CN115742369A - Forming die and forming method for reinforcing wing ribs between composite beams - Google Patents
Forming die and forming method for reinforcing wing ribs between composite beams Download PDFInfo
- Publication number
- CN115742369A CN115742369A CN202211494457.3A CN202211494457A CN115742369A CN 115742369 A CN115742369 A CN 115742369A CN 202211494457 A CN202211494457 A CN 202211494457A CN 115742369 A CN115742369 A CN 115742369A
- Authority
- CN
- China
- Prior art keywords
- die
- forming
- rib
- reinforcing
- composite material
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
The invention discloses a forming die and a forming method for reinforcing ribs among composite beams, wherein the forming die is used for forming the reinforcing ribs among the composite beams, each reinforcing rib consists of a rib web and rib flanges, the rib web is provided with a reinforcing rib and lightening holes, and the rib flanges are provided with flange sinking strips for matching with the flange strips of a wing beam; the molding die includes: the forming device comprises a forming lower die, a lower die core die, a plurality of intermediate dies and a forming upper die; the lower forming die, the lower die core die, the plurality of middle dies and the upper forming die are sequentially stacked to form a combined forming die; the middle part of the lower forming die is provided with a first groove matched with the shape of the lower die core die; the outer profile of the lower die core mold is matched with the inner profile of the reinforcing wing rib, and a second groove corresponding to the reinforcing rib is formed in the outer profile of the lower die core mold; the inner profile of the middle die is matched with the outer profile of the reinforcing rib, and the outer profile of the middle die is matched with the inner profile of the reinforcing rib; the inner profile of the upper forming die is matched with the outer profile of the reinforcing wing rib.
Description
Technical Field
The invention relates to the technical field of composite material forming, in particular to a forming die and a forming method for a reinforced rib between composite material beams.
Background
The wing rib is one of the important components of the airplane wing, is used as a transverse stress framework of the wing, generally conforms to the shape of an airfoil, and is used for supporting the skin of the airplane wing and maintaining the section shape of the wing. The rib is used for connecting the longitudinal skeleton and the skin into a whole, transmitting aerodynamic load transmitted by the skin and the stringer to the wing beam and keeping the shape of the wing section. In order to reduce the weight of the structure, the rib web is typically apertured, but the apertures reduce the strength and rigidity of the rib web and require reinforcement.
Disclosure of Invention
The invention aims to: the invention provides a reinforced rib between composite beams and a forming die thereof, and provides a forming method of the reinforced rib between the composite beams, aiming at the problem that the strength and rigidity of a rib web are greatly reduced after the rib web is perforated.
The invention is realized by the following technical scheme:
the forming die is used for forming the reinforced rib between the composite beams, the reinforced rib between the composite beams is composed of a rib web and rib flanges, a plurality of reinforcing ribs are arranged on the rib web, a plurality of lightening holes are further arranged on the rib web, and the rib flanges are provided with flanges sinking for being matched with the flanges of the wing beams;
the forming die comprises: the forming device comprises a forming lower die, a lower die core die, a plurality of intermediate dies and a forming upper die; the lower forming die, the lower die core die, the plurality of intermediate dies and the upper forming die are sequentially stacked to form a combined forming die;
the middle part of the lower forming die is provided with a first groove matched with the shape of the lower die core die; the outer molded surface of the lower die core mold is completely matched with the inner molded surface of the reinforcing wing rib, and a second groove corresponding to the reinforcing rib is formed in the outer molded surface of the lower die core mold; the inner profile of the middle die is matched with the outer profile of the reinforcing rib, and the outer profile of the middle die is matched with the inner profile of the reinforcing rib; the inner molded surface of the upper molding die is matched with the outer molded surface of the reinforcing rib.
The rib web plate is provided with rib lightening holes, and reinforcing ribs are arranged beside the lightening holes of the rib web plate. The two ends of the rib cap are provided with cap subsidences for matching with the cap of the wing spar. The reinforced wing rib between the composite material beams is formed by adopting a rapid curing prepreg mould pressing process.
