JP3822182B2 - Manufacturing method of composite material honeycomb sandwich structure - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a method for manufacturing a composite material honeycomb sandwich structure in which a composite material face plate is bonded to both surfaces of a honeycomb core.
[0002]
[Prior art]
For structural parts such as aircraft and automobiles, a composite honeycomb sandwich structure that is lightweight and excellent in rigidity is frequently used. This composite material honeycomb sandwich structure has a structure in which composite face plates are bonded to both surfaces of a honeycomb core.
[0003]
FIG. 9 is a schematic diagram for explaining one step of a method for producing a conventional composite material honeycomb sandwich structure. In such a conventional method for manufacturing a honeycomb sandwich structure of a composite material, a required number of uncured prepregs in which reinforcing fibers are impregnated with a thermosetting synthetic resin are laminated to form two prepreg laminated face plates 101 and 102, respectively. These prepreg laminated face plates 101 and 102 are coated so as to sandwich the honeycomb core 103 whose end is tapered, and the uncured honeycomb sandwich structure 104 thus obtained is applied to a bag film (not shown). After the coating, the bag film is pressed and heated in an autoclave to cure the prepreg laminated face plates 101 and 102 and bond the prepreg laminated face plates 101 and 102 and the honeycomb core 103 substantially simultaneously. This is called the cocure molding method.
[0004]
In such a conventional composite material honeycomb sandwich structure manufacturing method, the end of the honeycomb core 103 is formed in a taper shape. Therefore, as shown in FIG. Pressure in a direction perpendicular to the tapered surface acts on the tapered portion 105 of the cured honeycomb sandwich structure 104. As a result, a force in the direction of increasing the thickness of the taper portion 105 is applied to the honeycomb core 103, which causes the honeycomb core to slide on the prepreg laminated face plate 101 in which the thermosetting synthetic resin is flexible because it is uncured. As shown in FIG. 9B, the honeycomb core 103 may be partially crushed, resulting in manufacturing defects.
[0005]
In addition, the composite material honeycomb sandwich structure may require partial increase in strength depending on the intended use. FIG. 10 is a perspective view schematically showing a configuration of a prepreg laminated face plate 101 used in a conventional composite material honeycomb sandwich structure. As shown in FIG. 10, in such a case, a prepreg 106 having a linear end at the portion where the strength of the lower prepreg laminated face plate 101 is increased is further laminated to partially increase the number of laminated layers. This is dealt with by providing an up unit 107.
[0006]
FIG. 11 is a cross-sectional view illustrating a composite material honeycomb sandwich structure provided with a ply-up portion 107. When such a ply-up portion 107 is provided, as shown in FIG. 11, the honeycomb core 103 is placed on the surface having the step portion 108 of the prepreg laminated face plate 101 to form an uncured honeycomb sandwich structure 104, In contrast, a heating / pressurizing process is performed. However, in the vicinity of the stepped portion 108 provided in a straight line, the honeycomb core 103 is separated from the prepreg laminated face plate 101 due to the step, so that the honeycomb core 103 easily slips due to pressurization, and the above-described manufacturing defects are particularly noticeable. Was.
[0007]
In order to eliminate the manufacturing defect of such a composite honeycomb sandwich structure, the synthetic resin is filled in the cells in the outer peripheral portion of the honeycomb core, this is cured, and a pin or a bolt is passed through the through hole provided in the synthetic resin, As a result, a method of preventing the honeycomb core from slipping by fixing the uncured honeycomb sandwich structure to the mounting table (see Patent Document 1), and a plate-like elasticity in the surplus portion where the prepreg laminated face plates covering the honeycomb core overlap each other. Place the member and the presser member, or secure the width of the surplus part more than a predetermined dimension, increase the frictional force between the prepreg laminated face plates due to the weight of the presser member, and the edge effect of the presser member, or surplus Proposed is a method for preventing the honeycomb core from slipping by increasing the frictional force between the prepreg laminated face plates due to the weight of the part (see Patent Document 2).
