KR102076827B1 - Integrated Folding Wing using Composite materials and Method for manufacturing the same - Google Patents

Abstract

Disclosed is an integrated folding wing using a composite material. The integrated folding wing using the composite material includes: a first body part of which a rotating shaft hole is formed at one end; and a second body part integrally formed on the other end of the first body part, wherein the first body part includes: a support part mold; and a wing skin layer formed on a surface of the support part mold.

Description

Integrated folding wing using composite materials and method for manufacturing the same

The present invention relates to a unitary folding wing using a composite material, and more particularly, to a monolithic folding wing using a composite material and a manufacturing method thereof.

In addition, the present invention relates to an integrated folding wing and a method for manufacturing the same using a composite material that can be stored in a foldable rather than simply assembled and fixed to the fuselage, and can change the position of the wing according to the operating concept.

Recently, a lot of small and medium sized vehicles are being developed according to the global trend. The wings of small and medium-sized aircraft are usually of high aspect ratio to satisfy aerodynamic performance. And since the wing is the main component of the gas structure, it must satisfy all general related environmental conditions such as basic stiffness, strength, weight requirements and temperature and humidity.

That is, the blades must be small in deformation, not broken within the design load, and light. The wing must also satisfy the mounting and operating concepts required for the electric unit. Folded wings are used in some small and medium sized vehicles due to the advantages of operation and storage, and the application of foldable wings is continuously increasing.

In recent years, efforts have been made to economically manufacture a gas structure. Representative methods for manufacturing low cost gas structures include integrated gas structure design and fabrication. In the past, methods of fabricating structures by machining and assembling metal were typical. Recently, however, a method of fabricating a structure by stacking and curing an intermediate material such as a prepreg is used. Composite structure fabrication method is very advantageous to reduce the number of parts or to fabricate the structure in one piece.

In the construction of wings, it is necessary to use materials with high rigidity and specific strength for structural performance. For the aerodynamic performance, the outer surface of the wing should be well managed during the manufacturing stage. And according to the aircraft operation concept, it must have a pivot to implement the folding function in the wing root (wing root). Wings should be built in one piece to reduce costs and the pre- and post-process of each manufacturing process step should be minimized.

The prior art has been applied to the folding function as a content for manufacturing a composite composite wing. However, the wing is composed of pivot mount, spar, rib and fairing, which makes the inner mold (IML) mold complex. In addition, at least five IML molds were identified as required.

1. Korean Registered Patent No. 10-1407721 (Registration Date: 2014.06.09) 2. Korean Registered Patent No. 10-1267073 (Registration Date: May 16, 2013) 3. Japanese Patent Application Publication No. 2018-204461

1. Joo, Young-Sik and four others, "A Study on the Fabrication of High-Integrated Equipment Composites", Journal of the Korean Society for Aeronautical and Space Sciences, 2013.02. 2. Joo, Young-Sik and three others, "Development of Foldable Composite Wings for Kits", Journal of the Korean Institute of Military Science and Technology, 2013.08.

In order to solve the problems according to the background art, an object of the present invention is to provide an integrated folding wing of monocoque type using a composite material and a method for manufacturing the same.

In addition, the present invention is not simply assembled and fixed to the fuselage, but is stored in a foldable, and provides an integrated folding wing and a method of manufacturing the same using a composite material that can change the position of the wing according to the operating concept. have.

The present invention provides a monolithic folding wing in the form of a monocoque using a composite material to achieve the above problems.

Integrated folding wing using the composite material,

A first body part having a rotation shaft hole formed at one end thereof; And

And a second body part integrally formed at the other end of the first body part.

At this time, the first body portion, a support mold; And a wing skin layer formed on the surface of the support mold.

In addition, the second body portion is hollow inside, characterized in that the wing skin layer is integrally extended,

In addition, the wing skin layer is characterized in that the composite material is laminated on the surface of the inner mold of the removable mold assembled to the removable mold removable structure on the support mold.

At this time, the removable structure is characterized in that it consists of a protrusion and a concave portion to match the protrusion.