The invention provides a forming die for reinforcing ribs between composite material beams, which comprises the following steps: the forming die is different from a common forming die and is a combined die comprising a lower forming die, a lower die core die, an intermediate die and an upper forming die. The number of the middle dies is not limited, and the lower die core die and the middle dies can be used as paving dies. The middle of the lower forming die is provided with a first groove which is completely matched with the shape of the lower die core die.
Preferably, in the forming die provided by the invention, the lower forming die, the middle die and the upper forming die can be provided with guide post holes, so that the die can be accurately closed in place. In the forming die, the lower die core die and the middle die can be replaced by turns quickly, so that the production efficiency is improved.
Further, a mould for forming the reinforced rib between the composite material beams is as follows: the lightening holes are formed in rib webs between two adjacent reinforcing ribs.
Further, a mould for forming the reinforced rib between the composite material beams is as follows: the flanges are recessed at the ends of the rib flanges.
Further, a mould for forming the reinforced rib between the composite material beams is as follows: the lower die core die and the middle die can be used as paving dies.
Further, a mould for forming the reinforced rib between the composite material beams is as follows: the forming die is made of die steel with high hardness. For example, P20 steel is selected.
A method for forming a reinforced rib between beams made of composite materials is characterized in that the method adopts the forming die to carry out forming and manufacturing, and the method comprises the following steps:
s1, fixing the lower forming die on a lower platform of a die press, fixing the upper forming die on an upper platform of the die press, aligning the lower forming die with the upper forming die, and starting heating at the same time;
s2, respectively paving and sticking prepreg on the lower die core die and the middle die to form a prefabricated body;
s3, sequentially placing the lower die core die paved with the prefabricated body into a first groove of a forming lower die, and placing the middle die paved with the prefabricated body onto the lower die core die;
s4, die assembly: closing the lower forming die and the upper forming die, and heating and pressurizing simultaneously to cure;
s5, cooling after solidification, and opening the mold;
s6, demolding: and taking down the reinforced wing ribs between the cured composite material beams from the lower die core die and the middle die.
The reinforced wing rib between the composite material beams is formed by adopting a rapid curing prepreg mould pressing process.
Further, a method for forming the reinforced rib between the composite material beams comprises the following steps: the temperature of heating in step S1 depends on the resin.
Further, a method for forming the reinforced rib between the composite material beams comprises the following steps: the pressure set in step S3 is 0.6-2.0MPa.
Further, a method for forming the reinforced rib between the composite material beams comprises the following steps: the heating mode adopted in the step S3 is electromagnetic induction heating, and the heating time is 10-15 minutes.
The invention has the beneficial effects that:
(1) The structural design of the reinforced rib between the composite material beams manufactured by the invention solves the problem of strength and rigidity reduction caused by the opening of the web plate of the existing rib.
(2) The reinforced wing ribs between the composite material beams manufactured by the invention adopt a rapid curing prepreg compression molding process, and can realize mass production.
(3) The forming die for the reinforcing rib between the beams made of the composite materials can quickly form the reinforcing rib between the beams in batches, and the formed rib between the beams has smooth and flat inner and outer surfaces and high dimensional precision.
(4) The lower die core die and the middle die in the composite material inter-beam reinforced rib forming die can be replaced in turn quickly, and the production efficiency can be effectively improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings may be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural view of a reinforcing rib between composite beams made in accordance with the present invention;
FIG. 2 is a schematic structural view of a mold for forming a reinforced rib between beams of composite material according to the present invention;
FIG. 3 is a schematic structural diagram of a lower forming die in a forming die for reinforcing wing ribs between composite material beams, which is designed by the invention;
FIG. 4 is a schematic structural diagram of a lower mold core of the reinforced rib forming mold between beams made of composite materials according to the present invention;
5-6 are schematic structural views of the middle mold in the forming mold for the reinforced wing rib between the composite material beams designed by the invention;
fig. 7 is a schematic structural diagram of a forming upper die in a forming die for a reinforced rib between composite material beams designed by the invention.
