CN112895520A - Airplane control surface composite material bidirectional reinforcing structure and forming method - Google Patents
Airplane control surface composite material bidirectional reinforcing structure and forming method Download PDFInfo
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- CN112895520A CN112895520A CN202110056345.9A CN202110056345A CN112895520A CN 112895520 A CN112895520 A CN 112895520A CN 202110056345 A CN202110056345 A CN 202110056345A CN 112895520 A CN112895520 A CN 112895520A
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- 239000002131 composite material Substances 0.000 title claims abstract description 59
- 230000002457 bidirectional effect Effects 0.000 title claims abstract description 45
- 230000003014 reinforcing effect Effects 0.000 title claims abstract description 42
- 238000000034 method Methods 0.000 title claims abstract description 34
- 229920002379 silicone rubber Polymers 0.000 claims abstract description 39
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 29
- 239000004917 carbon fiber Substances 0.000 claims abstract description 29
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 27
- 239000002184 metal Substances 0.000 claims abstract description 25
- 238000000465 moulding Methods 0.000 claims abstract description 14
- 239000003292 glue Substances 0.000 claims abstract description 7
- 239000004945 silicone rubber Substances 0.000 claims description 12
- 239000000835 fiber Substances 0.000 claims description 10
- 238000009958 sewing Methods 0.000 claims description 10
- 239000011347 resin Substances 0.000 claims description 8
- 229920005989 resin Polymers 0.000 claims description 8
- 238000009941 weaving Methods 0.000 claims description 8
- 238000002360 preparation method Methods 0.000 claims description 6
- 230000002787 reinforcement Effects 0.000 claims description 5
- 238000005516 engineering process Methods 0.000 claims description 4
- 238000004073 vulcanization Methods 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 3
- 229920001971 elastomer Polymers 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 238000010276 construction Methods 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 230000005540 biological transmission Effects 0.000 abstract description 3
- 238000005457 optimization Methods 0.000 abstract 1
- 239000000463 material Substances 0.000 description 3
- 239000011162 core material Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000009940 knitting Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000010923 batch production Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000000805 composite resin Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 238000009417 prefabrication Methods 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 238000009745 resin transfer moulding Methods 0.000 description 1
- 238000001721 transfer moulding 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/04—Making preforms by assembling preformed material
-
- 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/681—Component parts, details or accessories; Auxiliary operations
- B29C70/682—Preformed parts characterised by their structure, e.g. form
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention relates to the field of large-size secondary bearing wall plates of airplane structures, and provides a composite material bidirectional reinforcing structure of an airplane control surface and a forming method. The bidirectional reinforcing structure comprises a middle layer plate, a first reinforcing layer arranged on one side of the middle layer plate and a second reinforcing layer arranged on the other side of the middle layer plate; the first reinforcing layer and the second reinforcing layer are respectively composed of a plurality of first stringers and second stringers which are arranged side by side, and a set included angle of 85-90 degrees is formed between each stringer web plate and the middle plate. The molding method comprises the following steps: preparing a metal hard die, preparing a silicon rubber soft die, forming a carbon fiber prefabricated body, injecting glue, curing and demolding. The invention can realize the optimization of the force transmission path of the control surface structure by changing the parameters such as the two-way reinforced integral structure form, the spatial arrangement included angle and the like; the forming process method can be suitable for various composite material integrated structures, improves the forming efficiency of the composite material part structure and reduces the manufacturing cost.
Description
Technical Field
The invention relates to the field of large-size secondary bearing wall plates of airplane structures, in particular to a composite material bidirectional reinforcing structure of an airplane control surface and a forming method.
Background
The existing airplane control surface composite material bidirectional reinforced structure mainly has 2 types, one type is a reinforced wall plate structure formed by co-cementing or co-curing of stringers such as 'T' and 'I' and composite material skins; the other is a sandwich panel structure formed by co-curing a honeycomb core material and a composite material skin. The structure mainly bears pneumatic load and transmits joint load in the stress mode of the control surface, the bearing direction is in the course, and the stability failure mode is mainly prevented during the design of the wall plate structure.
Patent 1 "Composite string and method of manufacturing a Composite string", patent 2 "Process of manufacturing Composite panels with U-shaped reinforcing members", patent 3 "liquid forming apparatus and method of Composite stiffened panel", and patent 4 "an aircraft Composite stiffened panel structure" are typical Composite stiffened panel structures. Patent 5 "a combined material elevator" all relates to combined material control surface wallboard co-curing integral molding method, and the wallboard structure mainly is honeycomb or foam sandwich integral structure.
Compared with the traditional metal structure, the two wallboard structures can effectively improve the rigidity of the control surface, reduce the connecting quantity of fasteners, reduce oil consumption and increase the economical efficiency.
However, the sandwich structure formed by the honeycomb core material faces the problems of moisture absorption and poor maintainability of the structure; the reinforced wall plate structure has the main defects of thick skin, heavy weight, limited structural efficiency and high process cost, and only a regular structure can be prepared.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides a bidirectional reinforcing structure for an aircraft control surface composite material and a forming method.
The invention adopts the following technical scheme:
a composite material bidirectional reinforcing structure for an aircraft control surface comprises a middle layer plate, a first reinforcing layer arranged on one side of the middle layer plate, and a second reinforcing layer arranged on the other side of the middle layer plate; the middle layer plate, the first reinforcing layer and the second reinforcing layer are integrally formed;
the first reinforcement layer is comprised of a plurality of first stringers arranged side-by-side and the second reinforcement layer is comprised of a plurality of second stringers arranged side-by-side; the included angle between the first stringer and the second stringer and the included angle between the planes of the first stringer, the second stringer and the middle layer plate are set angles.
Further, the first and second stringers may be U-shaped, J-shaped, T-shaped, or I-shaped, and the first and second stringers may be identical or different in structure.
Furthermore, the included angle between the planes of the first stringer, the second stringer and the middle layer plate ranges from 85 degrees to 90 degrees.
Further, the included angle between the first stringer and the second stringer is 90 °, 60 °, 45 °, or 30 °.
Furthermore, the middle layer plate, the first stringer and the second stringer are all made of composite materials.
Further, the composite material is a carbon fiber-resin composite material
A method of forming an aircraft control surface composite bidirectional reinforced structure, the method being used for forming the aircraft control surface composite bidirectional reinforced structure, the method comprising:
s1, preparing a metal hard die: finishing the preparation of a metal hard die according to the size of the composite material bidirectional reinforced structure, wherein the metal hard die is a combined closed die and is used for placing a silicon rubber soft die and a carbon fiber prefabricated body and injecting resin for molding;
s2, preparing a silicon rubber soft mold: finishing vulcanization molding of the silicon rubber soft mold according to the external dimensions of the first stringer and the second stringer; the silicon rubber soft die is used for positioning the first long truss and the second long truss in the forming process;
s3, preparing a carbon fiber preform: the preparation of the carbon fiber preform is completed by adopting a three-dimensional fiber weaving or fiber sewing technology; the shape or size of the carbon fiber preform is substantially the same as that of the integrated bidirectional reinforcing structure;
s4, injecting glue: integrally combining the carbon fiber prefabricated body and the silicon rubber soft mold, embedding the carbon fiber prefabricated body and the silicon rubber soft mold into a metal hard mold, arranging a rubber inlet and outlet channel on the metal hard mold, checking the sealing performance, vacuumizing, and injecting resin;
s5, curing: the curing molding of the integrated bidirectional reinforced structure of the composite material is realized at a set temperature;
s6, demolding: and cooling, and taking down the silicon rubber soft mold to obtain the aircraft control surface composite material bidirectional reinforcing structure.
Further, in step S1, the metal hard mold is provided with a silicone rubber positioning hole for fixing the silicone rubber soft mold.
Further, in step S2, the temperature for vulcanizing the soft mold of the silicone rubber is 150 to 200 ℃.
Further, in step S3, the knitting or sewing of the carbon fiber preform is performed by using a three-dimensional weaving apparatus or a fiber sewing apparatus.
Further, in step S5, the curing temperature is 25 to 200 ℃ and is specifically determined depending on the type of resin.
A forming tool for a composite bidirectional reinforcing structure of an airplane control surface comprises a metal hard die, a silicon rubber soft die and a carbon fiber prefabricated body;
the silicon rubber soft mold is attached to and arranged in each stringer interval of the carbon fiber prefabricated body, and the functions of overall positioning and size control of the first stringer and the second stringer are achieved (size deviation and axis deviation of the stringers in the curing and forming process are prevented).
The invention has the beneficial effects that: the integrated structure with bidirectional reinforcement solves the technical problem that the composite material structure in the prior art has lower overall strength in a structural body taking integral buckling as a control condition; by changing different design parameters such as the form of the bidirectional reinforced structure and the spatial arrangement included angle of the stringers, the optimal design of the force transmission path of the control surface structure can be realized, so that the application requirements of the aircraft control surface structure are met; the molding process method can be suitable for various composite material structures, improves the molding efficiency of the composite material part structure, and reduces the manufacturing cost.
Drawings
Fig. 1 is a schematic diagram of a composite bidirectional reinforcing structure for an aircraft control surface according to an embodiment of the invention.
FIG. 2 is a schematic three-view illustration of a composite bidirectional stiffening structure for an aircraft control surface in an embodiment; wherein (a) is a front view, (b) is a top view, and (c) is a side view.
FIG. 3 is a schematic view of an embodiment of the present invention showing the stringer at an angle of 85 to the plane of the intermediate plies.
Fig. 4 is a schematic flow chart of a method for forming a composite bidirectional reinforcing structure of an aircraft control surface according to an embodiment.
Fig. 5 is a schematic view showing an integral combination of a carbon fiber preform with a silicone rubber soft mold and a metal hard mold (in the figure, only a first reinforcing layer is shown, and a second reinforcing layer is not shown, for the sake of understanding).
In the figure: 1-intermediate layer plate; 2-a first stringer; 3-a second stringer; 4-metal hard mold; 5-silicon rubber soft mold; 6-carbon fiber preform.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that technical features or combinations of technical features described in the following embodiments should not be considered as being isolated, and they may be combined with each other to achieve better technical effects.
As shown in fig. 1, the aircraft rudder surface composite material bidirectional reinforcing structure according to the embodiment of the invention includes a middle layer plate 1, a first reinforcing layer arranged on one side of the middle layer plate 1, and a second reinforcing layer arranged on the other side of the middle layer plate 1; the first enhancement layer comprises a plurality of first longerons 2 of arranging side by side, the second enhancement layer comprises a plurality of second longerons 3 of arranging side by side, be the settlement contained angle between first longeron 2, second longeron 3. In this embodiment, the first and second stringers 2, 3 are U-shaped, and the included angle between the stringers and the middle deck boards 1 is 90 ° as shown in fig. 2. Figure 3 shows the stringer at an angle of 85 to the median sheet 1.
The included angle between the first stringer 2 and the second stringer 3 can be selected according to actual requirements, for example, 90 °, 60 °, 45 ° or 30 °, and can be determined according to the stress condition of the control surface of the aircraft.
The existing composite material integrated structure is used for a structural body with integral buckling as a control condition, and the overall strength of the structural body is low due to fiber breakage, accumulation and bending in a plate, so that the technical problem is solved. In the composite material bidirectional reinforced structure provided by the invention, the first stringer 2 and the second stringer 3 are arranged side by side in respective planes, so that the weak points of the strength and rigidity in the structure are avoided, and the strength and rigidity of the whole structure are greatly enhanced.
The integrated structure provided by the invention comprises the middle layer plate 1 and the bidirectional reinforcing layer, and the force transmission path of the control surface structure can be designed by changing the bidirectional reinforcing structure form and the spatial arrangement included angle based on the stress characteristic of the control surface structure, so that the application requirements of the aircraft control surface structure with different load stress characteristics are met, and the integrated structure becomes an effective substitute of the existing aircraft control surface structure adopting a reinforced wall plate and a sandwich structure.
It should be noted that first stringer 2 and second stringer 3 can take a variety of configurations, such as U-shaped, J-shaped, T-shaped, or drum-shaped, and that first stringer 2 and second stringer 3 can be identical or different, such as drum-shaped configuration for first stringer 2 and T-shaped configuration for second stringer 3. The spatial included angle between the first stringer 2 and the second stringer 3 can also be designed according to the actual stress characteristics. The included angles of the first stringer 2, second stringer 3 and the plane of the intermediate laminate 1 are typically arranged to be from 85 to 90. The invention provides a plurality of combination modes, which are convenient to flexibly select according to actual needs.
As shown in fig. 5, an embodiment of the present invention further provides a forming tool for a composite material bidirectional reinforcing structure of an aircraft control surface, including a metal hard mold 4, a silicone rubber soft mold 5, and a carbon fiber preform 6; and the silicon rubber soft mold 5 is attached and arranged in each stringer interval of the carbon fiber prefabricated body 6.
As shown in fig. 4, a method for forming an aircraft control surface composite material bidirectional reinforced structure according to an embodiment of the present invention is used for producing the aircraft control surface composite material bidirectional reinforced structure, and the method includes:
s1, preparing a metal hard die 4: finishing the preparation of a metal hard die 4 according to the size of the composite material bidirectional reinforcing structure, wherein the metal hard die 4 is used for placing a silicon rubber soft die 5 and a carbon fiber prefabricated body 6;
s2, preparing a silicon rubber soft mold 5: finishing vulcanization molding of the silicon rubber soft mold 5 according to the structural external dimensions of the first stringer 2 and the second stringer 3; the silicon rubber soft mold 5 is used for positioning the first stringer 2 and the second stringer 3 in the forming process;
s3, preparing a carbon fiber preform 6: the preparation of the carbon fiber preform 6 is completed by adopting a three-dimensional fiber weaving or fiber sewing technology; the shape or size of the carbon fiber preform 6 is substantially the same as the size of the integrated bidirectional reinforcing structure;
s4, injecting glue: integrally combining the carbon fiber prefabricated body 6 and the silicon rubber soft mold 5, embedding the combined body into the metal hard mold 4, arranging a rubber inlet and outlet channel on the metal hard mold 4, checking the sealing performance, vacuumizing, and injecting resin;
s5, curing: the curing molding of the integrated bidirectional reinforced structure of the composite material is realized at a set temperature;
s6, demolding: and cooling, and taking down the silicon rubber soft mold to obtain the aircraft control surface composite material bidirectional reinforcing structure.
Preferably, in step S1, the metal hard mold 4 is provided with a silicone rubber positioning hole for fixing the silicone rubber soft mold 5.
Preferably, in step S2, the vulcanization temperature of the silicone rubber soft mold 5 is 150 to 200 ℃.
Preferably, in step S3, the knitting or sewing of the entire structure of the carbon fiber preform 6 may be performed by using a three-dimensional weaving apparatus or a fiber sewing apparatus.
Preferably, the carbon fiber preform 6 and the silicone rubber soft mold 5 are fixed by an adhesive (matched with the glue injection resin).
The RTM process is a process in which a low viscosity resin flows in a closed mold, infiltrates a reinforcing material, and is cured to form. The airplane rudder surface composite material bidirectional reinforced structure is manufactured and finished by adopting a liquid molding RTM (resin transfer molding) process, the dry carbon fibers are utilized to realize the integral prefabrication molding of a three-dimensional weaving or sewing technology of a stringer structure in a middle layer plate 1 and two-direction reinforced layers, and then an RTM molding tool combined by a metal hard mold 4 and a silicon rubber soft mold 5 is utilized to integrally package and glue injection molding, so that the strength and the rigidity in two directions can be ensured simultaneously; the first stringer 2 and the second stringer 3 in the composite material bidirectional reinforced structure are accurately positioned and have high direction straightness, the forming process is simple and feasible, the silicon rubber soft die 5 can be used for multiple times, the batch production of the composite material integrated structure can be realized, the manufacturing cost is reduced, and the structure forming efficiency is improved.
While several embodiments of the present invention have been presented herein, it will be appreciated by those skilled in the art that changes may be made to the embodiments herein without departing from the spirit of the invention. The above examples are merely illustrative and should not be taken as limiting the scope of the invention.
Claims (10)
1. The aircraft control surface composite material bidirectional reinforcing structure is characterized by comprising a middle layer plate, a first reinforcing layer arranged on one side of the middle layer plate and a second reinforcing layer arranged on the other side of the middle layer plate; the middle layer plate, the first reinforcing layer and the second reinforcing layer are integrally formed;
the first reinforcement layer is comprised of a plurality of first stringers arranged side-by-side and the second reinforcement layer is comprised of a plurality of second stringers arranged side-by-side; the included angle between the first stringer and the second stringer and the included angle between the planes of the first stringer, the second stringer and the middle layer plate are set angles.
2. An aircraft rudder surface composite material bi-directional reinforcing structure as claimed in claim 1 wherein the first and second stringers are of U-shaped, J-shaped, T-shaped or of a cross-section and the first and second stringers are of the same or different construction.
3. An aircraft rudder surface composite material bidirectional reinforcing structure as defined in claim 1 wherein the included angle between the first stringer, the second stringer and the plane of the intermediate ply is in the range of 85 ° to 90 °.
4. An aircraft rudder surface composite material bi-directional stiffening structure as claimed in claim 1 wherein the angle between the first and second stringers is 90 °, 60 °, 45 ° or 30 °.
5. An aircraft rudder surface composite material bi-directional reinforcing structure as claimed in claim 1 wherein the intermediate deck, first stringer and second stringer are all of composite material.
6. A method of forming an aircraft control surface composite bidirectional reinforced structure, the method being used for forming the aircraft control surface composite bidirectional reinforced structure according to any one of claims 1 to 5, the method comprising:
s1, preparing a metal hard die: finishing the preparation of a metal hard die according to the outline shape and the size of the composite material bidirectional reinforced structure, wherein the metal hard die is a combined closed die and is used for placing a silicon rubber soft die and a carbon fiber prefabricated body and injecting glue for forming;
s2, preparing a silicon rubber soft mold: finishing vulcanization molding of the silicon rubber soft mold according to the external dimensions of the first stringer and the second stringer; the silicon rubber soft die is used for integral positioning and size control in the curing and forming process of the first stringer and the second stringer;
s3, preparing a carbon fiber preform: the preparation of the carbon fiber preform is completed by adopting a three-dimensional fiber weaving or fiber sewing technology; the shape and the size of the carbon fiber prefabricated body correspond to those of the composite material bidirectional reinforcing structure;
s4, injecting glue: integrally combining the carbon fiber prefabricated body and the silicon rubber soft mold, embedding the carbon fiber prefabricated body and the silicon rubber soft mold into a metal hard mold, arranging a rubber inlet and outlet channel on the metal hard mold, checking the sealing performance, vacuumizing, and injecting resin;
s5, curing: the curing molding of the integrated bidirectional reinforced structure of the composite material is realized at a set temperature;
s6, demolding: and cooling, and taking down the silicon rubber soft mold to obtain the aircraft control surface composite material bidirectional reinforcing structure.
7. The method for forming the aircraft rudder surface composite material bidirectional reinforced structure as defined in claim 6, wherein in the step S1, the metal hard mold is provided with silicone rubber positioning holes for fixing the silicone rubber soft mold.
8. The method for forming the aircraft rudder surface composite material bidirectional reinforced structure as defined in claim 6, wherein in the step S2, the temperature for vulcanizing the soft mold of the silicone rubber is 150 ℃ to 200 ℃.
9. The method for forming the aircraft rudder surface composite material bidirectional reinforced structure as defined in claim 6, wherein in the step S3, the weaving or sewing of the carbon fiber preform is performed by using a three-dimensional weaving device or a fiber sewing device.
10. The method for forming the aircraft rudder surface composite material bidirectional reinforced structure as defined in claim 6, wherein in the step S5, the curing temperature is 25 ℃ to 200 ℃.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110056345.9A CN112895520A (en) | 2021-01-15 | 2021-01-15 | Airplane control surface composite material bidirectional reinforcing structure and forming method |
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| CN202110056345.9A CN112895520A (en) | 2021-01-15 | 2021-01-15 | Airplane control surface composite material bidirectional reinforcing structure and forming method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114801251A (en) * | 2022-04-25 | 2022-07-29 | 沈阳航空航天大学 | Integrated forming method for general aircraft carbon fiber prepreg corrugated wall plate |
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2021
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| US20040130072A1 (en) * | 2001-08-07 | 2004-07-08 | Toshihide Sekido | Method for producing upsized frp member |
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