CN113561520A - Method for manufacturing airplane composite stringer - Google Patents
Method for manufacturing airplane composite stringer Download PDFInfo
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- CN113561520A CN113561520A CN202010358890.9A CN202010358890A CN113561520A CN 113561520 A CN113561520 A CN 113561520A CN 202010358890 A CN202010358890 A CN 202010358890A CN 113561520 A CN113561520 A CN 113561520A
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- 239000002131 composite material Substances 0.000 title claims abstract description 96
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 48
- 238000000034 method Methods 0.000 title claims abstract description 20
- 239000000463 material Substances 0.000 claims abstract description 131
- 241001589086 Bellapiscis medius Species 0.000 claims abstract description 21
- 238000013461 design Methods 0.000 claims abstract description 15
- 238000010438 heat treatment Methods 0.000 claims abstract description 3
- 238000003856 thermoforming Methods 0.000 claims abstract 2
- 239000003292 glue Substances 0.000 claims description 22
- 230000000903 blocking effect Effects 0.000 claims description 18
- 239000011324 bead Substances 0.000 claims description 11
- 238000002955 isolation Methods 0.000 claims description 7
- 238000007789 sealing Methods 0.000 claims description 6
- 238000001514 detection method Methods 0.000 claims description 5
- 238000000465 moulding Methods 0.000 description 15
- 238000005520 cutting process Methods 0.000 description 10
- 239000004744 fabric Substances 0.000 description 10
- 238000009434 installation Methods 0.000 description 7
- 238000012546 transfer Methods 0.000 description 7
- 238000003754 machining Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000007493 shaping process Methods 0.000 description 3
- 238000010030 laminating Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000003892 spreading Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
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- 238000005452 bending Methods 0.000 description 1
- 230000000994 depressogenic effect Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
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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
-
- 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
- B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
-
- 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
-
- 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
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a method for manufacturing an airplane composite stringer, which belongs to the technical field of airplane manufacturing, wherein the airplane composite stringer comprises twirling strips, a plane material layer and two main body parts, and the method for manufacturing the airplane composite stringer comprises the following steps: s1, preparing a flat board material layer of the main body part according to the design size of the main body part; s2, transferring the flat plate layer to a main body part forming core mold tool, wherein the main body part forming core mold tool and the flat plate layer are arranged in a one-to-one correspondence manner; s3, heating the flat board material layer and thermoforming the flat board material layer into a main body part; s4, combining the main body part on the main body part forming core mould tool, placing a twister strip and a plane material layer according to preset positions, and placing a composite material cover plate on the plane material layer, wherein the sizes of the twister strip and the plane material layer are designed; and S5, bagging and curing to form the airplane composite stringer. The invention can improve the manufacturing precision and the manufacturing speed of the composite stringer of the airplane and reduce the manufacturing cost.
Description
Technical Field
The invention relates to the technical field of aircraft manufacturing, in particular to a method for manufacturing a composite stringer of an aircraft.
Background
The stringer is one of the components of the aircraft, and its good design efficiency and design quality are one of the bases for ensuring the overall efficiency and performance of the aircraft design and manufacture.
In the prior art, aircraft stringers are typically composite materials. Aircraft composite stringers are generally manufactured by the following method: and (4) reserving allowance at the edge of the part for molding, and then cutting off the allowance at the edge by adopting mechanical processing. Namely, the size of the airplane composite stringer which is formed by preliminary processing is slightly larger than the design size, and then the margin of the edge is cut off to finish the processing of the airplane composite stringer.
The processing method has the following disadvantages:
(1) when the margin of the edge is cut off by machining, the edge of the airplane composite material stringer is easily layered or split, so that the airplane composite material stringer is scrapped or needs to be reworked, and the manufacturing cost is increased;
(2) machining is time and labor consuming, resulting in increased manufacturing time and costs.
Disclosure of Invention
The invention aims to provide a method for manufacturing an aircraft composite stringer, which can improve the manufacturing precision and the manufacturing speed of the aircraft composite stringer and reduce the manufacturing cost.