In addition, the composite material is characterized in that the material is at least one or more of unidirectional prepreg and woven prepreg.

In addition, the protruding portion or the concave portion of the demolding mold is characterized in that the first pin and the first pin-hole of each one of the first and second guide pins are formed.

In addition, it is characterized in that the recessed part or the protrusion part of the support part mold side are formed with 2-1 and 2-2 pin holes into which the other ends of the first and second guide pins are inserted.

In addition, the wing skin layer is formed and cured using an autoclave method.

At this time, the autoclave method is characterized by applying an OML mold assembly consisting of a lower outer mold line (OML) mold and an upper OML mold.

In addition, the autoclave method is characterized by applying an OML mold assembly consisting of a front OML mold and a rear OML mold.

In addition, the autoclave method is characterized by applying an integrated OML mold made of a flexible material.

In addition, the support mold is characterized in that it is produced using a hot press method.

In addition, the upper rotary shaft is fixed to the rotation shaft hole; And a lower rotating shaft for fixing the upper rotating shaft.

In addition, the inside of the rotary shaft hole is characterized in that the rotation preventing pin for preventing the upper or lower rotary shaft is rotated relative to the rotary shaft hole is characterized in that it is installed.

In addition, in order to prevent the relative rotational movement of the rotary shaft hole and the upper rotary shaft double, a second machining surface is formed on the upper surface of the upper rotary shaft having a shape corresponding to the first machining surface on the upper portion of the rotary shaft hole. It is characterized by.

In addition, the first and second working surface is characterized in that the track shape or elliptical track shape having a straight edge.

In addition, the inner side of the rotation shaft hole is characterized in that the first insertion hole is formed is inserted into one side of the anti-rotation pin.

In addition, the first insertion hole is characterized in that it is formed to extend to the inner portion of the lower rotating shaft.

In addition, the anti-rotation pin is characterized in that one of a square, a hexagonal, and a cylindrical.

At this time, the one-way prepreg is applied only to the main load direction and its vertical direction, the fabric type prepreg is characterized in that it is applied only to the direction bisecting the main load direction and the vertical direction.

On the other hand, another embodiment of the present invention, as a method of manufacturing an integrated folding wing using a composite material, a first body portion and a second body portion formed integrally with the other end of the first body portion is manufactured, It provides an integrated folding wing using a composite material, characterized in that the rotating shaft hole is formed at one end of the body portion.

According to the present invention, a design in which a unidirectional prepreg and a woven prepreg are mixed and laminated is much better in structural performance and manufacturability than a unidirectional or woven prepreg only design.

In addition, another effect of the present invention is to process the position for assembling the anti-rotation pin in the rotary shaft hole, the upper rotary shaft, the lower rotary shaft and to assemble and glue the pin in place, the anti-rotation pin of the blade rotation shaft is relative to the blade and the rotation shaft It can be said to play a role in preventing the rotational movement.

In addition, another effect of the present invention is that the machining surface of the upper rotary shaft and the machining surface of the upper skin corresponding thereto (ie, corresponding to the seating machine) also prevent the relative movement of the rotary shaft, so that the rotational movement between the two parts is achieved. Can be effectively and complexly prevented (doubled).

1 is a plan view of an integrated folding wing using a composite material according to an embodiment of the present invention.
FIG. 2 is a plan view of a demolding mold for manufacturing an integrated folding wing using the composite material shown in FIG. 1.
3 is a plan view of a support mold assembled with the demolding mold shown in FIG.
FIG. 4 is a plan view of an inner mold in which the demolding mold and the support mold illustrated in FIG. 1 are assembled.
FIG. 5 is a plan view in which the wing skin layer is laminated on the internal mold shown in FIG. 4.
FIG. 6 is a side cross-sectional view illustrating a concept of forming a wing skin layer laminated on the inner mold shown in FIG. 5.
FIG. 7 is a plan view of removing both the demolding mold and processing both sides after the molding and curing of FIG. 6.
FIG. 8 is a plan view of processing the hole digging portions of the rotating shaft holes and the upper rotating shaft after the processing of FIG.
FIG. 9 is a cross-sectional view of a rotating shaft portion in which an integrated folding wing using the composite material shown in FIG. 1 is assembled with a counterpart.
10 is a process chart showing the manufacturing process of the integrated folding wing using a composite material according to an embodiment of the present invention.
FIG. 11 is a graph showing a manufacturability evaluation scale of an integrated folding wing using the composite material shown in FIG. 1.