The labels in the figure are: the composite material rib forming process comprises the following steps of 1 reinforcing rib between composite material beams, 2 forming lower dies, 3 lower die core dies, 4 middle dies, 5 forming upper dies, 1-1 rib web plates, 1-2 rib edge strips, 1-3 reinforcing rib inner molded surfaces, 1-1-1 reinforcing ribs, 1-1-2 lightening holes, 1-2-1 edge strip sinking, 2-1 first grooves, 3-1 lower die core die outer molded surfaces, 3-1-1 second grooves, 4-1 middle die inner molded surfaces, 4-2 middle die outer molded surfaces and 5-1 forming upper die inner molded surfaces.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "left", "right", "top", "bottom", and the like, indicate orientations or positional relationships for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. Moreover, the terms "first," "second," and the like are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or described herein.
Example 1
As shown in fig. 1-7, a composite material rib forming mold for reinforcing a rib between beams is characterized in that the forming mold is used for forming a composite material rib 1 for reinforcing a rib between beams, as shown in fig. 1, the composite material rib 1 for reinforcing a rib between beams is composed of a rib web 1-1 and a rib rim 1-2, a reinforcing rib 1-1-1 is arranged on the rib web 1-1, a plurality of lightening holes 1-1-2 (lightening holes are used for lightening the structural weight of the rib, lightening holes 1-1-2 are arranged between two adjacent reinforcing ribs 1-1-1) are also arranged on the rib web 1-1, and two ends of the rib rim 1-2 are provided with rim depressions 1-2-1 for matching with rims of spars;
as shown in fig. 2, the molding die includes: a forming lower die 2, a lower die core die 3, a plurality of intermediate dies 4 and a forming upper die 5; the lower forming die 2, the lower die core die 3, the middle die 4 and the upper forming die 5 are sequentially stacked to form a combined forming die; the forming die is different from a common die and is a combined die;
the middle part of the lower forming die 2 is provided with a first groove 2-1 matched with the shape of the lower die core die 3; the outer molded surface 3-1 of the lower die core mold 3 is completely matched with the inner molded surface 1-3 of the reinforcing wing rib 1 between the composite material beams, and the outer molded surface 3-1 of the lower die core mold 3 is provided with a second groove 3-1-1 corresponding to the reinforcing rib 1-1-1; the inner profile 4-1 of the middle mould 4 is matched with the outer profile of the reinforcing rib 1, and the outer profile 4-2 of the middle mould 4 is matched with the inner profile 1-3 of the reinforcing rib 1 between the composite material beams; the inner molded surface 5-1 of the upper forming die 5 is matched with the outer molded surface of the reinforced wing rib 1 between the composite material beams.
Example 2
The method for forming the reinforced rib between the composite beams is characterized by adopting the forming die in the embodiment 1 for forming, and comprises the following steps:
s1, fixing the lower forming die 2 on a lower platform of a die press, fixing the upper forming die 5 on an upper platform of the die press, aligning the lower forming die 2 and the upper forming die 5, and simultaneously starting heating, wherein the temperature is determined according to resin;
s2, respectively paving and sticking prepreg on male dies of the lower die core die 3 and the middle die 4 to form a prefabricated body;
s3, sequentially placing the lower die core die 3 paved with the prefabricated body into a first groove 2-1 of a forming lower die 2, and placing the middle die 4 paved with the prefabricated body on the lower die core die 3;
s4, die assembly: closing the lower forming die 2 and the upper forming die 5, starting electromagnetic induction heating (heating time is 10-15 minutes), setting the pressurizing pressure to be 0.6-2.0MPa, and curing;
s5, cooling after solidification, and opening the mold;
s6, demolding: and (3) taking the cured composite material reinforcing rib 1 between beams down from the lower die core die 3 and the middle die 4.