As the conception, the technical scheme adopted by the invention is as follows:
a method for manufacturing an aircraft composite stringer, the aircraft composite stringer comprising a twister strip, a planar material layer and two main body portions,
the method of making the aircraft composite stringer includes the steps of:
s1, preparing a flat material layer of the main body part according to the design size of the main body part;
s2, transferring the flat plate material layer to a main body part forming core mold tool, wherein the main body part forming core mold tool and the flat plate material layer are arranged in a one-to-one correspondence manner;
s3, heating the flat board material layer and enabling the flat board material layer to be thermoformed into the main body part;
s4, combining the main body part on the main body part forming core mold tool, placing the twister strip and the plane material layer according to preset positions, and placing a composite cover plate on the plane material layer, wherein the sizes of the twister strip and the plane material layer are designed;
s5, bagging and curing to form the airplane composite stringer.
Optionally, in step S4, the two body section forming core mold tooling are placed in the designed position such that the two body sections are combined in their position within the aircraft composite stringer.
Optionally, the aircraft composite stringer is a T-shaped stringer, the main body portion is "L" shaped, the main body portion includes a T-shaped stringer web portion and a T-shaped stringer marginal strip portion, after the aircraft composite stringer is formed, the T-shaped stringer web portions of the two main body portions are attached to each other, and the T-shaped stringer marginal strip portions extend in directions away from each other.
Optionally, the aircraft combined material stringer is the I shape stringer, the main part is "C" type, the main part includes the web portion, the both ends of web portion all are equipped with the perpendicular to web portion and syntropy extension's fringe portion treat after the shaping of aircraft combined material stringer, two the main part the web portion laminating sets up, is "worker" style of calligraphy.
Optionally, the main body part forming core mold tool is provided with a flat plate material layer mounting recess.
Optionally, in the step S1, the flat board material layer is formed by cutting after the composite material is laid.
Optionally, a glue blocking groove is formed in the main body part molding core die tool.
Optionally, in the step S2, an auxiliary tool is used to transfer the flat material layer to the main body part forming core mold tool.
Alternatively, in step S2, after the flat sheet material layer is transferred to the main body part molding core mold tool, a pre-formed cover sheet is used to press the flat sheet material layer.
Optionally, the step S5 includes:
s51, sequentially arranging an isolation film, an air-permeable felt, a vacuum bag and a curing sealing strip on the main body part molding core mold tool;
and S52, after vacuumizing and leak detection are qualified, putting the main body part molding core die tool into an autoclave for curing molding.
The method for manufacturing the airplane composite stringer provided by the invention has the following advantages:
the size of the flat material layer is set to be the design size of the main body part, and the flat material layer is processed into the main body part on the main body part forming core die tool, so that the main body part can be formed at one time, the edge allowance does not need to be cut off, and the manufacturing speed and the manufacturing precision are improved.
Meanwhile, when the twister strips and the fabric layer are placed, the main body part is arranged on the main body part forming core die tool, the main body part does not need to be transferred, and the manufacturing cost and the manufacturing time are further saved.
When the twister strips and the fabric layer are placed, the twister strips and the fabric layer are designed according to the design sizes of the twister strips and the fabric layer, so that the airplane composite stringer is directly formed after bagging, curing and forming, other operations are not needed, and the manufacturing speed is increased.
Drawings
FIG. 1 is a flow chart of a method of manufacturing an aircraft composite stringer according to an embodiment of the present invention;
FIG. 2 is a schematic cross-sectional view of a T-shaped stringer according to an embodiment of the present invention;
FIG. 3 is a schematic view of a flat sheet of material being placed on a body portion forming core mold tooling in accordance with an embodiment of the present invention;
FIG. 4 is a schematic illustration of a flat sheet material layer as provided by an embodiment of the present invention in forming a body portion on a body portion forming core mold tool;
fig. 5 is a schematic view of two main body part forming core mold tooling according to a first embodiment of the present invention, which are placed at a designed position;
FIG. 6 is a schematic illustration of an aircraft composite stringer as it is cured and formed in accordance with an embodiment of the present invention;
FIG. 7 is a schematic cross-sectional view of an I-shaped stringer provided in accordance with a second embodiment of the present invention;
FIG. 8 is a schematic view of a flat sheet material layer provided in accordance with a second embodiment of the present invention being placed on a body portion forming core mold;
FIG. 9 is a schematic view of a sheet material layer provided in a second embodiment of the present invention when forming a main body portion on a main body portion forming core mold tool;
fig. 10 is a schematic view of two main body part forming core mold tooling provided by the second embodiment of the present invention when they are placed according to the designed position;
FIG. 11 is a schematic view of an aircraft composite stringer as provided by a second embodiment of the present invention, as cured.
