RU2623773C1 - Method of manufacturing panel with stiffening ribs of polymer composite materials - Google Patents

Method of manufacturing panel with stiffening ribs of polymer composite materials Download PDF

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Publication number
RU2623773C1
RU2623773C1 RU2016100992A RU2016100992A RU2623773C1 RU 2623773 C1 RU2623773 C1 RU 2623773C1 RU 2016100992 A RU2016100992 A RU 2016100992A RU 2016100992 A RU2016100992 A RU 2016100992A RU 2623773 C1 RU2623773 C1 RU 2623773C1
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RU
Russia
Prior art keywords
panel
vacuum
preform
stiffeners
binder
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RU2016100992A
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Russian (ru)
Inventor
Виктор Васильевич Авдеев
Алексей Валерьевич Кепман
Александр Владимирович БАБКИН
Екатерина Сергеевна Афанасьева
Анна Анатольевна Кузнецова
Эрдни Михайлович ЭРДНИ-ГОРЯЕВ
Марина Юрьевна Яблокова
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Публичное акционерное общество "Воронежское акционерное самолетостроительное Общество" (ПАО "ВАСО")
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Priority to RU2016100992A priority Critical patent/RU2623773C1/en
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Publication of RU2623773C1 publication Critical patent/RU2623773C1/en

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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/30Shaping 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
    • B29C70/36Shaping 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 impregnating by casting, e.g. vacuum casting

Abstract

FIELD: technological processes.
SUBSTANCE: forming a partially cured panel of polymeric composite materials (PCM) and forming at least two preforms in the form of an L-shaped profile by laying a layer of sacrificial tissue on the surface of the mould, and then several layers of carbonaceous material. The blanks are placed in pairs on the surface of the panel to form at least one preform of the stiffener in the form of a T-shaped profile. A layer of sacrificial fabric is laid on top of the panel with a stiffening preform placed on top of it, on which a distribution grid connected to the binder feed line is placed on top of the stiffener preform. In the depressions of the stiffener preform formed by the internal corners of the T-shaped profile, crimp elements are placed on top of the distribution grid. The resulting structure is covered with two layers of a vacuum film, with each layer forming an appropriate vacuum bag, connected by means of its vacuum line to its corresponding pump, and a vacuum is created in each of the vacuum bags formed. Afterwards, the thermosetting binder is fed and impregnated with the preform of the stiffener and then it is cured. The panel is formed on the basis of a fabric of carbon fiber impregnated with a thermosetting binder by the method of vacuum infusion and pre-determined according to a given regime.
EFFECT: simplification of the technology of manufacturing panels with stiffeners made of polymer composite materials and improving the quality of the resulting parts.
4 cl, 3 dwg

Description

The invention relates to the field of engineering, namely to the manufacture of parts with power elements from polymer composite materials (PCM), and can be used in aircraft, space technology, shipbuilding and automotive for the manufacture of shell casings in order to increase their strength characteristics and reduce weight designs.

A known method of manufacturing a panel with stiffeners from PCM (RF patent No. 2399491 dated December 9, 2008), which includes the manufacture of preforms of the ribs and sheathing, the placement and fixation of the preforms of the ribs on the preform of the sheathing, the installation of guide elements of the ribs and molding using vacuum films. Rib preforms are made in the form of channels on the mandrel. In this case, the rib preforms on the mandrels are laid on the sheathing preform so that the walls of the rib preforms are aligned with the sheathing preform, and the rib preforms with the shelves are aligned with each other. Then, the assembly is preheated, and after the formation of physical bonds between the assembly elements, the assembly is cooled and the mandrel is dismantled. A vacuum film is placed on the assembly, guide angles are laid on top of the film to the edges of the panel so that they are in direct contact with the preforms of the ribs, after which they are formed.

The disadvantage of the described method is that the fixing and molding of stiffeners on the panel are carried out in two stages, including the preliminary fixation of the ribs on the panel on the mandrels with their subsequent disassembly and placement after assembly of the vacuum package guide angles, which generally increases the complexity of the process and increases the manufacturing time the details. In addition, the method provides for the placement of the ribs on the panel only close to each other, which in the manufacture of large-sized products is impractical and will lead to increased labor intensity and weighting of the part.