The reinforced rib between the composite material beams manufactured by the invention solves the problem of strength and rigidity reduction caused by the opening of the web plate of the rib. The reinforced wing ribs between the composite material beams manufactured by the invention adopt a rapid curing prepreg compression molding process, and can realize mass production.
The combined forming die designed by the invention can be used for quickly forming the reinforced wing ribs between the composite material beams in batches, and the formed reinforced wing ribs between the composite material beams have smooth and flat inner and outer surfaces and high dimensional precision.
The lower die core die and the middle die can be replaced in turn quickly, so that the production efficiency is improved.
The above-mentioned preferred embodiments of the present invention are provided for illustration only and not for the purpose of limiting the invention. Obvious variations or modifications of the present invention are within the scope of the present invention.
Claims (9)
1. The forming die is used for forming the composite material inter-beam reinforcing rib (1), the composite material inter-beam reinforcing rib (1) is composed of a rib web (1-1) and rib flanges (1-2), a plurality of reinforcing ribs (1-1-1) are arranged on the rib web (1-1), a plurality of lightening holes (1-1-2) are further formed in the rib web (1-1), and the rib flanges (1-2) are provided with flange sinking (1-2-1) for being matched with flanges of a spar;
the forming die comprises: a forming lower die (2), a lower die core die (3), a plurality of intermediate dies (4) and a forming upper die (5); the lower forming die (2), the lower die core die (3), the plurality of middle dies (4) and the upper forming die (5) are sequentially stacked to form a combined forming die;
a first groove (2-1) matched with the shape of the lower die core mold (3) is formed in the middle of the lower forming die (2); the outer profile (3-1) of the lower die core die (3) is completely matched with the inner profile (1-3) of the reinforcing rib (1), and a second groove (3-1-1) corresponding to the reinforcing rib (1-1-1) is formed in the outer profile (3-1) of the lower die core die (3); the inner profile (4-1) of the middle mould (4) is matched with the outer profile of the reinforcing rib (1), and the outer profile (4-2) of the middle mould (4) is matched with the inner profile (1-3) of the reinforcing rib (1); and the inner profile (5-1) of the upper forming die (5) is matched with the outer profile of the reinforcing rib (1).
2. A mould for forming a reinforcing rib between beams of composite material according to claim 1, wherein said lightening holes (1-1-2) are provided in the rib web (1-1) between two adjacent reinforcing ribs (1-1-1).
3. A composite intercolumn reinforcing rib forming die as claimed in claim 1, wherein said bead undercut (1-2-1) is provided at the end of said rib bead (1-2).
4. The forming die for the reinforced rib between the composite material beams as claimed in claim 1, wherein the lower die core die (3) and the middle die (4) can be used as paving dies.
5. The forming die for the reinforcing rib between the composite material beams as claimed in claim 1, wherein the material of the forming die is die steel with high hardness.
6. A method of forming a reinforcing rib between beams of composite material, characterised in that the method uses a forming mould as claimed in any one of claims 1 to 5, the method including the steps of:
s1, fixing the lower forming die (2) on a lower platform of a die press, fixing the upper forming die (5) on an upper platform of the die press, aligning the lower forming die (2) with the upper forming die (5), and simultaneously starting heating;
s2, respectively paving and sticking prepreg on the lower die core die (3) and the middle die (4) to form a prefabricated body;
s3, sequentially placing the lower die core die (3) paved with the prefabricated body into a first groove (2-1) of a forming lower die (2), and placing the middle die (4) paved with the prefabricated body onto the lower die core die (3);
s4, die assembly: closing the lower forming die (2) and the upper forming die (5), and heating and pressurizing at the same time for curing;
s5, cooling after solidification, and opening the mold;
s6, demolding: and (3) taking the cured composite material inter-beam reinforcing wing rib (1) down from the lower die core die (3) and the middle die (4).