DETAILED DESCRIPTION Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings so that those skilled in the art may easily implement the present invention. As those skilled in the art would realize, the described embodiments may be modified in various different ways, all without departing from the spirit or scope of the present invention. In the drawings, parts irrelevant to the description are omitted in order to clearly describe the present invention, and like reference numerals designate like parts throughout the specification.

In the drawings, the thickness of layers, films, panels, regions, etc., are exaggerated for clarity. When a part of a layer, film, region, plate, etc. is said to be "on" another part, this includes not only the other part being "right over" but also the other part in the middle. On the contrary, when a part is "just above" another part, there is no other part in the middle. In addition, when a part is formed "overall" on another part, it means not only being formed in the whole surface (or front surface) of another part, but also not formed in the edge part.

Hereinafter, with reference to the accompanying drawings, it will be described in detail the integral folding wing using a composite material according to an embodiment of the present invention and its manufacturing method.

1 is a plan view of an integrated folding wing 100 using a composite material according to an embodiment of the present invention. Referring to FIG. 1, the integral folding wing 100 using the composite material is integrally formed at the other end of the first body part 110 and the first body part 110 in which a rotating shaft hole 112 is formed at one end thereof. The second body portion 120 and the like. The first body part 110 is an inboard corresponding to the root of the wing, and a rotating shaft hole 112 for the rotating shaft is formed, and there is no hollow type (solid type) 111. The second body part 120 is an outer board having a relatively small load, and has a hollow type 121 having an inner hollow shape. The integral folding wing 100 using the composite material is a monocoque (monocoque) form, there is no member, such as a spar, ribs, the skin is to support the load.

FIG. 2 is a plan view of the demolding mold 200 for manufacturing the integrated folding wing 100 using the composite material shown in FIG. 1. Referring to FIG. 2, the demolding mold 200 is a removable structure, and the demolding mold 200 is used to remove the mold during the manufacturing process. The removable structure consists of a protrusion and a recess that is mated to the protrusion. Referring to FIG. 2, the protrusion 210 is formed at the end of the demolding mold 200. The protrusion 210 has first and second pin holes 211 and 212 in which the first and second guide pins 221 and 222 are press-fitted to an interference fit level in a “⊃” shape. In particular, the demolding mold 200 is preferably made of a metal material, but may be a composite material, a polymer material, and the like.

3 is a plan view of the support mold 300 assembled with the demolding mold 200 shown in FIG. 2. Referring to FIG. 3, the support mold 300 is not removed and remains in the configuration of the first body portion 110. A recess 310 is formed at the end of the support mold 300 to be assembled with the protrusion 210 formed at the end of the demolding mold 200. The concave portion 310 has a "⊃" shape, and the first and second guide pins 221 and 222 are inserted into the second and second pin holes 321 and 322 at a loose fitting level. In other words, one end of the first and second guide pins 221 and 222 is press-fitted into the first and second pin holes 211 and 212, and the other end of the first and second guide pins 221 and 222 is 2-1. And the second-second pinholes 321 and 322.

Of course, in FIG. 2 and FIG. 3, for convenience of understanding, the protrusion 210 is formed on the demolding mold 200 side, and the recess 310 matching the protrusion 210 is formed on the support mold 300 side. Although illustrated as being formed, the concave portion 310 may be formed on the demolding mold 200 side, and the protrusion 210 may be formed on the supporting part mold 300 side.

In addition to the "오목" shape, the protrusions and the recesses may have other shapes such as "V" and "W" shapes.

