KR100551202B1 - Fiber reinforced composite sabots and thereof reinforcement manufacturing method - Google Patents

Abstract

The present invention relates to a fiber-reinforced composite material escape shell for producing a high strength fiber-reinforced composite material (Sabot) for wing stabilized iron shell (or kinetic energy coal / APFSDS; Armor Piercing Fin Stabilized Discarding Sabot) for military use The present invention is to develop a fiber orientation and lamination process that can produce a high-strength fiber-reinforced composite material escape strip having excellent weight ratio strength and low specific gravity to satisfy the performance of the existing aluminum stripping material. Breakaway is under conditions that must withstand very high pressures in the steel and is very complicated in shape. In particular, the breakaway joint coupled with the penetrator and the groove should have a shear strength that can be tolerated in the cavity to ensure viability in the cavity. Therefore, in the present invention, the orientation of the fiber prepreg is renewed in order to provide a method of stacking prepregs that can realize the shear strength of the groove, which is the part where the composite escape part and the penetrator are physically fastened. As an orientation and lamination technology that can be shaped to fit the breakaway shape by applying, a new lamination method in which the breakaway shape is divided into a segment and a subsegment stacking structure and combined is introduced. Therefore, the present invention is expected to be effective in improving the performance of the coal through the weight reduction and material properties of the escape by applying to the manufacturing process of the composite material escape skin.

Description

FIBER REINFORCED COMPOSITE SABOTS AND THEREOF REINFORCEMENT MANUFACTURING METHOD}

1 is a longitudinal cross-sectional view showing the configuration of a conventional escape.

2a to 15 is a view for explaining the configuration and manufacturing method of the fiber-reinforced composite escape peeling according to the present invention,

Figure 2a is a perspective view showing the appearance of the escape skin.

Figure 2b is a perspective view showing a piece constituting the escape.

Figure 2c is a longitudinal sectional view showing a piece constituting the escape.

3 is a perspective view showing a segment forming a piece;

4 is a configuration diagram showing a sub segment forming a segment;

5 is an exploded perspective view showing a laminated structure of sub-segments.

6 is a perspective view showing a plurality of plies constituting a sub segment;

7 is a partially cutaway perspective view of the fiber reinforced composite breakaway skin;

Figure 8 is a perspective view showing a separate form of the two segments are stacked.

9 is an enlarged cross-sectional schematic diagram of FIG. 8.

10 to 12 are views for explaining the process of forming the escape by stacking plies and the shape of the uneven coupling portion,

Figure 10a, b, c is a perspective view, a cross-sectional view and a partially enlarged longitudinal cross-sectional view for explaining the process of forming the escape by stacking plies in the axial direction and the shape of the uneven coupling portion.

Figure 11a, b, c is a perspective view, a cross-sectional view and a partially enlarged longitudinal cross-sectional view for explaining the process of forming the escape by stacking plies in the circumferential direction and the shape of the uneven coupling portion.

Figure 12a, b, c is a perspective view, a cross-sectional view and a partially enlarged longitudinal cross-sectional view for explaining the process of forming the escape by forming the ply radially laminated plies and the shape of the uneven coupling portion.

Figure 13 is a perspective view of one-way carbon fiber / epoxy ply.

14A and 14B are explanatory views of shear strength test.

<Description of the symbols for the main parts of the drawings>

100: escape 110: piece

111: uneven coupling 112: recessed portion

113: front inclined surface 114: rear inclined surface

120: segment 130: sub segment

140: fly 141: ground

142: carbon fiber 143: resin

144: release paper

The present invention relates to a fiber-reinforced composite material escape skin and a method of manufacturing the same, in particular, the sabot is subjected to a very high pressure in the steel, and in the case of the escape skin bonded to the penetrator and the groove, In order to secure the survivability, it is necessary to have the shear strength that can endure in the steel, so the fiber-reinforced composite material escape coating and its manufacture are newly developed and applied to the fiber orientation and lamination method of the composite material escape skin to secure the shear strength of the groove. It is about a method.

