JP4713778B2 - Wing structure and manufacturing method thereof - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a wing structure of light weight and excellent torsional rigidity, and a method for manufacturing the wing structure by which the manufacturing labor and cost can be reduced. SOLUTION: In the wing structure 10 comprising an outer plate part 11, a front edge part 12, beam parts 13 and end parts 14 in the longitudinal direction and having notched parts 20 for attaching metal fixtures at the front edge part 12, the beam parts 13 have retreating parts 13b which project rearward corresponding to the shapes of the notched parts 20 for attaching the metal fixtures. Dry performs for respective members are fixed with a flexible mandrel constituted by filling silicone beads into a bag film and with an upper and a lower mold, and a thermosetting resin is impregnated and cured in the dry perform for each member by an RTM method to cure and form the wing structure 10. The flexible mandrel is discharged from a work hole or the like after being formed.

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a wing structure and a method for manufacturing the wing structure, and more particularly, to a wing structure having a bracket mounting notch at a front edge and a method for manufacturing a wing structure using a specific flexible mandrel.
[0002]
[Prior art]
As shown in FIG. 5, various movable wings 100 such as an aircraft auxiliary wing (aileron), a flap, a lift (elevator), and a rudder (ladder) are connected to a main wing, a horizontal tail, It is pivotally attached to the vertical tail. As shown in FIG. 5, this type of movable blade 100 has a box-type structure in which a notch portion (hereinafter referred to as a “metal fitting notch portion”) 120 for attaching the hinge metal fitting 200 to the front edge portion 110 is provided. A girder 130 is provided in the interior.
[0003]
In order to manufacture the box-type structure of the movable blade 100 described above, the front edge portion 110 disposed in the front portion of the beam portion 130, the upper outer plate portion 140 disposed in the rear portion of the beam portion 130, and the lower outer portion. The plate portion 150 and the longitudinal end portion 160 of the movable blade 100 are separately manufactured from a metal material or a fiber-reinforced composite material, and these are coupled by a mechanical coupling means such as a rivet. The girder 130 provided inside the box structure is a long narrow member whose cross-sectional shape when cut at right angles to the length direction is substantially U-shaped or substantially I-shaped. Thus, it extends in the span direction of the movable blade 100 and is arranged at the rear position of the bracket mounting notch 120 (see FIGS. 6A and 6B).
[0004]
[Problems to be solved by the invention]
However, in the movable wing 100 as described above, it is necessary to dispose the girder part 130 behind the bracket mounting notch part 120, and accordingly, the area of the closed cross section of the rear part of the girder part of the box structure is small. It was. In general, the torsional rigidity of the blade structure is higher as the rear part of the girder is wider and the area of the closed cross section is larger. Therefore, the movable blade 100 having the bracket mounting notch 120 as described above has lower torsional rigidity. There was a case. In such a case, it is necessary to separately provide a reinforcing member, and as a result, the weight of the entire movable blade 100 is increased. Such an increase in the weight of the movable wing 100 is not preferable in the aerospace field where a lightweight and highly rigid structure is required.
[0005]
Moreover, when manufacturing the box-shaped structure as described above, as described above, since the girder part, the front edge part, the outer plate part, etc. are separately manufactured and then joined, the manufacturing process is performed. It was cumbersome and time-consuming, and the manufacturing cost was increased.
[0006]
An object of the present invention is to provide a blade structure that is lightweight and excellent in torsional rigidity, and to provide a method for manufacturing a blade structure that can significantly reduce manufacturing labor and manufacturing costs. .
[0007]
[Means for Solving the Problems]
In order to solve the above problems, the invention described in claim 1 is, for example, as shown in FIG. Leading edge In the wing structure having a notch for mounting the metal The leading part is Corresponding to the shape of the bracket mounting notch, there is a retracted part that protrudes backward. The retracted portion is disposed behind the metal fitting mounting notch, and a portion of the front beam portion excluding the retracting portion is disposed on the side of the metal fitting mounting notch. It is characterized by that.