The support part 300 may be made of carbon fiber prepreg, and in addition, a metal material, a composite material, a polymer material, a foam material, or the like may be used. For example, a support mold may be manufactured by repeatedly laminating a sublaminate composed of seven unidirectional prepregs. The sublaminate has a thickness of about 1 mm to 2 mm, and may be 45%, 45%, 10% in the ratio of 0 ° direction, ± 45 ° direction, and 90 ° direction, respectively.

On the other hand, the mold release mold 200 may be produced in one piece, or may be produced by dividing it into two pieces or three pieces or more. In other words, by forming a plurality of protrusions 210, guide pins (221, 222), pin holes (211, 212, 321, 322) and the like, it is also possible to assemble into pieces.

4 is a plan view of the internal mold 400 in which the demolding mold 200 and the support mold 300 illustrated in FIG. 1 are assembled. Referring to FIG. 4, one end of the first and second guide pins 221 and 222 may be press-fitted into the first and second pin holes 211 and 212, and the other ends of the first and second guide pins 221 and 222 may be formed. When inserted into the 2-1 and 2-2 pinholes 321 and 322, the demolding mold 200 and the support mold 300 are assembled.

This assembled state becomes the internal mold 400, and the carbon fiber prepreg, which is a composite material, is laminated on the surface of the internal mold 400 several times.

5 is a plan view in which the wing skin layer 500 is stacked on the internal mold 400 shown in FIG. 4. Referring to FIG. 5, the wing skin layer 500 is formed by laminating carbon fiber prepregs on the internal mold 400. The wing skin layer 500 is produced by laminating one-way prepreg in the 0 ° direction, a fabric prepreg in the ± 45 ° direction, and a one-way prepreg in the 90 ° direction. An example of lamination is as follows.

- stacking sequence Example 1 (mixed _{prepreg): [45 f / 0/} 0/45 f /0/0/.../45 f] ( optimum)

-Stacking example 2 (unidirectional prepreg only): [45 / -45 / 0/0/45 / -45 / 0/0 /.../ 45]

-Stacking example 3 (fabric prepreg only): [45 _f / 0 _f / 0 _f / 45 _f / 0 _f / 0 _f /.../45 _f ]

Here, the subscript "f" denotes a fabric prepreg.

This mixed prepreg stacking method has several advantages over designs using only one-way or woven prepregs.

In addition, the one-way prepreg may be applied only to the main load direction and its vertical direction, and the fabric type prepreg may be applied only to the direction bisecting the main load direction and the vertical direction. In other words, the 0 ° direction is the same as the main load direction and the wing length direction, and the 90 ° direction is the same as the vertical direction of the main load direction and the vertical direction of the wing length direction.

Prepreg is short for “pre-impregnated material” and refers to a sheet-like intermediate material in which a predetermined amount of impregnated fiber and matrix resin are impregnated in advance. Prepregs can be used to precisely control the ratio of fiber to resin. In addition, there is an advantage that the sheet-shaped prepreg can be cut and used as desired in a specific fiber direction to the required portion.

The embodiment of the present invention reflects the composite stacking guidelines generally applied to the optimum design, and designed the stacking order with reference to the results. In addition, according to the embodiment, both a symmetric lamination criterion and a balance lamination criterion may be applied. Symmetrical lamination refers to a case where the angle of the stacking order is vertically symmetric with respect to the intermediate plane. Balanced stacking refers to a case where + θ and -θ are paired regardless of whether they are adjacent in the stacking order.

On the other hand, by applying a 10% rule (that is, 10% rule) it can be set so that the minimum ratio of the 0 ° direction, +45 ° direction, -45 ° direction, 90 ° direction is about 10%. + 45 ° plies and -45 ° plies can be stacked adjacently, and ± 45 ° plies can be stacked on the outer surface. In addition, plies having the same angle may allow stacking of up to four sheets in succession.

5, the first mold fixing part 510-1 and the second mold fixing part 510-2 are reflected from each end of the demolding mold 200 and the supporting part mold 300. . In other words, the mold release part 200 and the support part mold 300 are manufactured in consideration of the mold fixing parts 510-1 and 510-2 at the initial stage of the overall process.