In the figure:
1. an aircraft composite stringer; 11. a main body portion; 111. a T-shaped stringer web; 112. a T-shaped stringer tape portion; 113. a T-shaped stringer bending portion; 114. a web portion; 115. a rim portion; 116. an arc-shaped portion; 12. twisting the strips; 13. a plane material layer;
2. a flat bed material layer;
3. a main body part forming core mould tool; 31. the flat material layer is provided with a concave part; 32. a T-shaped stringer web forming section; 33. a first positioning portion; 34. a first glue blocking groove; 35. a second glue blocking groove; 36. a third glue blocking groove; 37. a bead forming section; 38. a second positioning portion; 39. a fourth glue blocking groove;
4. an isolation film; 5. an air-permeable felt; 6. vacuum bag;
7. pre-forming a cover plate;
8. a composite cover plate;
9. curing the sealing strip;
10. and (5) a flat plate tool.
Detailed Description
In order to make the technical problems solved, the technical solutions adopted and the technical effects achieved by the present invention clearer, the technical solutions of the present invention are further described below by way of specific embodiments with reference to the accompanying drawings. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some but not all of the elements associated with the present invention are shown in the drawings.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Wherein the terms "first position" and "second position" are two different positions.
In the description of the present invention, it should be noted that unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection or a removable connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example one
Referring to fig. 1-6, the present embodiment provides a method of manufacturing an aircraft composite stringer that is capable of directly manufacturing an aircraft composite stringer according to the design dimensions of the aircraft composite stringer without the need for machining to remove edge margins.
Referring to FIG. 2, in particular, in this embodiment, an aircraft composite stringer 1 includes a twill strip 12, a flat bed layer 13, and two main body portions 11.
The method of making an aircraft composite stringer includes the steps of:
s1, preparing the flat sheet material layer 2 of the main body part 11 according to the design size of the main body part 11.
In step S1, the flat material layer 2 is a component of the unfolded main body 11, and the flat material layer 2 can be directly formed into the main body 11 without cutting the margin, thereby avoiding scrapping or rework of the composite stringer of the airplane when cutting the margin. Namely: the size of the flat sheet material layer 2 is the net size of the main body portion 11.
Specifically, in step S1, the flat sheet material layer 2 is formed by laying and cutting the composite material. Optionally, the composite material is laid manually or automatically.
And S2, transferring the flat plate material layer 2 to a main body part forming core mold tool 3, wherein the main body part forming core mold tool 3 and the flat plate material layer 2 are arranged in a one-to-one correspondence mode.
Specifically, in step S2, two main body portion forming core mold tools 3 are provided, and the main body portion forming core mold tools 3 are provided in one-to-one correspondence with the flat plate material layer 2.
Preferably, in step S2, the auxiliary tool is used to transfer the flat sheet layer 2 to the main body part forming core mold tool 3, so as to prevent the flat sheet layer 2 from wrinkling during the transfer process.
Preferably, in step S2, after the flat board material layer 2 is transferred onto the main body part forming core mold tooling 3, the preformed cover plate 7 is used to press the flat board material layer 2 to prevent the flat board material layer 2 from shifting in the subsequent forming process.
Specifically, the main body part molding core mold tooling 3 is specifically designed according to the shape of the airplane composite stringer.
S3, the flat board material layer 2 is heated and the flat board material layer 2 is thermoformed into the main body portion 11.
Specifically, the flat material layer 2 is heated and then the flat material layer 2 is bent, so that the flat material layer 2 is molded into the main body portion 11.