[0008]
The wing structure according to the first aspect of the present invention is provided with a specially shaped girder portion having a receding portion corresponding to the shape of the metal fitting mounting notch portion, and a portion excluding the receding portion of the girder portion is a front edge. Since it can arrange | position to the front side as much as possible of a part, a girder part can be functioned effectively as a reinforcing member of a front edge part. Accordingly, it is possible to prevent the torsional rigidity of the wing structure from being lowered due to the formation of the metal fitting attaching portion notch portion only by the girder portion. As a result, it is not necessary to separately provide a reinforcing member for increasing the torsional rigidity of the wing structure, and the wing structure can be lightweight and have high strength.
[0009]
The invention according to claim 2 is a dry preform for a lower outer plate portion, an upper outer plate portion, a front edge portion and a girder portion, for example, as shown in FIGS. A dry preform preparation step for preparing a lower mold, a lower mold arranging step for arranging a lower mold, a dry preform for a lower outer plate, a dry preform for a leading edge, and a dry preform for a girder on the lower mold In the space formed by the primary dry preform arranging step, the dry preform for the front edge portion, and the dry preform for the spar portion, silicon rubber is formed inside the bag film having the same expansion shape as this space. A front flexible mandrel arrangement step of arranging a front flexible mandrel filled with a plurality of beads, the main component of which is a bead made of steel, and the dry pref In the space formed by the drum and the lower outer plate dry preform, a bead made of silicon rubber is used as the main component inside the bag film having the same expansion shape as the space behind the spar of the wing structure to be manufactured. A rear flexible mandrel arranging step of arranging a rear flexible mandrel filled with a plurality of beads, a secondary dry preform arranging step of arranging an upper outer plate dry preform on the rear flexible mandrel, and the upper outer plate dry For each dry preform, an upper mold arranging step for arranging an upper die on the reform, an exhaust step for discharging air from a space formed by the upper die, the lower die, the front flexible mandrel and the rear flexible mandrel, and A resin impregnation step for impregnating a thermosetting resin and an impregnated resin A heating step of curing by heating, a demolding step of removing the upper and lower molds, characterized in that it comprises a discharge step of discharging said front and rear flexible mandrel.
[0010]
According to the second aspect of the present invention, a relatively light weight and high strength blade structure made of a fiber reinforced composite material can be integrally manufactured relatively easily. Therefore, it is not necessary to separately manufacture a member for a girder part, a member for a leading edge part, a member for an outer plate part, etc. as in the past, and join them together. Can be significantly reduced.
[0011]
According to a third aspect of the present invention, in the method for manufacturing a wing structure according to the second aspect, for example, as shown in FIG. 3, the girder dry preform is rearward corresponding to the shape of the bracket mounting notch. It has a retreating part which protrudes, It is characterized by the above-mentioned.
[0012]
According to invention of Claim 3, in addition to the effect which the manufacturing method of the blade structure of Claim 2 show | plays, the blade structure of Claim 1 can be manufactured. That is, the blade structure manufactured by the invention according to claim 3 is provided with a specially-shaped girder having a receding portion projecting rearward only at the notch portion for mounting the metal fitting, and most of the blade structure in the longitudinal direction. Thus, the area of the closed cross section of the rear part of the girder that receives the aerodynamic force is increased. As a result, it is possible to manufacture a blade structure that does not require a separate reinforcing member for increasing torsional rigidity. That is, a high-quality blade structure can be manufactured at low cost.
[0013]
For example, as shown in FIG. 4, the invention described in claim 4 is provided with an outer plate part, a front edge part, and a girder part. A dry preform preparation step for preparing a dry preform for a side skin portion, an upper skin portion, a leading edge portion and a girder portion, a lower die placement step for placing a lower die, and on the lower die, A primary dry preform placement step in which a dry preform for a lower outer plate part, a dry preform for a front edge part, and a dry preform for a girder part are arranged, and the dry preform for the front edge part and the dry preform for the girder part A notch mold having the same shape as the portion corresponding to the bracket mounting notch in the space ahead of the spar of the blade structure to be manufactured, and a portion corresponding to the bracket mounting notch Same expansion as the part excluding A front core placement step in which a front flexible mandrel filled with a plurality of beads mainly composed of silicon rubber beads is placed in a bag film having a shape, and for the girder dry preform and the lower outer plate A rear core placement step for placing a rear core jig in a space formed from the dry preform, and a second dry preform placement step for placing a dry preform for the upper outer plate on the rear core jig. An upper mold placing step for placing an upper mold on the upper outer plate dry preform, the upper mold, the lower mold, the notch mold, the front flexible mandrel, and the rear core jig An exhaust process for exhausting air from the space formed from, a resin impregnation process for impregnating each dry preform with a thermosetting resin, and heating the impregnated resin A heating step of reduction, the upper mold, the lower mold, the notch mold, characterized in that it comprises a demolding step of removing the front flexible mandrel and the rear core jig.
