoil surface die and is positioned on the airfoil surface die by the front edge pressing plate, and a wing rib preform is fixed on the wing rib fixing rods, the wing rib fixing rod is characterized in that two ends of the wing rib fixing rod are fixed on the airfoil surface mould through the root clamping plate and the end clamping plate, the wing rib preform is positioned on the main wing spar preform, a trailing edge forming raw material is paved on a trailing edge profile on the airfoil surface mould and is positioned on the airfoil surface mould through a trailing edge forming pressing plate, the trailing edge forming pressing plate and the trailing edge profile of the airfoil surface mould form a trailing edge forming cavity, the rib positioning pressing plate is arranged at the wing rib fixing and mounting position, two ends of the rib positioning pressing plate are respectively fixedly connected with the airfoil surface mould and the trailing edge forming pressing plate, the middle part of the rib fixing pressing plate is pressed on the wing rib preform, and the positions of the main wing spar, the wing rib, the leading edge and the trailing edge are fixed in the forming process.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention realizes the integration of assembly and curing of all components, and can also realize the manufacture of the trailing edge in the assembly, and a set of dies finishes the assembly, the preparation of the trailing edge and the co-curing;
(2) according to the invention, the front edge, the wing ribs and other non-main bearing component prefabricated parts can be prepared independently, the forming and assembling of the components of the wing part structure except the main beam can be realized, and a set of mould is shared to realize the front and rear edge manufacturing, component assembling and curing, so that the manufacturing cost is reduced;
(3) the invention realizes the manufacture and assembly with high quality, low cost and high precision, further reduces the manufacture cost, and realizes the manufacture of the full composite material wing with high precision, low cost and integrated assembly and molding;
(4) the invention realizes the gluing and assembly of multiple parts, saves the cost of multiple sets of dies and realizes lower manufacturing cost.
Drawings
FIG. 1 is a view of the mold construction of the present invention;
FIG. 2 is a view of the mold structure of the present invention (without the rib-locating platen);
FIG. 3 is a side view in the expanded direction of the assembled mold of the present invention.
Detailed Description
In order to reduce the manufacturing cost of the wing, the invention designs a forming and assembling integrated die, so that the composite material wing can be assembled, formed and integrally cured on one set of die.
For the wing made of the full composite materials with basically glued or co-cured assembly, in order to realize the manufacture and the assembly with high quality, low cost and high precision and further reduce the manufacturing cost, the forming of the front edge and the rear edge can be realized on an assembly mould.
The present invention will be described in detail with reference to the following examples and accompanying drawings.
The invention provides a composite material wing forming and assembling integrated die as shown in figures 1, 2 and 3, the composite material wing comprises a main wing spar, a plurality of wing ribs, a front edge 13 and a rear edge 14, the forming and assembling integrated die comprises an airfoil surface die 1, a root clamping plate 2, an end clamping plate 3, a rear edge forming pressing plate 4, a rib positioning pressing plate 5, a front edge pressing plate 6, main wing spar limiting blocks 7 and wing rib fixing rods 8, the forming surface of the airfoil surface die 1 is consistent with the outer surface of the composite material wing and comprises a front edge profile, a main wing spar profile and a rear edge profile, the airfoil surface die 1 is provided with the main wing spar limiting blocks 7 in the spanwise direction, the main wing spar is placed on the main wing spar profile of the airfoil surface die 1 and is positioned on the airfoil surface die 1 by the main wing spar limiting blocks 7, the root clamping plate 2 and the end clamping plate 3, the prefabricated body of the front edge is placed on the front edge profile of the airfoil surface die 1, the wing rib forming device is characterized in that a front edge pressing plate 6 is positioned on an airfoil profile mold 1, a wing rib prefabricated body is fixed on a wing rib fixing rod 8, two ends of the wing rib fixing rod 8 are fixed on the airfoil profile mold 1 through a root clamping plate 2 and an end clamping plate 3, the wing rib prefabricated body is positioned on a main wing beam prefabricated body, a rear edge forming raw material is paved on a rear edge profile on the airfoil profile mold 1 and is positioned on the airfoil profile mold 1 through a rear edge forming pressing plate 4, the rear edge forming pressing plate 4 and the rear edge profile of the airfoil profile mold 1 form a rear edge forming cavity, a rib positioning pressing plate 5 is arranged at a wing rib fixing and mounting position, two ends of the rib positioning pressing plate are respectively fixedly connected with the airfoil profile mold 1 and the rear edge forming pressing plate 4, the middle part of the rib pressing plate is pressed on the wing rib prefabricated body, and the positions of the main wing beam, the wing rib, a front edge 13 and a rear edge 14 are fixed in the forming process.
The forming technology comprises out-of-can bag prepreg forming (OOA) and vacuum bag wet forming. The main wing spar as the main bearing structural part can be formed by adopting bag-outside-tank prepreg pressing, and the structural parts such as the front edge, the rear edge, the wing ribs and the like of the non-main bearing part can be formed by adopting vacuum bag prepreg pressing or vacuum bag wet method.