In general, wing stabilized iron shell or kinetic energy bombs are ammunitions that destroy targets using the kinetic energy of the penetrator. Among these, the escape escape plays a role of transmitting the propulsion energy generated by the propellant to the penetrator, and has a flying characteristic that is separated from the penetrator in the state after completely transmitting the propulsion energy to the penetrator in front of the muzzle when a shot is fired from the gun. .

In order to improve the performance of wing stabilized armor shells, many studies have been conducted steadily, and one of such research methods is the lightening of the breakaway shell. The purpose of lightening the escape stability of wing stabilized armor shells is to increase the initial speed of the shot with the same propulsion force and to improve the maneuverability by reducing the weight of the shot. In addition, aluminum (Al), which has satisfied this, has been most widely used as a breakaway material until it has to be provided with sufficient strength and toughness at the same time to withstand severe conditions in the steel. Therefore, material researchers have been researching various materials in order to achieve lighter weight than aluminum stripping, adopting fiber-reinforced composite material as the most likely material among them and carrying out research until recently. As a result of this study, in the United States, fiber-reinforced composites are applied to breakaway and placed in practice.

Typically, the breakaway skin is separated into three pieces by the outer diameter of the penetrator, guides the penetrator from the barrel, and simultaneously transmits the propulsion energy to the penetrator to allow the penetrator to fly away from the barrel, and is separated from the penetrator. To prevent pressure leakage in the Therefore, as the propulsion energy generated to launch the penetrator must be transmitted to the penetrator as much as possible, the lighter the weight, the more advantageous the design of the performance of the whole system.

In addition, the breakaway blood is formed in the interface of the breakaway blood and the penetrating uneven coupling portion in order to sufficiently transfer the propulsion energy to the penetrator during firing, the appearance of the breakaway skin is in close contact with the barrel and the pressure generated during firing It is designed to be sealed, and is designed to be separated by air friction during flight without affecting the penetration of the penetrator if the penetrator escapes from the barrel after firing.

1 is a cross-sectional view showing the installation state of the conventional aluminum escape shell, as shown in the penetrating body (1) of the tank or armored vehicle, the penetrating shell (2) of the wing stabilized iron shell bullet coupled with the breakaway shell (3) consisting of three pieces. It is inserted in the form.

The outer diameter portion of the penetrator 2 and the inner diameter portion of the breakaway skin 3 corresponding thereto are formed with uneven coupling portions 2a, 3a in the form of threads or grooves, and the uneven coupling portions 2a, ( 3a) is designed not to be damaged in consideration of shear stress according to the firing energy.

The conventional breakaway skin configured as described above is formed entirely of aluminum, so there is no problem in the durability considering the shear stress required at launch, but there is a problem that the weight is relatively high compared to the composite material. This affects the penetration performance of the penetrator, the penetration rate to the target and the overall performance of the system.

Subsequently, the difference to the present invention of the prior art with respect to the escape of the composite material is as follows.

U.S. Patent 5,640,054 (Sabot segment molding apparatus and method for molding a sabot segment) proposes the development of compression molding dies and radial lamination method of the peel-off composite material. A radial lamination method of wedge shaped section prepregs rather than directional and axial lamination methods is presented, and a compression molding process using the developed mold is presented. However, this patent does not disclose a specific method of stacking the prepreg.

Meanwhile, US Patent No. 5,789,699 (Composite ply architecture for sabot) proposes a more specific stack orientation method of prepreg using radial stacking. That is, a specific orientation sequence of 0 / + / 0 /-/ 0 / and 0/0 / + /-/ 0/0, and a stacked orientation method of repeating them are proposed.

Here, + represents + 30 ° to + 45 °,-represents -30 ° to -45 °, the number represents the angle of orientation, and the sign "/" is used in the same sense as the comma ",". It was used to make it easier to distinguish.

However, how to design the combined segments and sub-segments in such a layered alignment method is a very important technical task, but US Patent No. 5,789,699 only shows the orientation for the specific angle. There is no specific description of the orientation angle, and there is no detailed description of the fiber orientation other than the aforementioned angle.