[0014]
According to the fourth aspect of the present invention, a relatively light weight and high strength blade structure made of a fiber reinforced composite material can be integrally manufactured relatively easily. Therefore, it is not necessary to separately manufacture a member for a girder part, a member for a leading edge part, a member for an outer plate part, etc. as in the past, and join them together. Can be significantly reduced.
[0015]
According to the invention described in claim 4, the blade structure described in claim 1 can be manufactured. That is, the wing structure manufactured by the invention according to claim 4 is provided with a girder part having a retreating part projecting rearward corresponding to the shape of the metal fitting mounting notch part. Except for this, the cross-sectional area of the rear part of the girder increases and the torsional rigidity is improved. As a result, a blade structure having high torsional rigidity can be manufactured without separately providing a reinforcing member for increasing torsional rigidity. That is, a high-quality blade structure can be manufactured at low cost. Further, by using the notch mold, it is possible to accurately form the mold mounting notch, and to manufacture a high-quality blade structure.
[0016]
The invention according to claim 5 is a method for manufacturing a blade structure, for example, as shown in FIGS. 2 to 4, the first dry preform placement step of the method for manufacturing a blade structure according to claim 2, 3 or 4. In the present invention, a separately hard-formed girder part is arranged in place of the girder part dry preform.
[0017]
According to the fifth aspect of the present invention, the front and rear flexible mandrels, the notch molds and the like can be arranged very easily by arranging the pre-cured girder instead of the girder dry preform. Therefore, it is possible to further reduce the labor when manufacturing the wing structure.
[0018]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings. A wing structure 10 according to the following embodiment is rotatably attached to a main wing of an aircraft via a hinge fitting.
[0019]
[First embodiment]
As shown in FIG. 1A, the wing structure 10 according to the present embodiment includes an outer plate portion 11, a front edge portion 12, a girder portion 13, and a length direction end portion 14. Two portions of the portion 11 are provided with metal fitting attachment notches 20 for attaching hinge metal fittings. As shown in FIG. 1 (b), the girder 13 provided behind the metal fitting mounting notch 20 has a retreating portion 13 b that protrudes rearward corresponding to the shape of the metal fitting mounting notch 20. The part of the girder part 13 excluding the receding part 13b is arranged so as to be located as far forward as possible from the front edge part 12, and the girder part 13 has a substantially corrugated shape in plan view (shape seen from above). It has a shape to present.
[0020]
The planer shape of the girder 13 is a substantially waveform shape as shown in FIG. 1 (b), and the portion excluding the receding portion 13 b is disposed as far as possible on the front edge portion 12. The area of the closed cross section surrounded by the beam portion 13 and the outer plate portion 11 behind it can be increased. For this reason, the torsional rigidity of the wing structure 10 can be increased. In addition, as shown in FIG.1 (c), the girder part 13 is provided with the flange 13f, and the cross-sectional shape at the time of cut | disconnecting at right angles to the length direction is exhibiting I-shape. The girder portion 13 may be pre-cured or primary-cured, and integrally formed with other portions (outer plate portion, front edge portion and end portion in the length direction) as described later. It may be a thing.
[0021]
Next, a method for manufacturing the wing structure 10 according to the present embodiment by a so-called RTM (Resin Transfer Molding) method will be described with reference to FIGS.
[0022]
First, as shown in FIG. 2, each dry preform (11′d, 11′u, for the lower outer plate portion, for the upper outer plate portion, for the front edge portion, for the girder portion and for the longitudinal end portion, 12 ′, 13 ′, 14 ′) is prepared (dry preform preparation step). In the present invention, the dry preform means a dried thin plate-like body composed of various reinforcing fibers that are not impregnated with resin. By impregnating the dry preform with a thermosetting resin and curing it, the weight is relatively light and high. A wing structure 10 made of a strong fiber reinforced composite material can be molded.