[0008]
[Patent Document 1]
Japanese Patent No. 257397 [Patent Document 2]
Japanese Patent Laid-Open No. 2001-150575
[Problems to be solved by the invention]
However, in the conventional method for manufacturing a honeycomb sandwich structure of a composite material disclosed in Patent Document 1, a synthetic resin is filled in the cells in the outer peripheral portion of the honeycomb core, and this is used to cure the prepreg laminated faceplate and to prepreg laminate. It is necessary to cure prior to adhesion between the face plate and the honeycomb core, resulting in troublesome work and a long manufacturing time.
[0010]
In addition, it is not preferable to increase the surplus portion (solid portion) of the outer peripheral portion of the composite material honeycomb sandwich structure with respect to the component dimensions from the viewpoint of securing rigidity, and the manufacturing cost increases if the surplus portion is cut off. Although the surplus portion is required to be as small as possible, the conventional method for manufacturing a honeycomb sandwich structure disclosed in Patent Document 2 must ensure a large surplus portion. I do not get. In addition, since dedicated jigs such as an elastic member and a pressing member are required, the manufacturing cost is high.
[0011]
The present invention has been made in view of such circumstances, and while preventing slippage of the honeycomb core, it is possible to reduce labor and manufacturing time as compared with the prior art, and to reduce the surplus portion as much as possible. It is an object of the present invention to provide a method for manufacturing a composite honeycomb sandwich structure that can be reduced in size and does not require a special dedicated jig.
[0012]
[Means for Solving the Problems]
In order to solve the above-described problems, a method for manufacturing a composite honeycomb sandwich structure according to the present invention includes an uncured prepreg in which a reinforcing fiber is impregnated with a thermosetting synthetic resin and an uncured end having a non-linear shape. A lamination step of laminating prepregs in a step-like manner, and a surface having a step portion of the first prepreg laminated face plate formed in the lamination step is superimposed on one surface of the honeycomb core having a tapered end, and the other surface of the honeycomb core A coating step in which a separately formed second prepreg laminated face plate is closely attached and the honeycomb core is sandwiched between the first and second prepreg laminated face plates, and an uncured honeycomb sandwich structure formed by the coating step The first and second prepreg laminated face plates are cured, and the first and second prepreg laminated face plates and the honeycomb core are heated. Having substantially a curing bonding step for simultaneously bonding and.
[0013]
As a result, the step shape of the first prepreg laminated face plate becomes non-linear, and the edge area of the step portion that is strongly pressed against the honeycomb core becomes larger than that of the straight shape step portion, so that the honeycomb core slip is suppressed. The In addition, since the step shape is non-linear, the cells of the honeycomb core are deformed so as to follow the step shape, and the step portion and the honeycomb core mesh with each other, thereby suppressing the slip of the honeycomb core. .
[0014]
Furthermore, since the prepreg whose end portion has a non-linear shape is simply laminated in a stepped manner on the uncured prepreg, it is possible to reduce labor and manufacturing time as compared with the conventional method, and to reduce the surplus portion. Can be made as small as possible, and no special dedicated jig is required.
[0015]
In this case, it is preferable to laminate an uncured prepreg whose end portion is corrugated on the uncured prepreg in the laminating step.
[0016]
In this case, the waveform is preferably a substantially trapezoidal wave, and more preferably, the inclination angle θ of the inclined portion of the substantially trapezoidal wave satisfies 90 ° <θ ≦ 135 °.
[0017]
In the said invention, the said waveform can be made into a substantially rectangular wave, a substantially sine wave, or a substantially triangular wave.
[0018]
In the above invention, the corrugated concave portion of the uncured prepreg having a corrugated end is set to a length corresponding to 5 to 20 honeycomb cells of the honeycomb core, and the corrugation amplitude is set to a length corresponding to 1 to 5 honeycomb cells. Preferably.
[0019]
In the said invention, it is preferable to laminate | stack an uncured prepreg so that the lamination | stacking step part of a prepreg may be located in the taper part vicinity of a honeycomb core at the said lamination process.