The present invention has been created to solve the above problems and defects as described above, the prepreg that can realize the maximum shear strength of the concave-convex coupling portion (groove) which is a part that is physically fastened to the penetrating body of the composite escape escape ( The purpose of the present invention is to provide a specific lamination technique in which the ply) orientation and lamination scheme are applied at different orientation angles from the existing techniques.

In addition, another object of the present invention is to provide a breakaway manufacturing method using a sub-segment and the formation process of the segment not developed in the existing technology in detail.

In order to achieve the above object, the present invention is to manufacture a composite material escape by stacking a one-way prepreg fiber, which is a composite material using a radial lamination method, a plurality of sub-segments each overlapping a plurality of plies, respectively A sub-segment forming step of forming into a shape, a segment forming step of forming a plurality of segments by stacking a plurality of sub-segments respectively, and a plurality of segments each formed of a plurality of pieces (preforms) into a predetermined shape And a piece forming step of forming a breakaway skin by combining the plurality of pieces to form a breakaway skin.

More specifically, the present invention provides a sub-segment forming step of forming four or more sub-segments each into a predetermined form by overlapping a plurality of plies, and a segment forming step of forming three or more segments by stacking four or more sub-segments, respectively. And a piece forming step of forming three pieces of three or more segments each formed into a predetermined shape so that the cross section becomes a non-shape and having a central angle of 120 °, and combining the plurality of pieces to form a breakaway skin. It is configured to include a breakaway forming step.

In the sub-segment forming step, the ply is stacked, for example, 7 sheets, and + 30 ° to + 60 ° / 90 ° / -30 ° to -60 ° / 0 ° / -30 based on the axial direction of the set segment, respectively. ° to -60 ° / 90 ° / + 30 ° to + 60 ° or 0 ° / + 30 ° to + 60 ° / 90 ° / 0 ° / 90 ° / -30 ° to -60 ° / 0 ° or 0 ° After orientation lamination at an angle of ++ 30 ° to + 60 ° / 0 ° / 90 ° / 0 ° / -30 ° to -60 ° / 0 °, a cut is formed in a predetermined form.

Further, in the sub-segment forming step, the plies are stacked, for example, 5 sheets, and 90 ° / -30 ° to -60 ° / 0 ° / -30 ° to -60 ° / 90 based on the axial direction of the set segment, respectively. ° or 0 ° / -30 ° to -60 ° / 90 ° / -30 ° to -60 ° / 0 ° or + 30 ° to + 60 ° / 90 ° / 0 ° / 90 ° / -30 ° to -60 Or it is oriented and laminated at an angle of + 30 ° to + 60 ° / 0 ° / 90 ° / 0 ° / -30 ° to -60 °, and is cut and formed into a predetermined shape.

More specifically, the present invention provides a sub-segment forming step of forming nine sub-segments each into seven plies to form a predetermined shape, and a segment forming step of forming nine sub-segments by laminating nine sub-segments, respectively, And a piece forming step of forming three pieces by laminating ten segments each formed into a predetermined shape, and a step of forming a breakaway skin by combining the three pieces.

The unidirectional fiber prepreg is one or more fibers selected from carbon fibers, graphite fibers, and glass fibers, and the base materials of the unidirectional fiber prepregs are thermosetting resins and thermoplastic resins.

The present invention is implemented by introducing a lamination method in which the ply is radially laminated so that the cross section is a fan shape in the prepreg ply lamination related art of the composite material escape. This lamination method is a method of lamination so that the ends of the fibers always face in contact with the penetrator. This lamination method consists of ten segments, each of which consists of nine sub segments so that the pieces have a shape of, for example, 120 degrees. In addition, each subsegment consists of seven layers of unidirectional prepreg layers. Thus, each segment consists of 63 plies. In addition, the raw material used in the embodiment of the present invention is a prepreg of unidirectional carbon fiber / epoxy resin of, for example, T700 grade (tensile strength 700 ksi).