S4, combining the main body part 11 on the main body part forming core mold tool 3, placing the twister strip 12 and the plane material layer 13 according to the preset position, and placing the composite material cover plate 8 on the plane material layer 13, wherein the sizes of the twister strip 12 and the plane material layer 13 are designed.
Specifically, in step S4, the two body portion forming core mold tooling 3 are placed in the designed position so that the two body portions 11 are combined in their positions within the aircraft composite stringer 1. At this time, the main body part forming core mold tooling 3 can position the two main body parts 11, and a special positioning tooling does not need to be arranged.
And S5, bagging and curing to form the airplane composite stringer 1.
Specifically, step S5 includes:
s51, sequentially arranging an isolation film 4, an air felt 5, a vacuum bag 6 and a curing sealing strip 9 on the main body part forming core mold tool 3;
and S52, after vacuumizing and leak detection are qualified, putting the main body part forming core mold tool 3 into an autoclave for curing and forming.
Referring to FIGS. 2-6, in this embodiment, a T-shaped stringer is used as an example to describe a method of manufacturing an aircraft composite stringer 1.
Referring to fig. 2, the cross section of the T-shaped stringer is "T" shaped, the main body 11 is "L" shaped, the main body 11 comprises T-shaped stringer web portions 111 and T-shaped stringer bead portions 112, after the aircraft composite stringer 1 is formed, the T-shaped stringer web portions 111 of the two main body portions 11 are attached to each other, and the two T-shaped stringer bead portions 112 extend in a direction away from each other. The main body 11 further includes a T-shaped stringer folded portion 113, and one end of the T-shaped stringer folded portion 113 is connected to the T-shaped stringer web 111 and the other end is connected to the T-shaped stringer edge strip portion 112. The aircraft composite stringer 1 includes a twill strip 12, the twill strip 12 being disposed between two T-shaped stringer bends 113.
The T-shaped stringer comprises a planar material layer 13, the planar material layer 13 is laid on two T-shaped stringer marginal strip portions 112, and the twister strip 12 is positioned in a gap formed by the planar material layer 13 and the two main body portions 11.
Specifically, in this embodiment, the method for manufacturing the T-shaped stringer includes the following steps:
s1, spreading the flat material layer 2 shown in fig. 3 according to the design size of the main body 11 of the T-shaped stringer, and cutting the flat material layer 2 after manually laying or automatically laying.
And S2, transferring the flat plate material layer 2 to the main body part forming core die tooling 3 by adopting an auxiliary tooling, and pressing the flat plate material layer 2 by using the pre-forming cover plate 7. Alternatively, the auxiliary tool may be a plurality of robots or other devices that cooperate with each other, as long as the transfer of the flat material layer 2 can be achieved, which is not limited herein.
Specifically, in this step, two main body part forming core mold tools 3 are provided, the main body part forming core mold tools 3 are arranged in one-to-one correspondence with the flat plate material layers 2, and one flat plate material layer 2 is placed on each main body part forming core mold tool 3.
S3, the flat board material layer 2 is heated and the flat board material layer 2 is thermoformed into the main body portion 11. Specifically, referring to fig. 4, the flat plate material layer 2 is bent at this time to form the main body portion 11.
S4, combining the main body part 11 on the main body part forming core mold tool 3, placing the twister strip 12 and the plane material layer 13 according to the preset position, and placing the composite material cover plate 8 on the plane material layer 13, wherein the sizes of the twister strip 12 and the plane material layer 13 are designed.
Referring to FIG. 5, specifically, in step 4, the two body portions 11 of the T-stringer have been formed, and the position of the two body portion forming mandrel tooling 3 is adjusted so that the two body portions 11 are combined according to their position within the aircraft composite stringer 1. That is, after the positions of the two body section forming core mold tools 3 are adjusted, the T-shaped stringer web portions 111 of the two body sections 11 are arranged in a manner of being attached to each other, and are formed in a "T" shape.
Specifically, in this step, before the twigs 12 and the fabric layer 13 are placed, the corresponding twigs 12 and the fabric layer 13 are cut according to the designed sizes of the twigs 12 and the fabric layer 13.