[0020]
In the above invention, in the covering step, a film-like adhesive is interposed between the first and second prepreg laminated face plates and the honeycomb core, and the honeycomb core is formed by the first and second prepreg laminated face plates. It can also coat | cover so that it may be pinched | interposed.
[0021]
In the above-mentioned invention, it is also possible to cover the uncured honeycomb sandwich structure with a bag film and to vacuum the inside of the bag film in the curing and bonding step.
[0022]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, a method for producing a composite material honeycomb sandwich structure according to an embodiment of the present invention will be specifically described with reference to the drawings.
[0023]
FIG. 1 is a perspective view for explaining an example of a stacking step of a method for manufacturing a composite material honeycomb sandwich structure according to an embodiment of the present invention. The prepreg 1 used in the embodiment of the present invention is a synthetic resin (thermosetting) which has a property of curing in response to heat on a woven fabric of reinforcing fibers such as carbon fiber, glass fiber, aramid fiber, and SiC fiber. Synthetic resin) and is formed into a sheet shape. In addition, the prepreg 1 was impregnated with a thermosetting synthetic resin in a reinforced fabric aligned in one direction, in addition to a woven fabric in which reinforcing fibers were woven so as to cross each other and impregnated with a thermosetting synthetic resin. Things can also be used. In the laminating process according to the present embodiment, first, the prepreg 1 is cut into a required size and shape, and a required number of layers are laminated, and the end portion is formed in a non-linear shape. A prepreg 2 having a smaller area than the uppermost part of the laminate is laminated and laminated to obtain a first prepreg laminated face plate 3.
[0024]
At this time, if it is necessary to partially increase the strength in the composite material honeycomb sandwich structure, as shown in FIG. 1, a prepreg 2 (for ply-up) for increasing the number of laminated portions where the reinforcement is required. The end of the can be non-linear. Thus, the 1st prepreg laminated surface board 3 which has the ply-up part 12 in which the step part 11 became non-linear shape can be comprised.
[0025]
FIG. 2 is a perspective view for explaining another example of the stacking step of the method for manufacturing the composite material honeycomb sandwich structure according to the embodiment of the present invention. When the composite honeycomb sandwich structure does not particularly require a portion where the strength is increased, as shown in FIG. 2, a strip-shaped prepreg 2a having an end having a non-linear shape is stacked on the prepreg 1 and laminated. The prepreg laminated face plate 3a is used. In the following description, a method of manufacturing a composite honeycomb sandwich structure using the first prepreg laminated face plate 3 shown in FIG. 1 will be described. However, the first prepreg laminated face plate 3a shown in FIG. The procedure is the same when used.
[0026]
FIG. 3 is a schematic side view showing an outline of the covering step and the curing and bonding step of the method for manufacturing a composite material honeycomb sandwich structure according to the embodiment of the present invention. The first prepreg laminated face plate 3 formed in the laminating step has a surface having a step portion 11 (see FIG. 1) on a forming jig having a flat or curved mounting surface, that is, an end portion having a non-linear shape. The surface to which the prepreg 2 is exposed is placed on the upper side (not shown). Then, the honeycomb core 4 is mounted on the first prepreg laminated face plate 3 so that the upper surface (the surface having the step portion 11) of the first prepreg laminated face plate 3 is aligned with the lower surface of the honeycomb core 4 having an end tapered. Further, a second prepreg laminated face plate 5 that is separately formed is placed thereon. Thus, the honeycomb core 4 is covered with the first prepreg laminated face plate 3 and the second prepreg laminated face plate 5. Note that the second prepreg laminated face plate 5 is formed by laminating the necessary number of the prepregs 1 described above, and the second prepreg laminated face plate 5 may have a configuration in which a stepped portion such as the first prepreg laminated face plate 3 is provided on either side. Alternatively, a configuration in which a step portion is not provided on either side may be used.
[0027]
At this time, the honeycomb core 4 is mounted on the first prepreg laminated face plate 3 so that the height of the surface of the honeycomb core 4 increases in the step portion 11 in the direction in which the taper thickness of the honeycomb core 4 decreases. Placed. Note that the direction of the stepped portion 11 is not limited to this, and the first prepreg is formed so that the surface height thereof is increased by one step in the stepped portion 11 in the direction in which the taper thickness of the honeycomb core 4 increases. The honeycomb core 4 may be placed on the laminated face plate 3.