In an embodiment of the present invention will be described with respect to the change in shear strength according to the orientation angle of the fiber.

Hereinafter, with reference to the accompanying drawings, the present invention will be described in detail as follows.

Figures 2a to 14 are views for explaining the configuration and manufacturing method of the fiber-reinforced composite breakaway peeling according to the present invention, Figure 2a is a perspective view showing the appearance of the breakaway peel, Figure 2b is a perspective view showing a piece forming a breakaway peel, respectively 2C is a longitudinal cross-sectional view showing a piece forming a breakaway blood, FIG. 3 is a perspective view showing a segment forming a piece, and FIG. 4 is a configuration diagram showing a subsegment forming a segment, respectively.

First, referring to FIGS. 2A to 4, in FIG. 2A, 100 shows a breakaway blood, in FIGS. 2B and 2C, 110 shows a piece, and in FIG. 3, 120 shows a segment, so that the breakaway 100 shows a piece 110. It consists of three. Each piece 110 may be formed by stacking seven segments 120 as shown in FIG. 2C, but may be formed by stacking three or more segments 120 in consideration of pressure resistance.

4 is an exploded perspective view showing a sub-segment forming a segment, FIG. 5 is an exploded perspective view showing a laminated structure of sub-segments, and FIG. 6 is a perspective view showing a plurality of plies forming a sub-segment. FIG. 7 is a partially cutaway perspective view of the fiber-reinforced composite breakaway skin, FIG. 8 is a perspective view illustrating a state in which two segments are stacked, and FIG. 9 is an enlarged cross-sectional schematic view of FIG. 8.

Hereinafter, referring to FIG. 1 to FIG. 9, the preferred embodiment of the present invention will be described in more detail. The breakaway 100 includes three pieces 110 equally divided at 120 °, and each piece 110. ) Consists of ten segments 120 equally divided into 12 ° angles.

And the segment 120 is composed of nine sub-segments 130 that can be different from each other, as shown in Figure 4, each sub-segment 130 is composed of seven plies 140, each as shown in FIG. .
In addition, as shown in FIG. 2B, the inner circumferential surface of each piece 110 is formed with an uneven portion 111 corresponding to the uneven portion engaging portion of the penetrator, and the uneven portion 112 of the uneven portion 111 is a moving direction of the bullet. That is, the front inclined surface 113 and the rear inclined surface 114 are formed at inclinations of 45 ° and 7 °, respectively, with respect to the longitudinal direction in which the breakaway 100 is advanced.

The segment 120 has a predetermined length, for example, has a width equal to a 12 ° angle, and has a flat cross section when cut in the transverse direction. And the segment 120 is molded in the form which laminated | stacked 9 sub segments 130, respectively, as shown in FIG.

The sub-segments 130 forming the segment 120 are formed by stacking seven plies 140 shown in FIG. 13 and cutting them into a predetermined shape as shown in FIGS. 4 to 6.

The ply 140 is carbon fiber 142 is arranged in one direction on the base paper 141 as shown in Figure 13, the resin 143 is impregnated and attached to a certain thickness, the release paper 144 is attached to the pre-pre In its form. The fabric of the one-way carbon fiber ply 140 is manufactured and supplied in a predetermined size (for example, 100 mm x 100 mm).

Separating the base paper 141 and the release paper 144 of each ply 140, and if the seven sheets are stacked, each ply 140 has an adhesive, so seven plies 140 are like each other Adheres tightly.

Thus, the seven plies 140 bonded to each other are cut by a cutting machine to manufacture various types of sub-segments 130 as shown in FIG. 4.

Since each sub-segment 130 has a longitudinal section of the segment 120 as shown in FIGS. 2C, 4, and 9, the sub-segment 130 attached to both outer sides of the segment 120 includes the segment 120. The sub-segments 130 attached to the inner side may have a partial form, such as both sides of the outer side surface thereof.