FIG. 6 is a side cross-sectional view illustrating a concept of forming the wing skin layer 500 stacked on the inner mold 400 shown in FIG. 5. Referring to FIG. 6, the skin layer of the wing 500 is molded according to the temperature and pressure determined by the autoclave method after skin deposition is completed.

At this time, the temperature may be maintained at about 125 ° C. for about 90 minutes. In addition, the pressure can be maintained at about 5 bar for about 120 minutes. The temperature and pressure of the autoclave process can be changed depending on the prepreg.

To this end, an OML mold assembly 610 consisting of a lower OML mold 610-1 and an upper OML mold 610-2 is applied to the autoclave method. The lower OML mold 610-1 is disposed at the lower end of the inner mold 400, and the upper OML mold 610-2 is disposed at the upper end of the inner mold 400. The upper OML mold 610-2 and the lower OML mold 610-1 are pressed and matched, thereby forming and curing the wing skin layer 500.

Meanwhile, in addition to the combination of the upper OML mold and the lower OML mold, a combination of the front OML mold and the rear OML mold, or an integral OML mold made of a flexible material may also be applied. The integrated OML mold form is one in which the OML mold is oval, and one end of the oval OML mold is opened or closed. That is, the side cross section is a form in which the handle position is opened or closed in the form of a tennis racket.

In FIG. 6, the inner mold 400 and the wing skin layer 500 surrounding the mold 400 are shown in an elliptical cross section for convenience, but in reality, the airfoil becomes an airfoil.

FIG. 7 is a plan view of removing the demolding mold 200 and processing both sides after the molding and curing of FIG. 6. Referring to FIG. 7, after molding and curing are completed, the integral folding wing tip portion 710 and the wing root portion 720 are processed, and the rotating shaft is attached to the first body portion 110. To create a rotating shaft hole (112). The rotating shaft hole 112 is processed into various shapes such as a cylindrical shape, and the first insertion hole 901 for installing the anti-rotation pin is processed. The upper part of the rotating shaft hole 112 is subjected to a digging process for assembling and bonding the upper rotating shaft. The placer also has a purpose to prevent rotation.

According to the optimization result, since the wing root 720 has a large bending moment, the ratio of about 0 ° plies is the largest. As the bending moment decreases from the wing root portion 720 to the wing tip portion 710, the ratio of 0 ° fly also decreases. The wing tip 710 has a relatively large 90 ° fly rate compared to other areas under the influence of 10% regulation. Laminates have the thickest wing roots and the thinnest wing tips.

7 illustrates an embodiment in which the same thickness is applied from the wing root portion 720 to the wing tip portion 710. That is, the same thickness is applied from the wing root part to the wing tip part, and the external shape sectional drawing of the completed wing | tip is shown. However, if there is a change in the thickness of the wing skin layer 500, a taper or a step must be applied to the inner mold according to the thickness change, or the taper can be applied to the outer shape of the finished wing as a result.

8 is a plan view of processing the hole shaft 112 and the dent of the upper rotary shaft after the machining of FIG. Referring to FIG. 8, an anti-rotation pin 810 is installed inside the rotation shaft hole 112. In particular, the anti-rotation pin 810 is to prevent the upper and lower rotation shafts 920, 930 and the composite portion 300, 500 is relatively rotated. The material of the anti-rotation pin 810 may be a metal, a nonmetal, a plastic / polymer material, a composite material, or the like. The anti-rotation pin 810 may be in the shape of a tetrahedron, hexagonal, cylindrical, or the like.

FIG. 9 is a cross-sectional view of a rotating shaft portion in which the integrated folding wing 100 using the composite material shown in FIG. 1 is assembled with the counterpart 990. Integral folding wing 100 serves as a main structure of the aircraft to support and transmit the lift generated during the flight.

The integral folding wing 100 is folded and initially folded, and then unfolded at a specific angle according to operation. In other words, the pair of integrated foldable wings 100 are symmetrically developed about their respective rotational axes. Therefore, the wing root portion 720 of the integral folding wing 100 should have a pivot, and a mechanical interface such as an upper rotating shaft 920 and a lower rotating shaft 930 for wing mounting is provided. Is reflected.