[0028]
In such a covering step, as shown in FIG. 3A, a film-like film is formed between the first prepreg laminated surface plate 3 and the honeycomb core 4 and between the second prepreg laminated surface plate 5 and the honeycomb core 4, respectively. An uncured honeycomb sandwich structure 7a may be formed with an adhesive 6 interposed therebetween. As shown in FIG. 3 (b), the first prepreg laminated face plate 3 and the second prepreg laminated face plate 5 are connected to the honeycomb core 4 respectively. The uncured honeycomb sandwich structure 7b may be formed by directly adhering to the substrate. The adhesive 6 is made of an uncured thermosetting synthetic resin.
[0029]
FIG. 4 is a schematic side view for explaining the outline of the curing and bonding step of the method for manufacturing the composite material honeycomb sandwich structure according to the embodiment of the present invention. The uncured honeycomb sandwich structure 7a (7b) is covered with a nylon bag film 8, and the bag film 8 is put together in an autoclave (not shown). Then, the bag film 8 is pressurized and heated by the autoclave to cure the first prepreg laminated face plate 3 and the second prepreg laminated face plate 5, the first prepreg laminated face plate 3, the second prepreg laminated face plate 5, and the honeycomb core. Bonding of 4 proceeds almost simultaneously. As shown in FIG. 4, at this time, the inside of the bag film 8 may be evacuated, and the pressurization / heating treatment may be performed, or the evacuation may be performed without performing the evacuation.
[0030]
Here, when an adhesive 6 is interposed between the first prepreg laminated face plate 3 and the second prepreg laminated face plate 5 and the honeycomb core 4 as shown in FIG. The first prepreg laminated face plate 3 and the second prepreg laminated face plate 5 are bonded to the honeycomb core 4.
[0031]
Further, as shown in FIG. 3B, when the first prepreg laminated face plate 3 and the second prepreg laminated face plate 5 and the honeycomb core 4 are in direct contact, the first prepreg laminated face plate 3 is heated by autoclave. And the thermosetting synthetic resin contained in each of the second prepreg laminated face plate 5 is softened and oozed out once, and the thermosetting synthetic resin is thermally cured, whereby the first prepreg laminated face plate 3 and the second prepreg laminated face plate 5 5 and the honeycomb core 4 are bonded to each other.
[0032]
In such a curing and bonding step, the viscosity of the thermosetting synthetic resin contained in the first prepreg laminated face plate 3 is temporarily reduced by heating, and the honeycomb core 4 placed thereon becomes slippery. Due to the taper of the outer edge of the uncured honeycomb sandwich structure, a force is applied to the honeycomb core 4 in a direction in which the thickness of the taper increases. The surface of the first prepreg laminated face plate 3 is stepped in this direction. 11, the honeycomb cell in the vicinity of the step portion 11 of the honeycomb core 4 is pressed against the edge region of the step portion 11. At this time, since the step portion 11 of the first prepreg laminated face plate 3 has a non-linear shape, the honeycomb cells in the vicinity of the step portion 11 of the honeycomb core 4 are deformed along this shape, and more portions are formed. The wall portion of the honeycomb cell is brought into contact with the edge region of the step portion 11 and the corrugated step portion 11 and the honeycomb core 4 are engaged with each other, so that the honeycomb core 4 is prevented from slipping.
[0033]
Further, as described above, when the composite material honeycomb sandwich structure is manufactured by using the first prepreg laminated face plate 3a not provided with the ply-up portion, as shown in FIG. The prepreg 2a is laminated on the uppermost stage of the first prepreg laminated face plate 3a. At this time, the first prepreg laminated face board 3a is preferably configured so that the stepped part 11a is positioned in the vicinity of the tapered part of the honeycomb core 4. This is because a lateral force acts in the vicinity of the taper portion of the honeycomb core 4, and when the ply-up portion is not provided, the honeycomb cells are often crushed near the taper portion. Further, in this case, by forming the prepreg 2a in the shape of a band as shown in FIG. 2, it is possible to prevent the honeycomb cells from being crushed while reducing the weight of the manufactured composite honeycomb sandwich structure as much as possible. . However, it is needless to say that the prepreg 2a may be a wide face plate shape instead of a strip shape.