As described above, nine sub-segments 130 formed in various shapes as shown in FIG. 4 according to the segment 120 are put in a mold, stacked together, and bonded to each other to form a segment 120 as illustrated in FIG. 3.

When the plurality of plies 140 are stacked to form the sub-segment 130 and the plurality of sub-segments 130 are stacked to form the segment 120, a predetermined pressure is applied to the crimping mold as necessary. Overtemperature is applied to form a tighter and firmer mold.

In the process of forming the ply 140 to form the sub-segment 130 by stacking the sub-segments 130, forming the segment 120 by laminating the sub-segments 130, and stacking the segments 120 to form the piece 110. What is important to satisfy the required mechanical strength of the breakaway 100 is the orientation method of the ply 140.

10 to 12 are views for explaining the process of forming a breakaway skin by stacking plies and the concave-convex coupling portion, Figure 10a, b, c is a process of forming a breakaway skin by stacking plies in the axial direction A perspective view, a cross-sectional view and a partially enlarged longitudinal cross-sectional view for explaining the shape of the coupling portion, Figures 11a, b, c is a perspective view, a cross-sectional view and a portion for explaining the process of forming the escape by stacking plies in the circumferential direction and the shape of the uneven coupling portion 12a, b, and c show a perspective view, a cross-sectional view, and a partially enlarged longitudinal cross-sectional view for explaining a process of forming a breakaway ply by radially stacking plies and a concave-convex coupling portion, respectively.

In stacking the ply 140, first, as shown in FIGS. 10A, B, and C, the ply 140 is arranged in an axial direction (length direction) with respect to the set piece 110 (that is, one direction). There is a method of forming the sub-segment 130 by arranging the directions of the carbon fibers 142 of the carbon fiber ply 140 to coincide with the axial direction.

11A, B, and C, the ply 140 is arranged (provisionally) in the circumferential direction with respect to the set piece 110, that is, each carbon fiber 142 of the one-way carbon fiber ply 140. ) And the sub-segment 130 is formed by winding in the circumferential direction.

12a, b, and c, the ply 140 is arranged radially relative to the set piece 110, ie, each carbon fiber 142 of the one-way carbon fiber ply 140. ) And the sub-segment 130 is formed by arranging the directions in a radially matched manner.

As a result of the performance test among the alignment method of the ply 140 as described above, when the ply 140 is oriented in the axial direction as shown in FIGS. 10a, b, and c, the unevenness of each piece 110 is as shown in FIG. The plurality of carbon fibers 142 are arranged in the axial direction curved in the coupling portion 111, there is a problem that the corner portion of the uneven coupling portion 111 is not formed in the set form, there is a post-processing the uneven coupling portion 111 While cutting a plurality of carbon fibers 142, there was a problem that the strength is lowered.

In addition, when the ply 140 is oriented in the circumferential direction as shown in FIGS. 11A, 11B and 11C, a plurality of carbon fibers 142 may be formed on the uneven coupling portion 111 of each piece 110 as shown in FIGS. 11C and 15A. ) Is formed in a faithfully filled form, but in the state in which the escape arm 100 is coupled to the penetrator of the wing stabilized iron shell, the escape arm 100 and the penetrating interlocking joint 111 interlocked with each other in the state of being mounted on the barrel. When the pressure is applied, the carbon fiber 142 of the concave-convex coupling portion 111 is pushed easily damaged form has a weak pressure resistance strength.

12A, B, and C, when the ply 140 is radially oriented, as shown in FIG. 12C, a plurality of carbon fibers 142 are faithful to the uneven coupling portion 111 of each piece 110. It is formed in a stacked form, and accordingly pressure is applied to the uneven coupling portion 111 engaged with the breakaway skin 100 and the penetrator while being mounted on the barrel in a form in which the breakaway shell 100 is coupled to the penetrator of the wing stabilized iron shell. When acting, the carbon fiber 142 of the uneven coupling portion 111 is not pushed and damaged, and the pressure resistance is increased.