Referring to FIG. 9, one side of the anti-rotation pin 810 is inserted into the first insertion hole 901 formed in the inner side of the rotating shaft hole 112 and the inner side of the lower rotating shaft 930, and the other part is the other side. The side surface protrudes and is inserted into the second insertion hole 902 formed on the outer surface of the upper rotation shaft 920. The anti-rotation pin 810 is assembled and adhered to the first insertion hole 901 of the rotation shaft hole 112 and the lower rotation shaft 930 and the second insertion hole 902 of the upper rotation shaft 920. That is, the anti-rotation pin 810 is inserted into the second insertion hole 902 (or after the adhesive is applied), and the upper rotary shaft 930 is assembled and adhered to the rotary shaft hole 112.

The upper rotary shaft 920 has a central cross section of a "tt" shape, and the lower rotary shaft 930 for fixing the upper rotary shaft 920 has a donut shape. The second machining surface is formed on the upper rotary shaft 920. The "-" character on the machined surface can be a running track or oval track shape with straight edges, shapes similar to these, and the like. Of course, a first machining surface (not shown), which is a periphery (that is, a shape of which is shown in the rotary shaft hole of FIG. 1), is also formed for this purpose. It may be a track shape or an elliptical track shape having a straight edge, a shape similar to the above, and the like, so as to fit to the machining surface of the upper rotary shaft 920. In other words, the second processing surface has a convex shape, and the first processing surface has a concave shape to conform to each other.

 Similarly, the lower rotary shaft 930 is also assembled and glued to the lower end of the rotary shaft hole 112. Bonding is done using adhesives. As the adhesive, an epoxy adhesive, an acrylic adhesive, a plastic adhesive, a silicone adhesive, or the like may be used.

When the upper rotary shaft 920 and the lower rotary shaft 930 are assembled and fixed, the integrated folding blade 100 and the fixing washer 940 are assembled to the counterpart 990 and fixed with the screw bolt 950. The screw bolt 950 may be made of metal such as stainless steel or aluminum alloy. In addition, a first bearing 950-1 and a second bearing 950-2 are installed to rotate the integrated folding blade 100. In other words, the first bearing 950-1 is disposed below the lower rotation shaft 930, and the second bearing 950-2 is disposed above the fixing washer 940.

10 is a process chart showing the manufacturing process of the integrated folding wing using a composite material according to an embodiment of the present invention. Referring to FIG. 10, a demoulding mold 200 and a support part mold 300 are manufactured and assembled to fabricate the internal mold 400 (steps S1010, S1020, and S1030).

Thereafter, the composite material is laminated on the surface of the internal mold 400 to form the wing skin layer 500, and then molding and curing are performed by a constant pressure and temperature using an autoclave method (step S1040). .

Thereafter, the demolding mold 200 is removed, and processing of the wing tip 710, the wing root 720, and the rotation shaft hole 112 is performed (step S1050).

Subsequently, the upper rotating shaft 920 and the lower rotating shaft 930 and the counterpart 990 are assembled into the rotating shaft hole 112 of the integrated folding wing 100 (step S1060).

FIG. 11 is a graph showing a weight and manufacturability evaluation scale of the unitary folding wing 100 using the composite material shown in FIG. 1. Referring to FIG. 11, carbon fiber / epoxy unidirectional prepreg (SK Chemicals, Korea) and carbon fiber / epoxy woven prepreg (SK Chemicals, Korea) were used as materials of the composite material.

In order to optimize the composite wing, aluminum alloy, which is a metal material that is frequently used in the structure of the aircraft, and one-way and woven prepregs, which are composite materials, were used as candidate materials. Design optimization can be achieved by dividing the application of composite materials into unidirectional tape only (unidirectional tape only), woven prepreg only (plain weave fabric only), and two prepregs mixed (hybrid). Compared.

For prepreg blending, only one-way prepreg was applied in the 0 ° direction and 90 ° direction, and only the fabric type prepreg was applied in the ± 45 ° direction. Design optimization is performed on the basis of material strength and buckling in the same way as structural analysis.