A known method of manufacturing a panel with stiffeners from PCM (US 2010252180 A1, B29C 70/342, 10/07/2010), which is characterized by the fact that they form a panel of polymer composite materials, and also form stiffeners in the form of a T-shaped profile. In the method described above, stiffeners are preformed and in a prevented state they are placed on a panel laid out of the prepreg, which is then placed in an autoclave for curing.

The disadvantage of this method is that the prevented stiffeners must be firmly fixed on the panel and fixed, while during curing, a change in the geometric dimensions (thickness) will occur due to the subsidence of the panel during heating due to the transition of the binder into a fluid state. Because of this, leakage of the binder at the boundary of the stiffener and the panel can occur, which will degrade the mechanical characteristics of the part and its appearance.

The objective of the present invention is to overcome the above disadvantages while simplifying the molding technology and improving the quality of parts with stiffeners.

The technical result is achieved by a method of manufacturing a panel with stiffeners from polymer composite materials, characterized in that they form a partially cured panel of polymer composite materials and form at least two blanks in the form of an L-shaped profile by laying on the surface of the mold a layer of sacrificial fabric, and then several layers of carbon material, these blanks are placed in pairs on the surface of the panel with the formation of at least one rib preform and stiffnesses in the form of a T-shaped profile, on top of the panel with the stiffener preform placed on it, lay a layer of sacrificial fabric on which a distribution grid connected to the binder feed line is placed over the stiffener preform, and in the recesses of the preform of the stiffener formed by internal angles T -shaped profile, crimping elements are placed on top of the distribution grid, the resulting structure is covered with two layers of a vacuum film with the formation of each of the layers of the corresponding vacuum package Connected by its vacuum line to its respective pump and formed in each of the vacuum bag is evacuated, after which the supply is carried out the thermosetting binder and impregnation of the preform stiffeners thermosetting binder, and then curing it.

Crimp elements can be made of silicone. The flexibility of this material and ease of processing allows you to effectively place and fix stiffeners not only on flat surfaces in the manufacture of straight panels, but also on complex parts of various curvatures.

When placing blanks on the panel surface for stiffeners, a carbon tow is laid in the gap formed by the external corners of the connected L-shaped cross-section profiles and the panel, and the thermosetting binder is fed by forming a binder supply line from the top of the stiffener preform, and vacuum lines are placed around the perimeter of the panel. When forming a part by vacuum infusion, a carbon bundle will collect excess binder and eliminate the porosity defect that can occur when forming stiffeners on a prevented panel.

The panel can be formed on the basis of carbon fiber fabric, impregnated with a thermosetting binder by the method of vacuum infusion and prevented by a given mode.

The above features and advantages of the invention will be apparent from the following description of a preferred embodiment of a method for manufacturing a panel with stiffeners from PCM with reference to the accompanying drawings, in which the same positions are used to represent the same elements:

In FIG. 1 shows a diagram of a panel with PCM stiffeners during its manufacture in accordance with the present invention;

in FIG. 2 is a diagram of a blank in the form of an L-shaped profile during its manufacture in accordance with the present invention.

In FIG. 3 shows a diagram of a panel with PCM stiffeners in finished form in accordance with the present invention.

A method of manufacturing a panel with stiffeners from polymer composite materials is as follows.

A partially cured panel 1 is formed from PCM. Molding is carried out by the method of vacuum infusion by laying out carbon fiber cloth on a snap, assembling a vacuum bag, impregnating the bag with a thermosetting binder and preventing PCM according to a given technological mode.

At least two preforms 2 are also formed to further form stiffeners 3. As shown in FIG. 2, the preparation of blanks 2 for stiffeners 3 is carried out by laying and gluing to the surface of the mold 4 made of PVC profile, layer 5 of sacrificial fabric, and then several layers 6 of carbon material, giving them the shape of an L-shaped profile.