Referring to fig. 5, after the flat material layer 13 is placed, a cover sheet 8 of composite material is placed on the flat material layer 13.
S5, see FIG. 6, bagging and curing to form the aircraft composite stringer 1.
Specifically, step S5 includes:
s51, sequentially arranging an isolation film 4, an air felt 5, a vacuum bag 6 and a curing sealing strip 9 on the main body part forming core mold tool 3; specifically, in step S51, after the main body part forming core mold tooling 3 is placed on the flat tooling 10, the isolation film 4, the airfelt 5, the vacuum bag 6 and the curing seal strip 9 are set again;
and S52, after vacuumizing and leak detection are qualified, putting the main body part forming core mold tool 3 into an autoclave for curing and forming.
Preferably, in this embodiment, the main body part forming core mold tooling 3 is provided with a flat plate material layer mounting recess 31 and a glue blocking groove.
Referring to fig. 3 to 6, in the present embodiment, the main body part forming core mold tooling 3 is provided with the flat material layer installation recess 31, and the size of the flat material layer installation recess 31 is the same as that of the T-shaped stringer tape part 112; the main body part forming core mold tooling 3 is further provided with a T-shaped long truss web part forming part 32, the T-shaped long truss web part forming part 32 is perpendicular to the flat material layer mounting concave part 31, and the joint of the T-shaped long truss web part forming part and the flat material layer mounting concave part 31 is provided with a round angle. After the main body 11 is formed on the flat bed layer 2, the T-shaped stringer edge strip 112 is attached to the flat bed layer installation recess 31, the T-shaped stringer web 111 is attached to the T-shaped stringer web forming section 32, and the T-shaped stringer bent section 113 can be smoothly formed by providing a fillet. Referring to fig. 5, one of the two body portion forming core mold tools 3 fitted to each other is provided with a first positioning portion 33, and the width of the first positioning portion 33 is twice the thickness of the T-shaped stringer web portion 111.
Set up first fender glue groove 34 and second fender glue groove 35 on the main part shaping mandrel frock 3 that is equipped with first locating part 33, first fender glue groove 34 sets up adjacent with first locating part 33, and second fender glue groove 35 sets up with dull and stereotyped material layer installation depressed part 31 interval. The other main body part forming core mold tooling 3 is provided with a third glue blocking groove 36. The composite cover plate 8 can cover the second glue blocking groove 35 and the third glue blocking groove 36 at the same time.
Preferably, in step S3, after the positions of the two body portion molding core mold tools 3 are adjusted, the weather strips are placed in the first glue blocking groove 34, the second glue blocking groove 35, and the third glue blocking groove 36.
The flat material layer 2 is placed in the flat material layer installation concave part 31 to enable the T-shaped stringer edge strip part 112 to be formed, the glue blocking groove and the composite material cover plate 8 can well avoid the edge effect of parts, the edge quality of the parts is good, the parts can be used after deburring, and machining operation is not needed.
In this embodiment, the specific structure of the main body part forming core mold tooling 3 can be designed by a designer, and the method for manufacturing the aircraft composite stringer provided in this embodiment is not limited to this.
Example two
The present embodiments provide a method of manufacturing an aircraft composite stringer.
Referring to fig. 7-11, in particular, in this embodiment, an aircraft composite stringer 1 includes a twill strip 12, a planar bed 13, and two body portions 11.
The method of making an aircraft composite stringer includes the steps of:
s1, preparing the flat sheet material layer 2 of the main body part 11 according to the design size of the main body part 11.
In step S1, the flat material layer 2 is a component of the unfolded main body 11, and the flat material layer 2 can be directly formed into the main body 11 without cutting the margin, thereby avoiding scrapping or rework of the composite stringer of the airplane when cutting the margin. Namely: the size of the flat sheet material layer 2 is the net size of the main body portion 11.
Specifically, in step S1, the flat sheet material layer 2 is formed by laying and cutting the composite material. Optionally, the composite material is laid manually or automatically.
And S2, transferring the flat plate material layer 2 to a main body part forming core mold tool 3, wherein the main body part forming core mold tool 3 and the flat plate material layer 2 are arranged in a one-to-one correspondence mode.