In other words, design optimization aims to calculate design results with a minimum weight and a margin of safety (MS). And manufacturability of design result is evaluated quantitatively. In order to avoid stress concentration of the wing skin layer 500, the rotational axis portion of the wing is excluded. Optimal design was performed by dividing the wing skin into five regions in the longitudinal direction.

Based on the mechanical properties of lamina, the equivalent properties of laminates (ie laminates) for different lamination angle ratios are estimated. Iterative design is applied by applying the equivalent physical properties to determine the effective laminate having the minimum weight, that is, the ratio of each lamination angle and the thickness of the laminate. Based on the effective laminates, candidates for stacking order are generated and iterative design is performed based on the minimum weight.

The final step is to determine the stacking order of each region by considering the ply-drop between the regions.

In general, the composite stacking guidelines, which are widely applied, are applied as the stacking order criteria of the optimum design. In addition, the symmetric stacking and balance stacking standards were also observed. The 10% rule was applied to set the minimum ratios in the 0 ° direction, the ± 45 ° direction, and the 90 ° direction to 10%. + 45 ° plies and -45 ° plies were stacked adjacent to each other and ± 45 ° plies were stacked on the outer surface. Plies with the same angle allowed stacking of up to four sheets in succession.

Referring to FIG. 11, the weight result was normalized based on the aluminum alloy according to the optimum design result, and the fabrication result was normalized based on the one-way prepreg. Compared with aluminum alloys, unidirectional prepregs decreased in weight and woven prepregs increased in weight.

In the case of mixing two types of prepregs, the weight was reduced the most and the manufacturability was the best. The manufacturability evaluation scale was defined as the sum of the number of corners of all plies. This design optimization tendency did not change significantly even in the analysis model reflecting the first body 110 and the rotation axis. The stacking order of the wing skins was determined by reflecting the results of the optimal design study. Based on the stacking sequence design and structural analysis results using a mixture of unidirectional and woven prepregs, the ratios of 0 °, ± 45 ° and 90 ° are 60%, 30% and 10%, respectively, and the thickness is 3 mm to 4 A composite stacking sequence of mm was designed.

On the other hand, the composite wing of the monocoque form is characterized in that there is no inner member such as spar, lip, so that the wing skin layer supports and transmits the load. In small and medium-sized aircraft, such monocoque wings are considered to be more suitable in terms of manufacturing cost and manufacturability.

Compared to the prior art in which a plurality of demolding molds are applied, in one embodiment of the present invention, only a single demolding mold is sufficient. The number of molds affects manufacturing and maintenance costs. As a result, the mold quantity should be minimized in order to manufacture a low cost structure, and the number of demolding molds of the present invention may be ideal. This process design is, of course, possible because of the use of the shaft support as part of the IML mold.

In addition, the composite material in the form of the intermediate material (fabric, prepreg, etc.) is characterized in that it is possible to design a variety of structures according to the stacking order setting. However, due to strict design guidelines, determining the stacking order is not easy. In an embodiment of the present invention, the lamination order of the rotation shaft support unit is illustrated using a sublaminate. Repeated use of sublaminates makes it easier to create or estimate material properties for the design and analysis of structures.

100: integral folding wing
110: first body portion
120: second body portion
200: demoulding mold
300: support mold
500: wing skin layer
810: anti-rotation pin

Claims (20)