[0023]
Examples of the types of reinforcing fibers constituting each dry preform include glass fibers, carbon fibers, aramid fibers, and alumina fibers. Moreover, each dry preform can be made into the form comprised by the textile form, the knitted form, the mat form, and the felt form by weaving, knitting, or twisting the said reinforcement fiber, for example. The thickness of each dry preform can be appropriately determined according to the size of the blade structure 10 to be manufactured.
[0024]
In addition, in the dry preform 14 ′ for the longitudinal end portion, working holes 30 for discharging a flexible mandrel, a front bag film 40, and a rear bag film 50, which will be described later, are formed in front and rear of the beam portion. deep. Also, the dry preform 12 'for the front edge is prepared in the shape of the front edge, but the portion provided with the notch for mounting the metal is not introduced and impregnated with a thermosetting resin in the resin impregnation step described later. A blocking member is disposed.
[0025]
After preparing each dry preform described above, first, a lower mold (not shown) used for molding is arranged (lower mold arranging step). The lower mold is formed in the shape of the lower half of the blade structure 10 to be manufactured, and can be prepared from a metal material that can withstand the heating in the RTM method.
[0026]
Next, on the lower mold, the lower outer plate portion dry preform 11′d, the front edge portion dry preform 12 ′, the girder portion dry preform 13 ′, and the longitudinal end portion dry preform 14 ′. Are arranged (first dry preform arranging step). At this time, the working hole 30 provided in the lengthwise end dry preform 14 ′ is closed with a spacer that does not allow the thermosetting resin to pass therethrough.
[0027]
The lower outer plate dry preform 11′d and the front edge dry preform 12 ′ may be sewn in advance before placement. Further, a dry preform for the lower end portion and the longitudinal end portion of the dry preform 13 'for the girder portion is previously prepared by stitching the dry preform 11'd for the lower outer plate portion and the dry preform 12' for the front edge portion. 14 'may be sewn.
[0028]
Next, in the space formed by the dry preform 12 ′ for the leading edge portion, the dry preform 13 ′ for the spar portion, and the dry preform 14 ′ for the end portion in the longitudinal direction, the same expansion as the space in front of the spar portion of the blade structure 10 to be manufactured is performed. A front flexible mandrel 40 having a shape is disposed (front flexible mandrel arranging step, see FIG. 3). This front flexible mandrel 40 is configured by filling a bag film 41 with a plurality of beads 42 whose main constituents are beads made of silicon rubber, and the shape is arbitrarily changed according to the shape to be arranged. This is a core jig that can be used.
[0029]
The beads 42 filled in the bag film 41 may be composed of only silicon rubber beads, or may be composed of silicon rubber beads and glass beads. The diameter, hardness, and filling rate of the silicon rubber beads can be appropriately determined according to the size of the blade structure 10 to be manufactured.
[0030]
The front flexible mandrel 40 is housed in another mold that imitates the front space of the spar of the wing structure 10 to be manufactured, and the shape in the bag film 41 constituting the front flexible mandrel 40 is discharged. If fixed, the shape does not collapse when the front flexible mandrel 40 is disposed at a predetermined position, so that work efficiency can be improved.
[0031]
Next, in the space formed by the girder dry preform 13 ', the lower outer plate dry preform 11'd, and the lengthwise end dry preform 14', the rear of the girder structure 10 to be manufactured. A rear flexible mandrel 50 having the same expansion shape as the space is disposed (rear flexible mandrel arranging step, see FIG. 3). The rear flexible mandrel 50 is configured by filling the inside of the bag film 51 with the plurality of beads 52 described above, and is a core jig whose shape can be arbitrarily changed according to the shape to be arranged. is there.