Specifically, in step S2, two main body portion forming core mold tools 3 are provided, and the main body portion forming core mold tools 3 are provided in one-to-one correspondence with the flat plate material layer 2.
Preferably, in step S2, the auxiliary tool is used to transfer the flat sheet layer 2 to the main body part forming core mold tool 3, so as to prevent the flat sheet layer 2 from wrinkling during the transfer process.
Preferably, in step S2, after the flat board material layer 2 is transferred onto the main body part forming core mold tooling 3, the preformed cover plate 7 is used to press the flat board material layer 2 to prevent the flat board material layer 2 from shifting in the subsequent forming process.
Specifically, the main body part molding core mold tooling 3 is specifically designed according to the shape of the airplane composite stringer.
S3, the flat board material layer 2 is heated and the flat board material layer 2 is thermoformed into the main body portion 11.
Specifically, the flat material layer 2 is heated and then the flat material layer 2 is bent, so that the flat material layer 2 is molded into the main body portion 11.
S4, combining the main body part 11 on the main body part forming core mold tool 3, placing the twister strip 12 and the plane material layer 13 according to the preset position, and placing the composite material cover plate 8 on the plane material layer 13, wherein the sizes of the twister strip 12 and the plane material layer 13 are designed.
Specifically, in step S4, the two body portion forming core mold tooling 3 are placed in the designed position so that the two body portions 11 are combined in their positions within the aircraft composite stringer 1.
And S5, bagging and curing to form the airplane composite stringer 1.
Specifically, step S5 includes:
s51, sequentially arranging an isolation film 4, an air felt 5, a vacuum bag 6 and a curing sealing strip 9 on the main body part forming core mold tool 3;
and S52, after vacuumizing and leak detection are qualified, putting the main body part forming core mold tool 3 into an autoclave for curing and forming.
In this embodiment, a method for manufacturing an aircraft composite stringer 1 is described by taking an i-shaped stringer as an example.
In this embodiment, the i-shaped stringer includes two main parts 11, and main part 11 is "C" type, and main part 11 includes web 114, and the both ends of web 114 all are equipped with the border portion 115 of perpendicular to web 114, treat aircraft combined material stringer 1 shaping back, and the web 114 laminating setting of two main parts 11 is "worker" style of calligraphy.
The aircraft composite stringer 1 comprises two twill strips 12 and two flat material layers 13.
Each connecting portion between the rim portion 115 and the web portion 114 is provided with an arc portion 116, and after the web portions 114 of the two main body portions 11 are attached, a gap is formed between two adjacent arc portions 116, and the twill 12 is placed in the gap. The flat bed of material 13 is laid on two rim portions 115 lying on the same plane.
Specifically, in this embodiment, the manufacturing method of the i-shaped stringer includes the following steps:
s1, spreading the flat material layer 2 shown in fig. 8 according to the design size of the main body 111 of the i-shaped stringer, and cutting the flat material layer 2 after manually laying or automatically laying.
And S2, transferring the flat plate material layer 2 to the main body part forming core die tooling 3 by adopting an auxiliary tooling. Alternatively, the auxiliary tool may be a plurality of robots or other devices that cooperate with each other, as long as the transfer of the flat material layer 2 can be achieved, which is not limited herein.
Specifically, in this step, two main body part forming core mold tools 3 are provided, the main body part forming core mold tools 3 are arranged in one-to-one correspondence with the flat plate material layers 2, and one flat plate material layer 2 is placed on each main body part forming core mold tool 3.
S3, the flat board material layer 2 is heated and the flat board material layer 2 is thermoformed into the main body portion 11. Specifically, referring to fig. 9, the flat plate material layer 2 is bent at this time to form the main body portion 11.
S4, combining the main body part 11 on the main body part forming core mold tool 3, placing the twister strip 12 and the plane material layer 13 according to the preset position, and placing the composite material cover plate 8 on the plane material layer 13, wherein the sizes of the twister strip 12 and the plane material layer 13 are designed.