In the one-piece folding wing using a composite material,
A first body part 110 having a rotating shaft hole 112 formed at one end thereof; And
And a second body part 120 formed integrally with the other end of the first body part 110.
The first body portion 110,
Support mold 300; And
And a wing skin layer 500 formed by stacking a composite material on the surface of the support part mold 300.
The second body portion 120 is hollow inside, the wing skin layer 500 formed by stacking a composite material is integrally extended,
An upper rotary shaft 920 inserted into and fixed to the rotary shaft hole 112; And a lower rotation shaft 930 for fixing the upper rotation shaft 920.
An anti-rotation pin 810 is installed inside the rotating shaft hole 112 to prevent the upper rotating shaft 920 or the lower rotating shaft 930 from being rotated relative to the rotating shaft hole 112. Integral folding wing using composite materials.
delete delete The method of claim 1,
The wing skin layer 500 is a composite material, characterized in that the composite material is formed on the surface of the inner mold mold 400 is assembled to the removable mold 200 removable removable structure to the support mold 300 Integrated folding wing using.
The method of claim 4, wherein
The detachable structure is a one-piece folding wing using a composite material, characterized in that consisting of the protrusions 210 and the concave portion 310 is matched to the protrusions 210.
The method of claim 5, wherein
The protrusions 210 or the recesses 310 of the release mold 200 are formed with first and second pin holes 211 and 212 in which one end of each of the first and second guide pins 221 and 222 is press-fitted. Integrated folding wing using a composite material characterized in that.
The method of claim 6,
2-1 and 2-2 pinholes 321 and 322, into which the other ends of the first and second guide pins 221 and 222 are inserted, are formed in the recess 310 or the protrusion 210 of the support part mold 300. Integral folding wing using a composite material characterized in that.
The method of claim 4, wherein
The wing skin layer 500 is molded and cured using an autoclave method, and the autoclave method is an OML mold including a lower outer mold line (OML) mold 610-1 and an upper OML mold 610-2. An integrated folding wing using a composite material, characterized by applying an assembly (610), applying an OML mold assembly (610) consisting of a front OML mold and a rear OML mold, or applying an integral OML mold made of a flexible material.
The method of claim 1,
The support part mold 300 is an integral folding wing using a composite material, characterized in that the production using a hot press method.
delete delete The method of claim 1,
The upper rotary shaft 920 having a first machining surface and a shape corresponding thereto on the upper portion of the rotary shaft hole 112 in order to prevent a relative rotational movement of the rotary shaft hole 112 and the upper rotary shaft 920 double. Integrated folding wing using a composite material, characterized in that the second processing surface is formed on the upper portion of the.
The method of claim 12,
The first and second working surfaces are integral folding wings using a composite material, characterized in that the track shape or elliptical track shape having a straight edge.
The method of claim 1,
The inner side of the rotating shaft hole 112 is integral folding wing using a composite material, characterized in that the first insertion hole 901 is inserted into one side of the anti-rotation pin 810 is formed.
The method of claim 14,
Integral folding wing using a composite material, characterized in that the outer surface of the upper rotating shaft 920 is formed with a second insertion hole 902 is inserted into the other side of the anti-rotation pin 810.
The method of claim 14,
The first insertion hole 901 is integral folding wings using a composite material, characterized in that it is formed to extend to the inner portion of the lower rotating shaft (930). The method of claim 1,
The anti-rotation pin 810 is a one-piece folding wing using a composite material, characterized in that one of rectangular, hexagonal, and cylindrical.
The method of claim 4, wherein
The composite material is an integral folding wing using a composite material, characterized in that the material is at least one or more of unidirectional prepreg and woven prepreg.
The method of claim 18,
The one-way prepreg is applied only to the main load direction and its vertical direction, and the fabric-type prepreg is applied to the integral folding wing using a composite material, characterized in that it is applied only to the direction bisecting the main load direction and vertical direction.
In the manufacturing method of the integrated folding wing using a composite material,
The first body portion 110 and the second body portion 120 is formed integrally with the other end of the first body portion 110 is produced,
A rotating shaft hole 112 is formed at one end of the first body 110,
The first body portion 110,
Support mold 300; And
And a wing skin layer 500 formed by stacking a composite material on the surface of the support part mold 300.
The second body portion 120 is hollow inside, the wing skin layer 500 formed by stacking a composite material is integrally extended,
An upper rotary shaft 920 inserted into and fixed to the rotary shaft hole 112; And a lower rotation shaft 930 for fixing the upper rotation shaft 920.
An anti-rotation pin 810 is installed inside the rotating shaft hole 112 to prevent the upper rotating shaft 920 or the lower rotating shaft 930 from being rotated relative to the rotating shaft hole 112. Method of manufacturing integral folding wings using composite materials.

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