As described above, in manufacturing the composite material escape shell 100 by stacking a plurality of plies 140, the mold (s) in the forming of the sub-segment 130, the segment 120, the piece 110, and the escape shell 100 is performed. mold) is used, and the material is put into a mold, and manufactured by laminating and joining by applying a predetermined pressure and temperature.

In addition, in forming the concave-convex coupling part 111 of the breakaway skin 100, a method of forming in a molding step using a mold and an inner diameter portion of the inner diameter of the breakaway skin 100 in a step of molding using a mold are provided. After forming into a flat curved surface, there is a method of forming the concave-convex coupling portion 111 by machining in a later process can be used.

Referring to the above description, the method of manufacturing a fiber-reinforced composite material escape shell according to the present invention is separated and coupled to the outer diameter of the shell penetrator to guide the penetrator to the barrel and to deliver the propulsion energy to the penetrator, The sub-segment forming step of forming a predetermined number of sub-segments 130 of a predetermined type by overlapping a plurality of plies 140 in manufacturing the escape shell 100 separated from the penetrator while flying, and the plurality of subs A segment forming step of stacking the segments 130 to form a predetermined number of segments 120, a piece forming step of stacking the plurality of segments 120 to form a predetermined number of pieces 110, and the plurality of pieces It is configured to include a breakaway forming step of coalescing (110) to form a breakaway blood (100).

12A, 12B, and 12C, in the sub-segment forming step, each ply 140 has a longitudinal direction of the carbon fiber 142 of the ply 140 based on the set segment 120. After the 90 ° direction orthogonal to the axial direction of the 120, that is, the longitudinal direction of the carbon fiber 142 is laminated in the form arranged in the radial direction of the segment 120, the sub-segment 130 having a predetermined shape as shown in FIG. Is formed by cutting.

One specific form of this sub-segment forming step is the carbon fiber 142 of the ply 140 based on the segment 120 in which at least one of the plies 140 is set as shown in FIGS. 5, 6 and 12a. The 90 ° direction in which the longitudinal direction is orthogonal to the axial direction of the segment 120, that is, the longitudinal direction of the carbon fiber 142 is disposed in the radial direction of the segment 120, and the other part is + 30 ° to +60 to the right. It is arranged to be inclined at an angle (eg, + 45 °), the other part is arranged to be inclined from -30 ° to -60 ° (eg -45 °), while the other part is carbon fiber 142 of the ply 140. After the laminate is stacked so as to be disposed in an axial direction of 0 °, the substrate is cut into sub segments 130 having a predetermined shape.

In more detail, the method of manufacturing a fiber-reinforced composite material avoiding skin of the present invention comprises forming a sub-segment step of forming nine sub-segments 130 in a predetermined form by overlapping seven plies 140 respectively. A segment forming step of forming the segments 120 by stacking nine sub-segments 130 respectively, and a piece forming step of forming the three pieces 110 by stacking ten segments 120 each having a predetermined shape. And a breakaway forming step of forming the breakaway skin 100 by merging the three pieces 110.

In the forming of the sub-segment, in forming the sub-segment 130 by stacking the 7 plies 140, the 7 plies 140 are each + based on the axial direction of the set segment 120. After orientation lamination at an angle of / 90 /-/ 0 /-/ 90 / +, it is cut and formed into a predetermined shape.
Here, 0 means that the longitudinal direction of the carbon fiber 142 of the ply 140 is disposed in the 0 ° direction coinciding with the axial direction with respect to the axial direction of the segment 120, + is the right (clock Direction), + 30 ° to + 60 °,-means to be inclined -30 ° to -60 ° to the left (counterclockwise), 90 means to be arranged orthogonally in the 90 ° direction. The symbol "/" is used to mean commas "," to make it easier to distinguish adjacent numbers.

In this embodiment of the present invention, first, after forming a composite of various fiber orientation in order to determine the proper orientation of the fibers of the sub-segment 130, the groove shear strength, which is a machined test piece, was measured. After molding, the average density was 1.60g / cm ³ or less, and the fiber content was more than 60% by volume ratio.