Referring to FIG. 10, specifically, in step 4, the two body portions 11 of the I-shaped stringer have been formed, and the position of the two body portion forming mandrel tooling 3 is adjusted so that the two body portions 11 are combined according to their position within the aircraft composite stringer 1. That is, after the positions of the two body section forming core mold tools 3 are adjusted, the web portions 114 of the two body sections 11 are attached to each other, and are in an "i" shape.
Specifically, in this step, before the twigs 12 and the fabric layer 13 are placed, the corresponding twigs 12 and the fabric layer 13 are cut according to the designed sizes of the twigs 12 and the fabric layer 13.
Referring to fig. 10, in this step, after the flat material layer 13 is placed, a cover plate 8 made of composite material is placed on the flat material layer 13. Specifically, each of the two surface material layers 13 is covered with a cover plate 8 made of composite material.
And S5, bagging and curing to form the airplane composite stringer 1.
Preferably, in this embodiment, the main body part forming core mold tooling 3 is provided with a flat plate material layer mounting recess 31 and a glue blocking groove.
Referring to fig. 8 and 9, in the present embodiment, the main body portion forming core mold tooling 3 is provided with the flat plate material layer mounting recessed portion 31, and the size of the flat plate material layer mounting recessed portion 31 is the same as that of the web portion 114; the main body part forming core mold tooling 3 is further provided with a rim strip forming part 37, the rim strip forming part 37 is perpendicular to the flat plate layer mounting recess part 31, and two ends of the flat plate layer mounting recess part 31 are respectively provided with a rim strip forming part 37. The joint of the bead molding portion 37 and the flat sheet layer installation recess portion 31 is provided with a round corner. When the flat material layer 2 is formed into the main body portion 11, the web portion 114 is attached to the flat material layer mounting recess portion 31, and the bead portion 115 is attached to the bead molding portion 37. The rounded corners enable the arc-shaped portion 116 to be smoothly formed.
Referring to fig. 9 and 10, two of the body portion molding core mold tooling 3 are each provided with one second positioning portion 38, and after the bead portion 115 is placed in abutment with the bead molding portion 37, the end portion of the bead portion 115 abuts against the second positioning portion 38. The sum of the thickness of the rim portion 115 and the thickness of the facestock layer 13 is equal to the thickness of the second locator portion 38.
Two of the main body part molding core mold tools 3 are respectively provided with a fourth glue blocking groove 39. When the composite cover plate 8 is covered on the plane material layer 13, the composite cover plate 8 can cover the two fourth glue blocking grooves 39 on the same side of the two main body part forming core mold tools 3.
Preferably, in this embodiment, in step S3, after the positions of the two body portion molding core die assemblies 3 are adjusted, a weather strip is placed in each fourth weather strip groove 39.
In this embodiment, the flat material layer 2 is placed in the flat material layer installation recess 31 to enable the web portion 114 to be formed, and the glue blocking groove and the composite material cover plate 8 can well avoid the edge effect of the part, so that the edge quality of the part is good, the part can be used after deburring, and machining operation is not needed.
In this embodiment, the specific structure of the main body part forming core mold tooling 3 can be designed by a designer, and the method for manufacturing the aircraft composite stringer provided in this embodiment is not limited to this.
The foregoing embodiments are merely illustrative of the principles and features of this invention, which is not limited to the above-described embodiments, but rather is susceptible to various changes and modifications without departing from the spirit and scope of the invention, which changes and modifications are within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. A method for manufacturing an aircraft composite stringer, the aircraft composite stringer (1) comprising a twister strip (12), a planar material layer (13) and two main body portions (11),
the method for manufacturing the composite stringer of the airplane is characterized by comprising the following steps of:
s1, preparing the flat plate material layer (2) of the main body part (11) according to the design size of the main body part (11);
s2, transferring the flat plate material layer (2) to a main body part forming core mold tooling (3), wherein the main body part forming core mold tooling (3) and the flat plate material layer (2) are arranged in a one-to-one correspondence manner;
s3, heating the flat board material layer (2) and thermoforming the flat board material layer (2) into the main body part (11);
s4, combining the main body part (11) on the main body part forming core mold tool (3), placing the twister strip (12) and the plane material layer (13) according to preset positions, and then placing a composite material cover plate (8) on the plane material layer (13), wherein the sizes of the twister strip (12) and the plane material layer (13) are designed sizes;
s5, bagging and curing to form the airplane composite stringer (1).