[0034]
In this way, the first prepreg laminated face plate 3 and the second prepreg laminated face plate 5 are cured, and the first prepreg laminated face plate 3, the second prepreg laminated face plate 5, and the honeycomb core 4 are bonded together, whereby the composite material honeycomb sandwich is obtained. The structure is complete.
[0035]
Here, FIG. 1 shows a case where the end shape of the prepreg 2 for ply-up is a substantially trapezoidal wave. FIG. 2 shows a case where the end portion shape of the prepreg 2a is a substantially sine wave. Thus, it is preferable that the non-linear shape of the end part of the prepregs 2 and 2a is a waveform. This is because the end portions of the prepregs 2, 2 a have a wave shape, so that the end portions regularly repeat irregularities for each predetermined length, and the step portions 11 on which the above-described honeycomb cell wall portions abut, This is because the size of the edge region 11a is substantially uniform over the entire length of the end portions of the prepregs 2 and 2a, and the occurrence of a portion where the honeycomb core 4 is easily slipped is prevented.
[0036]
FIG. 5 is a plan view showing details of the end shape of the prepreg 2 shown in FIG. End of the prepreg 2 as shown in FIG. 1, as shown in FIG. 5, the inclination angle theta is for the wavelength direction of the inclined portion 9 of substantially trapezoidal wave, preferably satisfies 90 ° <θ ≦ 135 °. This is because the honeycomb core 4 slides in the sliding direction indicated by an arrow in the figure, and in order to deform the honeycomb cells of the honeycomb core 4 into a shape along the inclined portion 9 by minute sliding, the sliding direction of the honeycomb core 4 This is because it is considered desirable that the inclined portions 9 face each other at a certain angle.
[0037]
In addition, the length of the concave portion of the trapezoidal wave is preferably 5 to 20 honeycomb cells of the honeycomb core 4 and the amplitude of the waveform is preferably 1 to 5 honeycomb cells. This is because if the size of the concave portion is about one honeycomb cell, the honeycomb cell may protrude from the concave portion when the honeycomb core 4 slips, and it is considered that the sliding cannot be effectively prevented. This is because a large straight portion is included in the vicinity of the center of the recess, and the probability that slippage occurs in this portion increases.
[0038]
6 and 7 are perspective views showing another example of the prepreg laminated face plate used for manufacturing the composite material honeycomb sandwich structure. In the method for manufacturing the composite material honeycomb sandwich structure according to the embodiment of the present invention, as shown in FIGS. 6 and 7, the step portions 11b and 11c are not trapezoidal or sinusoidal but rectangular or triangular. The occurrence of slippage of the honeycomb core 4 can also be suppressed by using the first prepreg laminated face plates 3b and 3c. At this time, the length of each corrugated concave portion is set to 5 to 20 honeycomb cells of the honeycomb core 4 and the amplitude is set to the length of 1 to 5 honeycomb cells, thereby making the sliding of the honeycomb core 4 more efficient. Can be prevented.
[0039]
The inventors of the present invention provide a method for manufacturing a conventional composite material honeycomb sandwich structure (hereinafter referred to as a conventional method) and a method for manufacturing a composite material honeycomb sandwich structure according to an embodiment of the present invention (hereinafter referred to as the present method). A comparative experiment was conducted. FIG. 8 is a plan view showing the experimental results, (a) is a plan view showing the experimental results in the conventional method, and (b) is a plan view showing the experimental results in the present method. In the experiment for the conventional method, the composite material honeycomb sandwich structure 10d was manufactured with the step portion 11d of the first prepreg laminated face plate formed into a linear shape, and an X-ray photograph of the composite material honeycomb sandwich structure 10d was taken. Moreover, in the experiment about the method of the present application, the composite material honeycomb sandwich structure 10 was manufactured with the stepped portion 11 of the first prepreg laminated face plate 3 having a trapezoidal wave shape, and an X-ray photograph of the composite material honeycomb sandwich structure 10 was taken.