[0032]
The beads 52 filled in the bag film 51 of the rear flexible mandrel 50 may have the same configuration as that filled in the bag film 41 of the front flexible mandrel 40. The diameter, hardness, filling rate, and glass beads of the silicon rubber beads You can also change the ratio of Moreover, it is preferable to arrange | position after discharging | emitting the air in the bag film 51 of the back flexible mandrel 50, and fixing a shape according to a girder part back space. The bag films 41 and 51 constituting the front and rear flexible mandrels 40 and 50 are preferably made of silicon rubber having excellent heat resistance and flexibility.
[0033]
Next, the upper outer plate dry preform 11′u is arranged on the rear flexible mandrel 50 (secondary dry preform arranging step), and the upper outer plate dry preform 11′u is used as the girder dry preform 13 ′ and It sews to the dry preform 14 'for the longitudinal end. Next, an upper die (not shown) is placed on the upper outer plate dry preform 11'u (upper die placing step). This upper mold is formed in the shape of the upper half of the blade structure 10 to be manufactured, and can be prepared from a metal material that can withstand the heating in the RTM method. By fixing the arranged upper mold to the lower mold, a molding mold capable of introducing a thermosetting resin described later is configured.
[0034]
Next, air is discharged from the space formed by the upper mold, the lower mold, the front and rear flexible mandrels 40, 50, that is, the space where each dry preform is arranged (hereinafter referred to as “resin introduction space”) (exhaust process). ). In this case, an exhaust hole is provided in the upper die, and the exhaust hole is connected to the vacuum device by an exhaust pipe, and air is exhausted from the closed space by evacuation by the vacuum device.
[0035]
Next, a thermosetting resin is introduced into the resin introduction space, and each dry preform is impregnated with the thermosetting resin (resin impregnation step). At this time, a resin introduction pipe connected to a predetermined resin tank is connected to the lower mold, and the thermosetting resin in the resin tank is introduced into the resin introduction space by the vacuum pressure in the discharging step. Examples of the thermosetting resin include an epoxy resin, a phenol resin, a cross-linked polyethylene, and a polyimide, and among them, an epoxy resin is preferable. Thereafter, the exhaust hole connected to the vacuum device is closed, and pressure is applied from the resin tank side to sufficiently introduce the thermosetting resin into the resin introduction space.
[0036]
Next, together with the upper die and the lower die, the resin impregnated in each dry preform is heated and cured using an oven or the like (heating step). The heating temperature and heating time at this time can be appropriately determined according to the type of the thermosetting resin, the amount of impregnation of the thermosetting resin, and the like. By this heating process, the plurality of beads 42 and 52 filled in the bag films 41 and 51 of the front and rear flexible mandrels 40 and 50 are expanded, and the dry preform impregnated with the thermosetting resin is uniformly pressed from the inside. Thus, a sufficient pressure can be applied to the curing molding.
[0037]
Next, the upper mold and the lower mold are removed (demolding step), and the spacer that has blocked the working hole 30 provided in the dry preform 14 ′ for the length direction end is removed. Thereafter, the bag films 41 and 51 of the front and rear flexible mandrels 40 and 50 are broken, and the plurality of beads 42 and 52 filled inside are broken out from the working holes formed at the end portions in the length direction to the outside. Discharge. After the beads 42 and 52 are almost discharged, the bag films 41 and 51 are discharged from the work holes (discharge process). Finally, the working hole 30 formed in the longitudinal end 14 is closed to obtain the wing structure 10 (see FIG. 1).
[0038]
According to the manufacturing method according to the present embodiment, a relatively light weight and high strength blade structure made of a fiber reinforced composite material can be manufactured by using a flexible mandrel and adopting a so-called RTM method. Therefore, it is necessary to go through the process of joining these members after manufacturing separately the members for girders, the members for the leading edge, the members for the upper outer plate, the members for the lower outer plate, etc. Therefore, labor and cost for manufacturing the wing structure can be remarkably reduced.
[0039]
Further, according to the manufacturing method according to the present embodiment, as shown in FIG. 1, the wing structure provided with the specially shaped girder portion 13 having the receding portion 13 b corresponding to the shape of the metal fitting mounting notch portion 20. 10 can be easily manufactured integrally. Since the girder part 13 of the wing structure 10 has the special shape described above, the part excluding the receding part 13b of the girder part 13 is arranged on the front side of the front edge part 12 as much as possible. The area of the closed cross section of the rear portion is significantly larger than that of the conventional structure. As a result, it is not necessary to separately provide a reinforcing member for increasing torsional rigidity, and the high-quality blade structure 10 can be manufactured at low cost.