14A and 14B are schematic views showing the shape of the test piece 110 and the groove combined with the penetrator-shaped metal punch 170 for measuring the shear strength of the uneven coupling portion of the breakaway skin.

In addition, the shear strengths of the grooves according to the fiber orientations of the sub-segments 130 were different from each other as shown in the following table. In this table, as described above, 0 means that the longitudinal direction of the carbon fiber 142 of the ply 140 is disposed in the 0 ° direction coinciding with the axial direction with respect to the axial direction of the segment 120, and + is + 30 ° to + 60 ° to the right,-means to be inclined to -30 ° to -60 ° to the left, and 90 means to be orthogonally disposed in the 90 ° direction.

Shear Strength of Grooves with Fiber Orientation

material Stacking orientation angle (°) Uneven joint shear strength (Mpa)    Unidirectional Carbon Fiber / Epoxy Prepreg 0 22 90 112 + 129 - 147 +/- 170 -/ 90 190 + / 90 /-/ 0 /-/ 90 / + 220 Aluminum (Al) - 190

In other words, the shear strength was 129Mpa and 147Mpa at the fiber orientation lamination angles of '-' and '+', respectively, and 170Mpa and 190Mpa for '+/-' and '-/ 90', respectively. In particular, the composite sheared fiber with '+ / 90 /-/ 0 /-/ 90 / +' showed the highest shear strength of 220 Mpa, which is higher than the groove shear strength of the existing aluminum material. I could confirm it.

The present invention as described above has the effect of replacing the existing product by developing a manufacturing process of the escape from satisfying the performance of the existing aluminum material. That is, the manufacturing method of the composite material used in the prior art can not satisfy the requirements of the escape avoidance, the product can be implemented due to the present invention. This, in turn, has the effect of improving the performance of the bullet through the weight of the final escape avoidance and material properties.

Claims (14)