These blanks 2 are placed in pairs on the surface of the panel 1 with the formation of the preform 7 of the stiffener 3 in the form of a T-shaped profile (Fig. 1), i.e. the preform 7 of the stiffener 3 is two mirrored L-shaped profiles, the vertical shelves of which are adjacent to each other, and the horizontal are located on the panel 1. Preferably, the thickness of the L-shaped profiles is selected so that the thickness of the resulting stiffener 3 is approximately equal the thickness of the panel 1. For example, in the manufacture of panel 1 with a thickness of 6.5-7.0 mm, the thickness of the L-shaped profile with a size of 50 × 50 mm should be 3-3.5 mm, respectively, the stiffener 3 will have a thickness of 6-7 mm and overall times EASURES 50 × 100 mm.

The recommended distance between the stiffeners 3 when they are placed on the surface of the panel 1 from 150 to 350 mm. In the manufacture of large-sized parts, it is possible to increase the distance between the ribs 3 with a simultaneous increase in their height.

When placing on the surface of the panel 1 blanks 2 stiffeners in the gap 8, formed by the external corners of the connected profiles of the L-shaped cross section and panel 1, lay a carbon bundle that will collect excess binder and eliminate the porosity defect that may occur when forming stiffeners 3 on prevented panel 1.

On top of the panel 1 with the preform 7 placed on it, stiffeners lay a layer 9 of sacrificial fabric.

Then, on top of the preform 7 formed, the stiffeners 3 in the form of a T-shaped profile covered with a layer 9 of sacrificial fabric, place a distribution grid 10 connected to the binder supply line 11.

A binder supply line 11 connected to the distribution grid 10 is formed on top of the preforms 7 of the stiffeners 3. To improve the supply of the binder and improve the quality of impregnation of the stiffeners, a spiral polyethylene tube 12 is sewn into the distribution grid 10 with a cut along the entire length of the stiffener. With this embodiment, the binder supply line 11, if there are protruding elements on the panel 1, can be circumvented by breaking the line to an obstacle and continuing behind it, while the distribution grid 10 will be placed along the entire length of the impregnation line.

In the recesses of the preform 7, the stiffening ribs 3 formed by the internal corners of the T-shaped profile, crimping elements 13 are placed over the distribution grid 10, which serve as guides and fixing the preform 7 elements. The crimping elements 13 are made of silicone by mixing the components of the organosilicon compound, pouring it into a mold and then curing with the formation of bars, from which blanks with the desired geometry are cut depending on the preform 7 formed by the stiffener 3 and the panel configuration 1. The small silicone selected for the manufacture of blanks hardness (Shore hardness 12-15A) to ensure its flexibility when fixing stiffeners 3. Silicone, thanks to its flexibility and ease of processing, allows to place and fix stiffeners 3 not only on flat surfaces in the manufacture of straight panels 1, but also on complex parts of different curvatures.

The resulting structure, consisting of a panel 1, on which a preform 7 of stiffening ribs 3 in the form of a T-shaped profile is placed, covered with a layer 9 of sacrificial fabric and a distribution grid 10, with crimping elements 13 located in the recesses of the T-shaped profile, is covered with a layer of vacuum film 14 and fix it with a sealing rope with the formation of a vacuum package connected by means of a vacuum line 15 to the pump 16.

Then, the vacuum film layer 14 is covered with another layer of the vacuum film 17 to form a corresponding vacuum package connected via its vacuum line 18 to the corresponding pump 19.

In this case, both vacuum lines 15 and 18 are placed around the perimeter of the panel 1.

Vacuum is created in each of the vacuum bags formed by means of pumps 16 and 19.

On the supply line 18 of the binder, the thermosetting binder is fed into the distribution grid 10 and the preform 7 of the stiffener 3 is impregnated with a thermosetting binder. In this case, the binder also enters the gap 8, formed by the external corners of the connected profiles of the L-shaped cross section and panel 1, and impregnates the carbon bundle laid therein. Exit of excess binder will be carried out along the perimeter of panel 1, and since panel 1 has already been prevented, it will not absorb excess binder, which will go along the distribution grid 10 into the vacuum outlet line.