[0040]
[Second Embodiment]
Next, a second embodiment will be described with reference to FIG. In the present embodiment, a method of integrally manufacturing the wing structure 10 shown in FIG. 1 through a process different from the manufacturing method according to the first embodiment will be described. In the manufacturing method according to the present embodiment, the “front flexible mandrel placement step” in the first embodiment is changed to the “front core placement step”, and the “rear flexible mandrel placement step” is changed to the “back core placement step”. And the introduction of the thermosetting resin in the “resin impregnation step” is a so-called VARTM (Vacuum Assist RTM) method in which only the vacuum pressure in the “exhaust step” is used, so other overlapping configurations, Description of the process is omitted.
[0041]
In the present embodiment, the space formed by the front edge dry preform 12 ′, the girder dry preform 13 ′, and the longitudinal end dry preform 14 ′ is attached to the space in front of the girder. A notch part mold 60 having the same shape as the part corresponding to the notch part, and a front flexible mandrel 40 ′ having the same expansion shape as the part excluding the part corresponding to the bracket mounting notch part in the space ahead of the girder part. Arrange (refer to the front core arrangement step, FIG. 4). The front flexible mandrel 40 'is filled with a plurality of beads 42 used in the first embodiment. In the present embodiment, the front flexible mandrel 40 ′ is divided into three parts (see FIG. 4A) in order to arrange the notch mold 60.
[0042]
Further, in the present embodiment, similarly to the first embodiment, the lower outer plate dry preform 11′d, the upper outer plate dry preform 11′u, the girder dry preform 13 ′, and the length direction. A rear bag film 51 ′ having a trapezoidal cross-sectional shape and a filler 70, which is a long member having a triangular cross-sectional shape, are disposed in a space formed from the dry preform 14 ′ for the end (rear core arrangement) Process).
[0043]
In the present embodiment, the introduction of the thermosetting resin in the “resin impregnation step” in the first embodiment is performed only by the vacuum pressure in the “exhaust step”. That is, in the present embodiment, the step of sufficiently introducing the thermosetting resin into the resin introduction space by applying pressure from the resin tank side is omitted, and the thermosetting resin is made to be resin only by the vacuum pressure of vacuuming by the vacuum device. Each dry preform introduced into the introduction space and disposed between the lower mold and the upper mold and the rear bag film 51 ′ is impregnated with a thermosetting resin only by vacuum pressure. For this reason, the back bag film 51 ′ is not filled with a plurality of beads.
[0044]
According to the present embodiment, by using the notch mold 60, it is possible to more reliably form the mold mounting notch, and to manufacture the high-quality blade structure 10. In this embodiment, the so-called VARTM method is employed, and the thermosetting resin is introduced and impregnated by effectively utilizing the vacuum pressure in the exhaust process, so that the thermosetting resin is pressurized and introduced. Therefore, the manufacturing cost can be significantly reduced.
[0045]
In the manufacturing method according to the above embodiment, the girder dry preform 13 'is used. However, instead of this girder dry preform 13', a pre-cured girder 13 may be arranged. it can. Further, instead of the dry preform for the spar, an intermediate product of the spar that has been subjected to primary curing molding may be disposed and secondarily cured in the heating step of the above-described embodiment.
[0046]
Further, in the manufacturing method according to the above-described embodiment, the length direction end portion 14 is replaced with other constituent parts (the outer plate portion 11 and the front edge portion 12 using the dry preform 14 ′ for the length direction end portion. The wing structure 10 is integrally formed at the same time as the spar 13), but the lengthwise end portion 14 is separately manufactured, and other components are integrally formed except for the lengthwise end portion 14. In addition, the wing structure 10 can be manufactured by joining the end portions 14 in the longitudinal direction by a mechanical coupling means (fastener coupling).