In manufacturing a composite material escape by stacking a unidirectional prepreg fiber which is a composite material by a radial lamination method, a sub-segment forming step of forming a plurality of sub-segments, each of which overlaps a plurality of plies to form a predetermined shape, A segment forming step of forming segments by laminating a plurality of sub-segments respectively; a piece forming step of forming a plurality of pieces by laminating a plurality of segments each formed into a predetermined shape; and a plurality of pieces to coalesce the escape pieces. A method for producing a fiber-reinforced composite material breakaway skin comprising a step of forming a breakaway forming step. The method of claim 1, wherein the sub-segment forming step of forming four or more sub-segments, respectively, in a predetermined form by overlapping a plurality of plies, and a segment forming step of forming three or more segments by laminating four or more sub-segments respectively. And a piece forming step of forming three pieces of three or more segments each formed into a predetermined shape so that the cross section becomes non-shaped and having a central angle of 120 °, and combining the plurality of pieces to form a breakaway skin. Method for producing a fiber-reinforced composite material escape peeling comprising the step of forming a peeling off. The method of claim 2, wherein the sub-segment forming step of forming nine sub-segments each into seven plies to form a predetermined shape, a segment forming step of forming ten sub-segments by laminating nine sub-segments, and the three A fiber-forming composite comprising a piece forming step of stacking ten pieces each of which is formed into a predetermined shape, and a stripping step of combining the three pieces to form a breakaway skin; Method of producing breakaway skin. The fiber according to any one of claims 1 to 3, wherein the fiber of the unidirectional fiber prepreg is at least one fiber selected from carbon fiber, graphite fiber and glass fiber, and the base material of the unidirectional fiber prepreg is a thermosetting resin and A method for producing a fiber-reinforced composite material leaving skin, characterized in that the thermoplastic resin. In the composite material escape skin obtained by laminating the unidirectional prepreg fiber, which is a composite material, in a radial lamination method, three pieces formed in a fan shape having a center angle of 120 ° are formed by dividing the composite material escape skin into three parts. The composite material escape skin is formed, and each piece is formed by stacking three or more segments each formed into a predetermined shape, and each segment is formed by stacking four or more sub-segments, respectively, and each of the sub-segments Breakaway fiber reinforced composite material, characterized in that formed in a predetermined form by overlapping a plurality of plies, respectively. The method of claim 5, wherein the nine sub-segments are formed in a predetermined form by overlapping each of the seven plies, 10 segments are formed by stacking nine sub-segments each, three pieces each formed into a predetermined form 10 Formed by stacking two segments, wherein the three pieces are coalesced to form a breakaway skin. The method of claim 5, wherein in the sub-segment forming step, the ply is stacked 7 sheets, and the longitudinal direction of the carbon fibers of the ply is + 30 ° to + 60 ° / 90 ° with respect to the axis direction of the segment, respectively, based on the set segment. Fiber reinforcement, characterized in that the orientation laminated at an angle of --30 ° to -60 ° / 0 ° / -30 ° to -60 ° / 90 ° / +30 ° to +60 °, and then cut into a predetermined shape Method for producing composite escape The method of claim 5, wherein in the sub-segment forming step, the ply is stacked 7 sheets, and the longitudinal direction of the carbon fiber of the ply is 0 ° / + 30 ° to + 60 ° with respect to the axial direction of the segment, respectively, based on the set segment. A method for producing a fiber-reinforced composite material escape coating, characterized in that the substrate is oriented and laminated at an angle of / 90 ° / 0 ° / 90 ° / -30 ° to -60 ° / 0 °, and cut into a predetermined shape. The method of claim 5, wherein in the sub-segment forming step, the ply is stacked 7 sheets, and the longitudinal direction of the carbon fiber of the ply is 0 ° / + 30 ° to + 60 ° with respect to the axial direction of the segment, respectively, based on the set segment. A method for producing a fiber-reinforced composite material avoiding skin, characterized in that the substrate is oriented and laminated at an angle of 0 ° / 90 ° / 0 ° / -30 ° to -60 ° / 0 °, and cut into a predetermined shape. The method of claim 5, wherein the ply is stacked five sheets in the sub-segment forming step, the longitudinal direction of the carbon fiber of the ply is 90 ° /-30 ° to -60 ° with respect to the axis direction of the segment, respectively, based on the set segment A method for producing a fiber-reinforced composite material leaving skin, characterized in that the cut is formed in a predetermined form after the alignment laminated at an angle of / 0 ° / -30 ° to -60 ° / 90 °. According to claim 5, wherein in the sub-segment forming step, the ply is stacked five sheets, the longitudinal direction of the carbon fiber of the ply is 0 ° /-30 ° to -60 ° with respect to the axis direction of the segment, respectively, based on the set segment A method of producing a fiber-reinforced composite material leaving skin, characterized in that the cut is formed in a predetermined shape after the orientation laminated at an angle of / 90 ° / -30 ° to -60 ° / 0 °. According to claim 5, wherein the ply is stacked in the sub-segment forming step 5 sheets, the longitudinal direction of the carbon fiber of the ply is +30 ° to +60 ° / 90 ° respectively with respect to the axis direction of the segment based on the set segment A method for producing a fiber-reinforced composite material escape coating, characterized in that the substrate is oriented and laminated at an angle of 0 ° / 90 ° / -30 ° to -60 ° and cut into a predetermined shape. According to claim 5, wherein the ply is stacked in the sub-segment forming step 5 sheets, the longitudinal direction of the carbon fiber of the ply is +30 ° to +60 ° / 0 ° respectively with respect to the axis direction of the segment based on the set segment A method for producing a fiber-reinforced composite material leaving skin, characterized in that the cut is formed in a predetermined form after the orientation laminated at an angle of / 90 ° / 0 ° / -30 ° to -60 °. The fiber of any one of claims 5 to 13, wherein the fiber of the unidirectional fiber prepreg is at least one fiber selected from carbon fiber, graphite fiber, and glass fiber, and the base material of the unidirectional fiber prepreg is a thermosetting resin. And a thermoplastic resin, wherein the fiber-reinforced composite material escapes.

Images