The wing main wing beam as a main bearing part needs to be manufactured by other processes, and then is fixed on the airfoil profile surface mould 1 through the root clamping plate 2, the end clamping plate 3 and the main wing beam limiting block 7 structure and limited, so that the mounting position precision of the main wing beam is ensured. The root of the airfoil profile is provided with a mounting post 10 which cooperates with a main spar metal joint 15.
The leading edge can be preformed by the die of the invention and then installed on the airfoil surface die 1 and limited by the airfoil surface die 1 and the leading edge pressure plate 6. The front edge molded surface of the airfoil surface mold 1 and the front edge pressing plate 6 form a front edge molding cavity, and a vacuum bag is adopted in advance to mold a front edge preform through the airfoil surface mold and the front edge pressing plate.
The ribs may be formed by machining the panel and then mechanically cutting it to the required shape and size, either by vacuum bag pre-preg or by vacuum bag wet-forming.
The trailing edge part of the die is provided with a trailing edge forming press plate 4, and the main function is to utilize the trailing edge profile of the airfoil surface die 1 formed by the wing to be matched with the trailing edge forming press plate 4 to form and fix the trailing edge, thereby realizing the accurate manufacture of the trailing edge. The rear edge forming pressing plate 4 is arranged below the rib forming pressing plate 5, is limited and fixed through the rib forming pressing plate 5 and is fixed on the airfoil surface die 1, and sufficient forming pressure is guaranteed.
The rear edge can be formed by adopting prepreg and adopting a vacuum bag prepreg forming process, or can be formed by adopting fiber re-impregnation and adopting a vacuum bag wet forming process, and foam sandwich can be arranged.
The mould material can adopt wood resin, glass fiber reinforced plastic, carbon fiber composite material, wood and various metal materials (aluminum alloy and steel) which are nearly commonly used, and the selection standard of different materials is determined according to the process requirements, the cost and the use convenience.
The actual size is mainly determined according to the size of the airfoil to be molded, the mold can adopt electric heating, water heating and oil heating devices and is provided with a corresponding temperature control device, or a heating device is not arranged, a blanket is directly heated or heated by an oven, and the specific heating form can be determined according to the molding temperature requirement of the mold.
The mould can realize the adhesive assembly of the wing skeleton structure (comprising a main wing beam, wing ribs, a front edge, a rear edge, a joint and the like) made of full composite materials. In combination with wet forming techniques, the manufacture of a part of the assembly can be achieved.
Main wing spar and wing rib mainly carry out spacing and location through root cardboard 2, tip cardboard 3, main wing spar stopper 7 in the mould, guarantee the precision of assembly.
The front edge in the die is limited and positioned through the airfoil surface die 1 and the front edge pressing plate 6, and the front edge can be directly formed on the die by assembling the airfoil surface die 1 and the front edge pressing plate 6.
The rib gluing and assembling in the die are mainly completed through two components, namely a rib positioning pressing plate 5 and a rib fixing rod 8, so that the rib can be accurately positioned in three directions, and the bonding and assembling can be completed. Wherein the outer diameter of the rib fixing rod 8 is slightly lower than the weight-reducing hole diameter of the rib, and the rib fixing rod can be inserted into the weight-reducing hole and clamped.
The trailing edge structure of the die is mainly formed on an airfoil surface die 1 through a trailing edge forming pressing plate 4 and a rib positioning pressing plate 5, the profile of the trailing edge is guaranteed through the airfoil surface die 1 and the trailing edge forming pressing plate 4, and the positioning and the complete fixation of the trailing edge forming pressing plate 4 are guaranteed through the rib positioning pressing plate 5.
Examples
The method comprises the steps of adopting wood-substitute resin as a material of the airfoil surface mold 1, firstly curing, then forming a main body of the mold 1, machining a mold surface through CNC, and finally performing surface correction and glue coating to complete the manufacture of the airfoil surface mold. Root cards 2 and end cards 3 are also manufactured in this way. The die support 9 is welded by adopting a steel structure, and the airfoil surface die 1 is fixed on the die support 9.
Processing a rear edge forming press plate: the method is characterized in that a glass fiber reinforced plastic composite material is used as a main material, wood resin is adhered to a molding surface, then a rear edge molding surface is processed through a CNC machine, and surface paint is sprayed.
Processing a rib positioning pressing plate: the method is characterized in that a glass fiber reinforced plastic composite material is used as a main material, wood resin is bonded on a molding surface, then a CNC (computerized numerical control) machine is used for processing the outer molding surface of the wing rib of the composite wing section, and surface paint is sprayed.
The wing rib fixing rod is manufactured by adopting a pipe coiling process, and carbon fiber reinforced resin composite materials can be selected as the materials.
The invention has not been described in detail and is in part known to those of skill in the art.