[0040]
8A and 8B illustrate the shapes of the honeycomb cores 4 obtained by these X-ray photographs. Moreover, the wavy line in the figure shows the position of the step parts 11 and 11d, and the upper part in the figure from this wavy line is a part that is one step higher than the step part.
[0041]
As shown in FIG. 8A, in the honeycomb core 4d of the composite material honeycomb sandwich structure 10d manufactured by the conventional method, the honeycomb cell is remarkably deformed in the vicinity of the step portion 11d. Compared to this, the honeycomb core 4 of the composite honeycomb sandwich structure 10 manufactured by the method of the present application has a honeycomb cell slightly deformed along the waveform of the step portion 11 as shown in FIG. The amount of deformation is significantly smaller than that produced by conventional methods. From such an experiment, it was found that the method of the present application is very effective against a manufacturing failure in which the honeycomb core is crushed in the curing and bonding step.
[0042]
Further, in the method of the present invention as described above, if the prepregs 2 and 2a are cut so that the end portions thereof are non-linear, thereby forming the first prepreg laminated face plates 3 and 3a, the other steps are the same as the conventional processes. Since it is the same as the manufacturing method of a general composite material honeycomb sandwich structure, no special treatment is required, and the manufacturing does not take a long time compared to the conventional method.
[0043]
In addition, it is not necessary to increase the surplus portion (solid portion) of the outer peripheral portion of the composite material honeycomb sandwich structure, and no special dedicated tool for pressing the surplus portion is required, thereby increasing the manufacturing cost. Can be prevented.
[0044]
【The invention's effect】
In the manufacturing method of the composite material honeycomb sandwich structure according to the present invention, the stepped shape of the first prepreg laminated face plate becomes non-linear, and the edge of the stepped portion that is strongly pressed against the honeycomb core compared to the linear shaped stepped portion Since the area becomes large, the sliding of the honeycomb core is suppressed. In addition, since the step shape is non-linear, the cells of the honeycomb core are deformed so as to follow the step shape, and the step portion and the honeycomb core mesh with each other, thereby suppressing the slip of the honeycomb core. .
[0045]
Furthermore, since the prepreg whose end portion has a non-linear shape is simply laminated in a stepped manner on the uncured prepreg, it is possible to reduce labor and manufacturing time as compared with the conventional method, and to reduce the surplus portion. Therefore, the present invention has an excellent effect that a special dedicated jig is not required.
[Brief description of the drawings]
FIG. 1 is a perspective view illustrating an example of a stacking process of a method for manufacturing a composite material honeycomb sandwich structure according to an embodiment of the present invention.
FIG. 2 is a perspective view for explaining another example of the stacking step of the method for manufacturing the composite honeycomb sandwich structure according to the embodiment of the present invention.
FIG. 3 is a schematic side view showing an outline of a covering step and a curing and bonding step of the manufacturing method of the composite material honeycomb sandwich structure according to the embodiment of the present invention, and (a) shows first and second prepreg laminations. The covering process and lamination | stacking process in the case of interposing an adhesive agent between a faceplate and a honeycomb core are shown, (b) shows the case where the 1st prepreg lamination faceplate and the 2nd prepreg lamination faceplate are each closely_contact | adhered directly to a honeycomb core The covering process and the laminating process are shown.
FIG. 4 is a schematic side view for explaining the outline of the curing and bonding step of the method for manufacturing the composite material honeycomb sandwich structure according to the embodiment of the present invention.
5 is a plan view showing details of an end shape of the prepreg shown in FIG. 1. FIG.
FIG. 6 is a perspective view showing another example of a prepreg laminated face plate used for manufacturing a composite material honeycomb sandwich structure according to an embodiment of the present invention.
FIG. 7 is a perspective view showing another example of the prepreg laminated face plate used for manufacturing the composite material honeycomb sandwich structure according to the embodiment of the present invention.