Then carry out the curing of the ribs 3.

Thus, stiffening ribs 3 are formed on the panel 1 by vacuum infusion by impregnating the preforms 7 of the stiffening ribs 3 on the surface of the panel 1 with a thermosetting binder and curing them according to a given technological mode.

The result is a part in the form of a panel 1 with stiffeners 3.

Thus, the present invention will simplify the manufacture of parts in the form of panels with stiffeners and improve the quality of the parts.

The embodiment described above should in all aspects be considered merely illustrative and not limiting. Therefore, other embodiments of the present invention and implementation examples that do not go beyond the essential features described herein may be used.

Claims (12)

1. A method of manufacturing a panel with stiffeners from polymer composite materials, characterized in that
- form a partially cured panel of polymer composite materials and
- form at least two blanks in the form of an L-shaped profile by laying on the surface of the form layer of sacrificial tissue, and then several layers of carbon material,
- these blanks are placed in pairs on the surface of the panel with the formation of at least one preform stiffeners in the form of a T-shaped profile,
- a layer of sacrificial fabric is laid on top of the panel with the preform placed on it;
- on which on top of the preform stiffeners place a distribution grid connected to the supply line of the binder, and
- in the recesses of the preform stiffeners formed by the internal corners of the T-shaped profile, crimp elements are placed over the distribution grid,
- the resulting structure is covered with two layers of a vacuum film with each of the layers forming a corresponding vacuum bag connected by means of its vacuum line to its corresponding pump, and a vacuum is created in each of the formed vacuum bags,
- then feed the thermoset binder and impregnate the preform of the stiffener with it, and then cure it.
2. The method according to claim 1, wherein the crimp elements are made of silicone.
3. The method according to p. 1, in which when placing blanks on the panel surface for stiffeners in the gap formed by the external corners of the connected L-shaped cross-section profiles and the panel, a carbon tow is laid, while the thermoset binder is fed by forming a binder feed line stiffeners are preformed on the top, and vacuum lines are placed around the perimeter of the panel.
4. The method according to p. 1, wherein the panel is formed on the basis of carbon fiber fabric, impregnated with a thermosetting binder by the method of vacuum infusion and prevented by a given mode.
RU2016100992A 2016-01-14 2016-01-14 Method of manufacturing panel with stiffening ribs of polymer composite materials RU2623773C1 (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2719527C1 (en) * 2019-09-02 2020-04-21 Федеральное государственное унитарное предприятие "Крыловский государственный научный центр" (ФГУП Крыловский государственный научный центр") Method for making beam of u-shaped profile of ship hull from polymer composite materials

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19832441C1 (en) * 1998-07-18 2000-01-05 Daimler Chrysler Aerospace Stringer-reinforced shell production with double curvature using fibrous composite materials, without risk of warping
RU2399491C2 (en) * 2008-12-09 2010-09-20 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Method for manufacturing panel with stiffening ribs of polymer composite materials
US20100252180A1 (en) * 2006-07-28 2010-10-07 Airbus Espana, S.L. Process for the manufacturing of parts made of composite materials with two curing cycles
RU2565177C1 (en) * 2014-09-25 2015-10-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Film-type epoxy binder

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19832441C1 (en) * 1998-07-18 2000-01-05 Daimler Chrysler Aerospace Stringer-reinforced shell production with double curvature using fibrous composite materials, without risk of warping
US20100252180A1 (en) * 2006-07-28 2010-10-07 Airbus Espana, S.L. Process for the manufacturing of parts made of composite materials with two curing cycles
RU2399491C2 (en) * 2008-12-09 2010-09-20 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Method for manufacturing panel with stiffening ribs of polymer composite materials
RU2565177C1 (en) * 2014-09-25 2015-10-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Film-type epoxy binder

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2719527C1 (en) * 2019-09-02 2020-04-21 Федеральное государственное унитарное предприятие "Крыловский государственный научный центр" (ФГУП Крыловский государственный научный центр") Method for making beam of u-shaped profile of ship hull from polymer composite materials

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