Claims (3)
1. The utility model provides a combined material wing shaping assembly integration mould, the combined material wing includes main wing spar, a plurality of wing rib, leading edge and trailing edge, its characterized in that: the forming and assembling integrated die comprises an airfoil profile die, a root clamping plate, an end clamping plate, a front edge pressing plate, a rear edge forming pressing plate, a rib positioning pressing plate, main wing beam limiting blocks and wing rib fixing rods, wherein the forming surface of the airfoil profile die is consistent with the outer profile surface of a composite material wing and comprises a front edge profile, a main wing beam profile and a rear edge profile, the airfoil profile die is provided with a plurality of main wing beam limiting blocks in the wingspan direction, a main wing beam is placed on the main wing beam profile of the airfoil profile die and is positioned on the airfoil profile die by the main wing beam limiting blocks, the root clamping plate and the end clamping plate, a front edge prefabricated body is placed on the front edge profile of the airfoil profile die and is positioned on the airfoil profile die by the front edge pressing plate, the prefabricated body of a wing rib is fixed on the wing rib fixing rods, two ends of the wing rib fixing rods are fixed on the airfoil profile die by the root clamping plate and the end clamping plate and position the prefabricated body of the wing rib on the main wing beam, the wing rib positioning pressing plate is arranged at the fixed installation position of the wing rib, two ends of the rib positioning pressing plate are respectively fixedly connected with the wing profile surface mold and the rear edge molding pressing plate, the middle part of the rib positioning pressing plate is pressed on a prefabricated body of the wing rib, and the positions of a main wing beam, the wing rib, the front edge and the rear edge are fixed in the molding process;
the front edge molding cavity is formed by the front edge molding surface of the airfoil surface mold and the front edge pressing plate, a front edge prefabricated body is formed in advance through the airfoil surface mold and the front edge pressing plate, and the front edge prefabricated body is formed by adopting a vacuum bag;
the rear edge adopts prepreg or adopts fiber re-impregnated as a forming raw material.
2. The integrated die for forming and assembling a composite material wing according to claim 1, wherein: the main wing beam is formed by pressing prepreg through an outer tank bag.
3. The integrated die for forming and assembling a composite material wing according to claim 1, wherein: the root of the airfoil surface mould is provided with an installation column matched with the main wing beam metal joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911041141.7A CN110712324B (en) | 2019-10-30 | 2019-10-30 | Integrated die for molding and assembling composite material wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911041141.7A CN110712324B (en) | 2019-10-30 | 2019-10-30 | Integrated die for molding and assembling composite material wings |
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| Publication Number | Publication Date |
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| CN110712324A CN110712324A (en) | 2020-01-21 |
| CN110712324B true CN110712324B (en) | 2022-06-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911041141.7A Active CN110712324B (en) | 2019-10-30 | 2019-10-30 | Integrated die for molding and assembling composite material wings |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112405953B (en) * | 2020-09-18 | 2022-05-03 | 航天特种材料及工艺技术研究所 | Composite material machine body integrated forming assembly die and manufacturing method |
| CN112238551B (en) * | 2020-09-27 | 2022-04-12 | 航天特种材料及工艺技术研究所 | Multi-part integrated forming assembly die and forming assembly method for composite wing |
Citations (5)
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| WO2014070341A1 (en) * | 2012-10-31 | 2014-05-08 | The Boeing Company | System and method for facilitating fluid movement in closed molds for composite parts |
| CN106273542A (en) * | 2016-10-13 | 2017-01-04 | 西安爱生技术集团公司 | Composite is straight empennage twin beams box section entirety co-curing forming method |
| CN206085432U (en) * | 2016-10-20 | 2017-04-12 | 西安爱生技术集团公司 | Whole co -curing of two roof beam box sections of straight fin of combined material frock for shaping |
| CN108177360A (en) * | 2017-12-25 | 2018-06-19 | 航天神舟飞行器有限公司 | The forming frock and its forming method of unmanned plane composite wing integral panel |
| CN108959744A (en) * | 2018-06-21 | 2018-12-07 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles composite wing wing box manufacturing method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110193955B (en) * | 2019-07-03 | 2021-05-18 | 西安爱生技术集团公司 | Process forming method for composite outer wing of small and medium-sized unmanned aerial vehicle |
-
2019
- 2019-10-30 CN CN201911041141.7A patent/CN110712324B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014070341A1 (en) * | 2012-10-31 | 2014-05-08 | The Boeing Company | System and method for facilitating fluid movement in closed molds for composite parts |
| CN106273542A (en) * | 2016-10-13 | 2017-01-04 | 西安爱生技术集团公司 | Composite is straight empennage twin beams box section entirety co-curing forming method |
| CN206085432U (en) * | 2016-10-20 | 2017-04-12 | 西安爱生技术集团公司 | Whole co -curing of two roof beam box sections of straight fin of combined material frock for shaping |
| CN108177360A (en) * | 2017-12-25 | 2018-06-19 | 航天神舟飞行器有限公司 | The forming frock and its forming method of unmanned plane composite wing integral panel |
| CN108959744A (en) * | 2018-06-21 | 2018-12-07 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles composite wing wing box manufacturing method |
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