FIG. 8 is a plan view showing the results of a comparative experiment between a conventional method for manufacturing a composite material honeycomb sandwich structure and a method for manufacturing a composite material honeycomb sandwich structure according to an embodiment of the present invention. It is a top view which shows the experimental result in a conventional method, (b) is a top view which shows the experimental result in this application method.
FIGS. 9A and 9B are schematic diagrams for explaining one step of a method for manufacturing a conventional composite material honeycomb sandwich structure. FIG. 9A shows a state before the honeycomb core is crushed, and FIG. Indicates the state.
FIG. 10 is a perspective view schematically showing a configuration of a prepreg laminated face plate used in a conventional composite material honeycomb sandwich structure.
FIG. 11 is a cross-sectional view showing a composite honeycomb sandwich structure provided with a ply-up portion.
[Explanation of symbols]
1, 2, 2a Prepreg 3, 3a, 3b, 3c First prepreg laminated face plate 4 Honeycomb core 5 Second prepreg laminated face plate 6 Adhesives 7a, 7b Uncured honeycomb sandwich structure 8 Bag film 9 Inclined portion 10, 10d Composite material honeycomb Sandwich structure 11, 11a, 11b, 11c, 11d Step part 12 Ply-up part

Claims (10)

A method of manufacturing a composite material honeycomb sandwich structure in which a honeycomb core having a tapered portion is sandwiched between and bonded between two prepreg laminated face plates,
The uncured prepreg impregnated with a thermosetting synthetic resin reinforcing fibers, the end portion forms a non-linear shape, another uncured prepreg smaller area than the prepreg are laminated so as to be stepped A laminating step for constituting the first prepreg laminated face plate ;
Wherein the one surface of the honeycomb core, combined before Symbol surface having a stepped portion of the first prepreg laminated faceplate, as stepped-in portion is positioned in the range or near the tapered portion of the honeycomb core, said first prepreg A coating step of forming an uncured honeycomb sandwich structure by covering the honeycomb core between the laminated face plate and a separately formed second prepreg laminated face plate;
Was heated with pressurizing the uncured honeycomb sandwich structure, the first and the hardening of the second prepreg laminate faceplate, said first and substantially curing bonding process carried out simultaneously with the adhesive of the second prepreg laminated surface plates and the honeycomb core A method for producing a composite honeycomb sandwich structure comprising:   2. The method for manufacturing a composite material honeycomb sandwich structure according to claim 1, wherein, in the laminating step, an uncured prepreg having a corrugated end is laminated on an uncured prepreg.   The manufacturing method of the composite material honeycomb sandwich structure according to claim 2, wherein the waveform is a substantially trapezoidal wave.   4. The method for manufacturing a composite honeycomb sandwich structure according to claim 3, wherein an inclination angle θ with respect to the wavelength direction of the inclined portion of the substantially trapezoidal wave satisfies 90 ° <θ ≦ 135 °.   The manufacturing method of the composite material honeycomb sandwich structure according to claim 2, wherein the waveform is a substantially rectangular wave.   The manufacturing method of the composite material honeycomb sandwich structure according to claim 2, wherein the waveform is a substantially sine wave.   The method of manufacturing a composite material honeycomb sandwich structure according to claim 2, wherein the waveform is a substantially triangular wave. The uncured prepreg having a corrugated end has a corrugated recess having a length corresponding to 5 to 20 honeycomb cells of the honeycomb core, and a corrugated amplitude having a length corresponding to 1 to 5 honeycomb cells. A method for manufacturing a composite honeycomb sandwich structure according to any one of claims 2 to 7 . In the covering step, a film-like adhesive is interposed between the first and second prepreg laminated face plates and the honeycomb core, and the honeycomb core is covered with the first and second prepreg laminated face plates. A method for manufacturing a composite material honeycomb sandwich structure according to any one of claims 1 to 8 . In the curing and bonding step, the uncured honeycomb sandwich structure is covered with a bag film,
The method for manufacturing a composite material honeycomb sandwich structure according to any one of claims 1 to 9 , wherein the bag film is evacuated.

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