2. The method of manufacturing an aircraft composite stringer according to claim 1, wherein in step S4, the two body portion forming core die tooling (3) are placed in a design position such that the two body portions (11) are combined in their position within the aircraft composite stringer (1).
3. The method of manufacturing an aircraft composite stringer according to claim 2, wherein the aircraft composite stringer (1) is a T-stringer, the main body portion (11) is "L" shaped, the main body portion (11) comprises T-stringer web portions (111) and T-stringer bead portions (112), the T-stringer web portions (111) of the two main body portions (11) are arranged in abutment after the aircraft composite stringer (1) is formed, and the T-stringer bead portions (112) extend in a direction away from each other.
4. The method of manufacturing an aircraft composite stringer according to claim 2, wherein the aircraft composite stringer (1) is an i-shaped stringer, the main body portion (11) is C-shaped, the main body portion (11) comprises a web portion (114), both ends of the web portion (114) are provided with rim portions (115) which are perpendicular to the web portion (114) and extend in the same direction, and after the aircraft composite stringer (1) is formed, the web portions (114) of the two main body portions (11) are attached to each other and are in an i shape.
5. The method of manufacturing an aircraft composite stringer according to claim 1, wherein the main body section forming core die tooling (3) is provided with a flat bed mounting recess (31).
6. The method for manufacturing an aircraft composite stringer according to claim 1, wherein in step S1, the flat sheet layer (2) is cut out after laying up of the composite material.
7. The method of manufacturing an aircraft composite stringer according to any of claims 1-6, wherein the body portion forming core die tooling (3) is provided with glue blocking grooves.
8. A method of manufacturing an aircraft composite stringer according to any of claims 1 to 6, wherein in step S2, the flat bed layer (2) is transferred to the body section forming core tooling (3) using auxiliary tooling.
9. The method of manufacturing an aircraft composite stringer according to any of claims 1-6, wherein in step S2, after the flat sheet layer (2) is transferred to the body section forming core tooling (3), it is further necessary to compact the flat sheet layer (2) using a pre-formed cover sheet (7).
10. A method of manufacturing an aircraft composite stringer according to any of claims 1-5, wherein said step S5 comprises:
s51, sequentially arranging an isolation film (4), an air felt (5), a vacuum bag (6) and a curing sealing strip (9) on the main body part forming core die tool (3);
and S52, after vacuumizing and leak detection are qualified, putting the main body part forming core die tool (3) into an autoclave for curing and forming.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010358890.9A CN113561520A (en) | 2020-04-29 | 2020-04-29 | Method for manufacturing airplane composite stringer |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010358890.9A CN113561520A (en) | 2020-04-29 | 2020-04-29 | Method for manufacturing airplane composite stringer |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115008787A (en) * | 2022-04-26 | 2022-09-06 | 浙江大学 | Composite material T-shaped stringer forming tool and method |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108943766A (en) * | 2017-05-19 | 2018-12-07 | 中国商用飞机有限责任公司 | Co-bonding forming process for T-shaped reinforced wall plate made of composite material |
| CN108973159A (en) * | 2017-05-31 | 2018-12-11 | 中国商用飞机有限责任公司 | A kind of I-shaped stringer moulding process of composite material |
-
2020
- 2020-04-29 CN CN202010358890.9A patent/CN113561520A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108943766A (en) * | 2017-05-19 | 2018-12-07 | 中国商用飞机有限责任公司 | Co-bonding forming process for T-shaped reinforced wall plate made of composite material |
| CN108973159A (en) * | 2017-05-31 | 2018-12-11 | 中国商用飞机有限责任公司 | A kind of I-shaped stringer moulding process of composite material |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115008787A (en) * | 2022-04-26 | 2022-09-06 | 浙江大学 | Composite material T-shaped stringer forming tool and method |
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Application publication date: 20211029 |