[0047]
As described above, according to the method in which only the longitudinal end portion 14 is fastened to the fastener, the front and rear flexible mandrels 40 and 50 can be arranged in a state of protruding from the longitudinal end portion of the wing. The end portions of the flexible mandrels 40 and 50 can be easily processed. In addition, when adopting a method in which only the lengthwise end portion 14 is manufactured by fastener bonding as described above, the front and rear flexible mandrels 40 in which a dry preform impregnated with a thermosetting resin is expanded by heating are used. , 50 and the upper die and the lower die, and pressurizing the outer plate portion 11 to cure. At this time, if necessary, spacers can be appropriately disposed and sealed. Moreover, a spacer may be arrange | positioned between the front flexible mandrel 40 and the back flexible mandrel 50, and a girder part may be sealed.
[0048]
【The invention's effect】
In the wing structure according to the first aspect of the present invention, the girder part has a receding part that partially protrudes rearward, and the part excluding the receding part of the girder part forms a wider closed cross section than the conventional one. It is possible to prevent a decrease in torsional rigidity of the wing structure. As a result, it is not necessary to separately provide a reinforcing member for increasing the torsional rigidity of the wing structure, so that the wing structure is light and has high strength, and the manufacturing cost can be reduced.
[0049]
According to the second aspect of the present invention, a relatively light weight and high strength blade structure made of a fiber reinforced composite material can be integrally manufactured relatively easily. Therefore, it is not necessary to go through the process of joining the members for the girder part, the leading edge part, the outer plate part, etc. separately as before, and the labor and cost in manufacturing the wing structure are greatly reduced. Can be reduced.
[0050]
According to the invention described in claim 3, the blade structure according to claim 1 can be manufactured as well as the effect of the invention described in claim 2. That is, the wing structure manufactured by the invention according to claim 3 has a receding portion in which the spar portion partially protrudes rearward, and a portion excluding the receding portion of the spar portion forms a wider closed cross section than in the prior art. Therefore, it has high torsional rigidity. As a result, it is not necessary to separately provide a reinforcing member for increasing torsional rigidity, and a high-quality blade structure can be manufactured at low cost.
[0051]
According to the fourth aspect of the present invention, a relatively light weight and high strength blade structure made of a fiber reinforced composite material can be integrally manufactured relatively easily. Therefore, it is not necessary to go through the process of joining the members for the girder part, the leading edge part, the outer plate part, etc. separately as before, and the labor and cost in manufacturing the wing structure are greatly reduced. Can be reduced.
[0052]
Further, according to the invention described in claim 4, the blade structure described in claim 1 can be integrally manufactured relatively easily. That is, the wing structure manufactured by the invention according to claim 4 has a receding portion in which the spar portion partially protrudes rearward, and a portion excluding the receding portion of the spar portion forms a wider closed cross section than in the prior art. Therefore, it has high torsional rigidity. As a result, a high-quality blade structure can be manufactured at low cost without separately providing a reinforcing member for increasing torsional rigidity. In particular, by using the notch mold, it is possible to accurately form the mold mounting notch, and to manufacture a high-quality blade structure.
[0053]
According to the fifth aspect of the present invention, it is very easy to dispose the front and rear flexible mandrels and the notch molds by arranging the prefabricated girder instead of the girder dry preform. Therefore, it is possible to further reduce the labor when manufacturing the wing structure.
[Brief description of the drawings]
BRIEF DESCRIPTION OF DRAWINGS FIG. 1 is an explanatory diagram for explaining a wing structure according to a first embodiment of the present invention, where (a) is a perspective view, (b) is a plan view (viewed from above), and (c). FIG. 5 is a partially enlarged perspective view of a girder portion of a metal fitting mounting portion provided inside the wing structure.
FIG. 2 is an explanatory diagram for explaining a method of manufacturing the wing structure shown in FIG.
3 is an explanatory view for explaining a method of manufacturing the wing structure shown in FIG. 1, wherein (a) shows a state in which front and rear flexible mandrels are arranged, and (b) shows ( It is sectional drawing of the BB part of a), (c) is sectional drawing of CC part of (a).
FIG. 4 is an explanatory diagram for explaining a manufacturing method of a wing structure according to a second embodiment of the present invention, wherein (a) is a front flexible mandrel, a notch mold, a rear bag film, and a filler. And (b) is a cross-sectional view of the BB portion of (a).