7. The method of claim 6, wherein the temperature of the heating in step S1 is determined by the resin.
8. The method of claim 6, wherein the pressure set in step S3 is 0.6-2.0MPa.
9. The method of claim 6, wherein the heating step S3 is electromagnetic induction heating for 10-15 min.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211494457.3A CN115742369A (en) | 2022-11-25 | 2022-11-25 | Forming die and forming method for reinforcing wing ribs between composite beams |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211494457.3A CN115742369A (en) | 2022-11-25 | 2022-11-25 | Forming die and forming method for reinforcing wing ribs between composite beams |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115742369A true CN115742369A (en) | 2023-03-07 |
Family
ID=85338429
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211494457.3A Pending CN115742369A (en) | 2022-11-25 | 2022-11-25 | Forming die and forming method for reinforcing wing ribs between composite beams |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115742369A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117508561A (en) * | 2023-12-04 | 2024-02-06 | 哈尔滨远驰航空装备有限公司 | Wing integral type shaping structure and forming die thereof |
-
2022
- 2022-11-25 CN CN202211494457.3A patent/CN115742369A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117508561A (en) * | 2023-12-04 | 2024-02-06 | 哈尔滨远驰航空装备有限公司 | Wing integral type shaping structure and forming die thereof |
| CN117508561B (en) * | 2023-12-04 | 2024-04-02 | 哈尔滨远驰航空装备有限公司 | Wing integral type shaping structure and forming die thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2128019B2 (en) | Modified blade stiffener and fabrication method therefor | |
| EP2851283B1 (en) | Method for manufacturing an aeronautical torsion box, torsion box and tool for manufacturing an aeronautical torsion box | |
| US9248586B2 (en) | Moulding tool for producing a composite material part using a flexible preform composed of a skin and profiled preforms firmly attached to said skin | |
| CN106553357A (en) | Hollow multi-cavity abnormal shape surface composite material complex structural member integral forming technique | |
| CN112238551B (en) | Multi-part integrated forming assembly die and forming assembly method for composite wing | |
| CN109435272B (en) | Variable-thickness composite material integral framework forming method and forming die thereof | |
| CN102105296A (en) | Device and method for the manufacture of three dimensional beam type elements in composite material | |
| CN104494166A (en) | Air bag forming method of composite material part with T-shaped reinforced web structure | |
| CN115742369A (en) | Forming die and forming method for reinforcing wing ribs between composite beams | |
| CN103832574A (en) | Optimized torsion box for an aircraft | |
| CN112388993A (en) | RTM (resin transfer molding) integral forming die and process for T-shaped composite material part with single-side reinforcement | |
| CN218593731U (en) | Porous I-shaped roof beam autoclave integrated into one piece frock | |
| CN110341211A (en) | A kind of compression molding die component of thermoplastic composite work shape reinforcement component | |
| CN210553131U (en) | Integral curing forming die for composite material longitudinal and transverse reinforced wall plate | |
| CN218948479U (en) | Integrated forming die for multi-cavity section bearing member | |
| CN111873448A (en) | Manufacturing method of composite material hub and product | |
| CN216443110U (en) | Forming die for composite material parts of variable-cross-section closed-angle cap type pipeline | |
| CN113246493B (en) | Forming die of closed-angle part and manufacturing and using method thereof | |
| CN115742370B (en) | Co-curing forming device and method for composite material I-shaped reinforced wall plate with variable-curve structure | |
| US20210069997A1 (en) | Method for manufacturing a composite material structure using a cocuring process | |
| CN115592858A (en) | Composite material beam forming die and integrated forming preparation method thereof | |
| CN114248473B (en) | Carbon fiber machine case shaping mold core structure | |
| CN219667535U (en) | Frame forming die with ribs | |
| CN218803402U (en) | Forming die applied to S-shaped variable cross-section structure air inlet channel | |
| CN110509569B (en) | Integral curing and forming tool for longitudinal and transverse reinforced wallboard made of composite material |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |