CN214524367U - Aircraft control surface composite material wallboard structure and forming system thereof - Google Patents

Abstract

The utility model provides an aircraft control surface composite material wallboard structure and a forming system thereof, which relate to the technical field of aviation manufacturing, can realize quick and low-cost manufacturing, can increase the rigidity of the wallboard based on the stress characteristics of the control surface, and simultaneously designs a force transmission path; the structure is a plate-shaped structure provided with a plurality of geometric groove structures; the molding system includes: the upper surface is provided with a female die of a plurality of concave grating unit blocks, the lower surface is provided with a male die of a plurality of convex grating unit blocks, a heating device, a cold water circulating device, a vacuum bag and a press machine; placing the ribs in the grooves of the concave grid template, and paving a layer of skin on the ribs; and after preheating, pressing the convex grid template downwards under a vacuum condition to carry out die assembly, pressurizing, maintaining pressure, cooling, shaping and demoulding to obtain the wallboard structure. The utility model provides a technical scheme is applicable to the in-process of aircraft control surface wallboard design and manufacturing.

Description

Aircraft control surface composite material wallboard structure and forming system thereof

[ technical field ] A method for producing a semiconductor device

The utility model relates to an aeronautical manufacturing technical field especially relates to an aircraft control surface combined material wallboard structure and forming system thereof.

[ background of the invention ]

The design of new aircraft airframe components requires ultra-lightweight construction with limited weight allowed. The fiber reinforced composite material is widely applied to main and secondary load-bearing structures of modern aviation aircrafts due to excellent specific stiffness and specific strength. The control surface structure is used as a secondary bearing structure of the airplane wing, and metal is replaced by composite material relatively earlier in order to reduce weight and improve vibration characteristics.

The existing aircraft control surface wallboard structure mainly has 2 types, one type is a reinforced wallboard structure formed by co-cementing or co-curing a stringer such as a T, I or Pi and the like and a composite material skin; the other is a sandwich panel structure formed by co-curing a foam core material and a composite skin. Wherein the stiffened wall panel structure has wider application. 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. But the main disadvantages are that the skin is thicker, the weight is larger, only a regular structure can be prepared, the structural efficiency is limited, and the process cost is higher. And based on the control surface structure stress characteristics, the force transmission path of the wallboard structure is difficult to design.

Among the prior art solutions, the closest technical solutions to the proposed solution of the present application include the following 4:

the first one, as shown in FIG. 1, comes from the patent "Composite string and method of manufacturing a Composite string", application No. WO 2011121340. The proposal relates to a forming mode and a manufacturing process of a composite material reinforced wall plate. The stringer is T-shaped and the web includes an insert and a twister bar design. Two rows of nails are used as crack-stopping design at the end of the stringer of the stiffened plate. The scheme belongs to a typical T-shaped long-truss wallboard co-cementing stiffened wallboard structure.

Second, from the patent "Process of manufacturing composition panels with U-shaped constraining members", application No. US7959753B 2. The scheme mainly relates to a co-curing integral forming method for a U-shaped stringer stiffened wall plate structure, is suitable for two typical structures of an intermediate intercalation and a non-intercalation, and does not relate to a positioning device between a stringer and a skin. The scheme belongs to a typical U-shaped non-continuous stringer wallboard co-curing stiffened wallboard structure.

The third is shown in figure 2 and is from the patent application No. CN102990940A of composite material stiffened plate liquid forming device and method. The patent mainly designs a liquid forming device and a method for a composite material stiffened plate, which comprises the steps of placing a reinforcing fiber material with a rib structure in a groove of a forming die for forming, then laying and forming the reinforcing fiber material with a skin structure, and then injecting liquid resin for integral forming. The patent does not use a mould pressing process for forming, and the control difficulty of the volume content of the fiber is higher.

The fourth is shown in fig. 3 from the patent "a composite elevator", application No. CN 103754353B. This patent mainly relates to a combined material elevator structure, and this structure arranges the counter weight roof beam, has creatively designed the butt joint of elevator and trimmer, adopts transition joint to connect etc.. The control surface structure adopts an advanced honeycomb wall plate rib thinning type structure and adopts a simple and reliable joint connection form.

The above four structures all have their drawbacks, and cannot meet the requirements for the structural design of the aircraft in the new era.

Accordingly, there is a need to develop a fast and easy-to-mold, low-cost, high-adaptability rudder surface wall plate structure and a molding system thereof to address the deficiencies of the prior art and to solve or alleviate one or more of the above problems.

[ summary of the invention ]

In view of this, the utility model provides an aircraft control surface combined material wallboard structure and molding system thereof both can realize quick low-cost manufacturing, can increase wallboard rigidity based on control surface atress characteristics again, designs simultaneously and passes the power route.

On the one hand, the utility model provides an aircraft control surface combined material wallboard structure, a serial communication port, the platelike structure of wallboard structure for being equipped with a plurality of geometry groove structure.

The above aspects and any possible implementations further provide an implementation where the geometric groove is a combination of one or more of a square groove, a triangular groove, a polygonal groove, and a trapezoidal groove.

The above aspect and any possible implementation further provide an implementation, wherein the geometric grooves are distributed on the same plane of the plate-shaped structure.

The above aspect and any possible implementation manner further provide an implementation manner, wherein the geometric grooves are distributed on two sides of the plate-shaped structure, and the shapes of the grooves on the two sides correspond to each other.

There is further provided in accordance with the above aspect and any possible implementation, a method of manufacturing a panel structure, the panel structure comprising a skin and a rib.

On the other hand, the utility model provides a molding system of aircraft control surface combined material wallboard structure, a serial communication port, molding system includes: the upper surface is provided with a female die of a plurality of concave grating unit blocks, the lower surface is provided with a male die of a plurality of convex grating unit blocks, a heating device, a cold water circulating device, a vacuum bag and a press machine;

the male die is hung above the female die and is opposite to the female die; the male die is connected with the press machine and finishes the actions of pressing down and lifting under the action of the press machine; a plurality of heating devices for heating the die and a cold water circulating device for cooling and shaping are arranged near the male die and the female die;

the concave grid cell blocks are placed in the vacuum bag, which is connected to a vacuum extraction device.

The above aspect and any possible implementation further provide an implementation in which the concave grill unit block is provided with an expansion pad on an inner wall of the groove.

The above aspects and any possible implementations further provide an implementation in which the concave grating unit block grooves are in the shape of one or a combination of square grooves, triangular grooves, polygonal grooves, trapezoidal grooves; the convex shape of the convex grating unit block corresponds to the shape of the groove.

The above-described aspects and any possible implementations further provide an implementation in which the female grid element blocks are laid evenly and regularly on the base plate of the female mould, and the male grid element blocks are laid in a manner corresponding to the female grid element blocks.

In another aspect, the present invention provides an aircraft control surface, wherein the wall plate structure is used as a wall plate of the aircraft control surface.

The utility model also discloses a forming method of the aircraft control surface composite material wallboard structure, which is characterized in that the forming method is realized by adopting any one of the forming systems;

the molding method comprises the following steps:

s1, cutting ribs and performing;

s2, placing the preformed ribs in the grooves of the concave grid unit blocks;

s3, cutting and preforming a skin panel material;

s4, starting a heating device to heat the die;

s5, laying the preformed skin panel material on the surface of the concave grid unit block;

s6, after the vacuum bag is vacuumized, pressing down a male die with a plurality of convex grid unit blocks on the lower surface, and closing the die;

s7, pressurizing, maintaining pressure, cooling and shaping;

and S8, demolding to obtain the aircraft rudder surface composite material wall plate structure.

Compared with the prior art, the utility model discloses can obtain including following technological effect: the composite material wallboard grid structure of the aircraft control surface and the forming method thereof have the advantages of light weight, large designable space, high bending rigidity, good stability and easy maintenance under the condition of ensuring the rigidity of the wallboard; the mould pressing process is utilized to realize rapid, low-cost and high-quality manufacturing more easily; the forming system is suitable for various composite material grating wall plate structures, can improve the forming efficiency of the composite material part structure and reduce the manufacturing cost; the addition of the ribs increases the rigidity of the wall plate on one hand, and forms a force transmission path on the other hand, so that the force borne by the wall plate has a fixed effective transmission way.

Of course, it is not necessary for any product of the present invention to achieve all of the above-described technical effects simultaneously.

[ description of the drawings ]

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.

FIGS. 1-3 illustrate three prior art configurations;

fig. 4 is a schematic structural view of a wall panel grating of an aircraft control surface according to an embodiment of the present invention;

fig. 5 is a flowchart of a method for forming an aircraft control surface wall plate according to an embodiment of the present invention;

FIG. 6 is a diagram of an exemplary grid structure provided by one embodiment of the present invention;

fig. 7 is a schematic diagram of a grid structure according to an embodiment of the present invention;

fig. 8 is a schematic structural view of a grid mold according to an embodiment of the present invention;

fig. 9 is a schematic structural view of an expansion pad of a grid die according to an embodiment of the present invention;

fig. 10 is a schematic view of a method for forming a composite material grid wall panel according to an embodiment of the present invention.

Wherein, in the figure:

1. a wall panel structure; 2. covering a skin; 3. an edge bead; 4. a middle rib; 5. a mold; 6. a mold base plate; 7. a grill unit block; 8. an intumescent mat; 9. vacuumizing equipment; 10. a female die; 11. A male mold; 12. a heating device; 13. circulating cold water; 14. a work table; 15. and (4) vacuum bag.

[ detailed description ] embodiments

For better understanding of the technical solutions of the present invention, the following detailed descriptions of the embodiments of the present invention are provided with reference to the accompanying drawings.

It should be understood that the described embodiments are only some embodiments of the invention, and not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the embodiments of the present invention and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.

The utility model provides a brand-new aircraft rudder face wallboard grid structure based on preparation of continuous compression molding process and forming method thereof both can realize quick low-cost manufacturing, can increase wallboard rigidity simultaneous design and pass the power route based on rudder face atress characteristics again.

The aircraft control surface wall panel grating structure is shown in figure 4. The grid reinforcing structure comprises reinforcing ribs and a skin 2, the reinforcing ribs comprise edge ribs 3 and middle ribs 4, the grid is distributed in a polygonal grid mode, and the structure shows various characteristics. The grid structure has better topological optimization characteristics in geometrical form. The aircraft control surface composite material wallboard grid unit structure is designed based on the optimized topological relation, the wallboard grid structure is preliminarily designed by utilizing commercial optimization software aiming at the load stress characteristic of the commercial aircraft control surface, and the detailed grid design is developed by comprehensively considering the weight cost, the structural strength, the manufacturability and the maintainability by adopting CATIA three-dimensional software.

The grid structure comprises a square shape, a hexagonal shape, a square shape with a meter-shaped shape, a positive and negative 45-degree oblique line and a horizontal line cross shape, and the cross shape can be in various cross modes, such as triangles with equal and uniform sizes, triangles with different sizes and regular arrangement or polygons with irregular arrangement. The grid structure is mainly, but not limited to, the form shown in fig. 6, and may be other polygonal shapes. The grid structure can be broken down into several sets of ribs of different orientations, as shown in fig. 7, with the diagonal ribs in horizontal, vertical and different angles grouped together. The inclination angle of the diagonal ribs is not limited to 45 °, but may be other angles.

The width and the length of the ribs are cut from the prepreg according to the design requirements of the control surface wallboard 1. The middle ribs 4 are the difficulty in manufacturing the grid structure (the edge ribs refer to the periphery and the whole four sides of the grid shown in the last figure of fig. 7, and are characterized by being capable of selecting non-intersection, and the middle ribs refer to ribs needing to be intersected, and are more difficult to process than non-intersection ribs due to the thickness problem). According to the groove position of the ribs in the mold 5, a grid with the same size is pasted on the aluminum plate by using a high-temperature PI adhesive tape and used as the reference of the preformed rib grid, and the prepreg tows are prepared into a plurality of single-layer grid ribs by using a fusion welding process, so that the ribs can be conveniently and rapidly laid under the high-temperature mold in the follow-up process, the time is saved, and the resin oxidation time is reduced.

The mould 5 adopts a mould pressing process, an upper female mould 10 moves, and a lower male mould 11 is fixed. The male mould 11 of the grid structure is shown in fig. 8. Mainly consisting of a mould base plate 6 and a grid unit block 7. The bottom plate 6 and the grating unit block 7 are positioned by bolt connection. The expansion pad groove is filled with composite material preformed ribs to form a grid structure.

The flow of the forming method of the aircraft control surface composite material wall plate grid structure is shown in figure 5, the aircraft control surface composite material wall plate grid structure is prepared by adopting a compression molding process of thermoplastic in-situ heating and rapid water cooling, and the steps comprise: rib cutting → middle rib performing → edge rib performing → panel cutting → panel laying performing → mold preheating → rib laying → panel laying → mold closing preheating → vacuum pumping → pressure maintaining → cooling shaping → demoulding.

The forming tool comprises a die 5, a die base plate 6, a grating unit block 7, an expansion pad 8 and a vacuumizing device 9; the moulding apparatus comprises a female mould 10, a male mould 11, heating means 12, a cold water cycle 13, a table 14, a vacuum bag 15 and a press. The forming die is provided with adjustable grid cell blocks 7 and their expansion pads 8. The molding equipment is provided with a vacuum auxiliary pressure device, an electric heating device, a quick water cooling device and a press pressurizing device. The press presses the male die 11 from top to bottom, so that the wallboard raw material is in an inward-concave grid structure under the action of pressure.

The specific content comprises the following steps: and paving a wallboard prepreg 2 on the upper layer of the mould 5 with the laid grid structure, manufacturing a vacuum bag 15 for the whole mould, and simultaneously vacuumizing, heating 12 and pressurizing the workpiece by using a vacuum machine 9 and a press machine 16 to form the required shape of the aircraft control surface wallboard. And then shaped and stripped using a rapid water cooling system 13. Generally, the compression molding needs to be preheated for 3 minutes, kept for 3 minutes under the pressure of 0.7-20MPa, cooled to 70-100 ℃ for about 20 minutes, and then the film can be removed.

The rib structure preform is placed in a groove of a forming die, then a wall plate skin is laid on the die, vacuum auxiliary pressurization is carried out, the shape is corrected in a preheating mode, and co-curing integrated forming is achieved through a molding press. The skin is of a laminated structure which sequentially comprises a conductive layer, a first insulating layer, a heating layer, a second insulating layer and a bearing layer; the conductive layer is used for providing a lightning path; the first insulating layer and the second insulating layer are used for positioning the heating layer and protecting the bearing layer from being subjected to different potential corrosion; the heating layer is used for electrically heating to prevent and remove ice; the bearer layer is used to provide bearer functionality for the other layers. The conductive layer is a wire mesh or a conductive polymer mesh material. The heating layer is made of copper-based or nickel-based materials.

The utility model discloses an aircraft rudder face combined material wallboard grid structure and molding system and method thereof, under the circumstances of guaranteeing wallboard rigidity, light in weight, but the design space is big, and bending stiffness is high, and stability is good, and easy maintainability. Rapid, low cost, high quality manufacturing is also more easily achieved using a molding process. The molding process and the tool thereof can be suitable for various composite material grating wall plate structures, improve the molding efficiency of the composite material part structure and reduce the manufacturing cost.

The aircraft control surface composite material wall plate structure and the forming system thereof provided by the embodiment of the application are described in detail above. The above description of the embodiments is only for the purpose of helping to understand the method of the present application and its core ideas; meanwhile, for a person skilled in the art, according to the idea of the present application, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present application.

As used in the specification and claims, certain terms are used to refer to particular components. As one skilled in the art will appreciate, manufacturers may refer to a component by different names. This specification and claims do not intend to distinguish between components that differ in name but not function. In the following description and in the claims, the terms "include" and "comprise" are used in an open-ended fashion, and thus should be interpreted to mean "include, but not limited to. "substantially" means within an acceptable error range, and a person skilled in the art can solve the technical problem within a certain error range to substantially achieve the technical effect. The description which follows is a preferred embodiment of the present application, but is made for the purpose of illustrating the general principles of the application and not for the purpose of limiting the scope of the application. The protection scope of the present application shall be subject to the definitions of the appended claims.

It is also noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a good or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such good or system. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a commodity or system that includes the element.

It should be understood that the term "and/or" as used herein is merely one type of association that describes an associated object, meaning that three relationships may exist, e.g., a and/or B may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.

The foregoing description shows and describes several preferred embodiments of the present application, but as aforementioned, it is to be understood that the application is not limited to the forms disclosed herein, but is not to be construed as excluding other embodiments and is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the application as described herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the application, which is to be protected by the claims appended hereto.

Claims (8)

1. The composite material wallboard structure for the control surface of the airplane is characterized in that the wallboard structure is a plate-shaped structure provided with a plurality of geometric groove structures; ribs are embedded in the protruding parts of the grooves, and the surface layers of the grooves are of skin structures;

the geometric grooves comprise one or more combinations of non-parallelogram grooves and polygonal grooves with five sides and more than five sides.

2. The aircraft rudder surface composite material panel structure according to claim 1, characterised in that the geometrical recesses are distributed on the same face of the plate-like structure.

3. The aircraft rudder surface composite material panel structure according to claim 1, wherein the geometrical grooves are distributed on both surfaces of the plate-shaped structure, and the shapes of the grooves on both surfaces correspond to each other.

4. A molding system for an aircraft control surface composite material panel structure, the molding system comprising: the upper surface is provided with a female die of a plurality of concave grating unit blocks, the lower surface is provided with a male die of a plurality of convex grating unit blocks, a heating device, a cold water circulating device, a vacuum bag and a press machine;

the male die is hung above the female die and is opposite to the female die; the male die is connected with the press machine and realizes the actions of pressing down and lifting under the control of the press machine; a plurality of heating devices and cold water circulating devices are arranged near the male die and the female die;

the concave grid cell blocks are placed in the vacuum bag, which is connected to a vacuum extraction device.

5. The system for forming an aircraft rudder surface composite material panel structure according to claim 4, wherein the concave grille unit blocks are provided with swelling pads on the inner walls of the grooves.

6. The system of claim 4, wherein the concave grid element panel grooves have a shape comprising a combination of one or more of non-parallelogram, pentagon and polygon above; the convex shape of the convex grating unit block corresponds to the shape of the groove.

7. The system for forming an aircraft rudder surface composite material panel structure according to claim 4, wherein the concave grid element blocks are uniformly and regularly laid on the base plate of the female mold, and the convex grid element blocks are laid in a manner corresponding to the concave grid element blocks.

8. An aircraft rudder surface, characterised in that a panel construction according to any one of claims 1 to 3 is used as a panel for an aircraft rudder surface.

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