FIG. 5 is an explanatory diagram for explaining a conventional blade structure having a notch for mounting a metal fitting.
FIGS. 6A and 6B are explanatory views for explaining a conventional blade structure having a notch for mounting a metal fitting, wherein FIG. 6A is a perspective view and FIG. 6B is a plan view.
[Explanation of symbols]
10 Wing structure
11 Outer plate
11'd Dry preform for lower skin
11'u Dry preform for upper skin
12 Front edge
12 'dry edge dry preform
13 digits
13b receding part
13f flange
13 'Dry preform for girder
14 Length direction end
14 'Dry preform for end in length direction
20 Notch for mounting bracket
30 working hole
40 Front flexible mandrel
41 Bag film
42 beads
40 'front flexible mandrel
50 Flexible rear mandrel
51 Bag film
52 beads
51 'Back bag film
60 Notch mold
70 filler
100 movable wings
110 Front edge
120 Notch for mounting bracket
130 digits
140 Upper die outer plate
150 Lower skin part
160 End in length direction

Claims (5)

In the wing structure that has a bracket mounting notch on the front edge ,
Front spar portion, have a receding portion projecting rearwardly so as to correspond to the shape of the metal mounting notches,
The blade structure characterized in that the retracted portion is disposed behind the metal fitting mounting notch, and a portion of the front beam portion excluding the retracted portion is disposed on the side of the metal fitting mounting notch . In manufacturing the wing structure,
A dry preform preparation step for preparing a dry preform for the lower outer plate portion, the upper outer plate portion, the leading edge portion and the girder portion,
A lower mold placing step for placing the lower mold;
On the lower mold, a primary dry preform arrangement step of arranging a lower outer plate dry preform, a leading edge dry preform, and a girder dry preform;
In a space formed from the dry preform for the leading edge and the dry preform for the spar, a plurality of beads having silicon rubber beads as the main component inside a bag film having the same expansion shape as this space A front flexible mandrel placement step of placing the filled forward flexible mandrel;
In a space formed by the dry preform for the spar and the dry preform for the lower outer plate, beads made of silicon rubber are mainly placed inside the bag film having the same expansion shape as the space behind the spar of the wing structure to be manufactured. A rear flexible mandrel arrangement step of arranging a rear flexible mandrel filled with a plurality of beads as constituent elements;
A secondary dry preform arrangement step of arranging an upper outer plate dry preform on the rear flexible mandrel;
An upper mold arrangement step of arranging an upper mold on the upper preform for the upper outer plate;
An exhaust process for exhausting air from the space formed by the upper mold, the lower mold, the front flexible mandrel and the rear flexible mandrel;
A resin impregnation step of impregnating each dry preform with a thermosetting resin;
A heating step of heating and curing the impregnated resin;
A demolding step of removing the upper mold and the lower mold;
And a discharging step for discharging the front and rear flexible mandrels. The girder dry preform is
3. The method for manufacturing a wing structure according to claim 2, further comprising a retreating portion projecting rearward corresponding to the shape of the metal fitting mounting notch. In producing a wing structure comprising an outer plate part, a front edge part and a girder part, and having a notch part for mounting a metal fitting on the front edge part,
A dry preform preparation step for preparing a dry preform for the lower outer plate portion, the upper outer plate portion, the leading edge portion and the girder portion,
A lower mold placing step for placing the lower mold;
On the lower mold, a primary dry preform arrangement step of arranging a lower outer plate dry preform, a leading edge dry preform, and a girder dry preform;
For a notch having the same shape as the part corresponding to the notch for mounting the metal fitting in the space ahead of the spar of the blade structure to be manufactured in the space formed by the dry preform for the leading edge and the dry preform for the spar A mold and a front flexible mandrel in which a bag film having the same expansion shape as a portion excluding a portion corresponding to the notch for mounting the metal fitting is filled with a plurality of beads mainly composed of silicon rubber beads are disposed. A front core placement step to perform,
A rear core placement step of placing a back core jig in a space formed by the girder dry preform and the lower outer plate dry preform;
A secondary dry preform arrangement step of arranging an upper outer plate dry preform on the rear core jig;
An upper mold arrangement step of arranging an upper mold on the upper preform for the upper outer plate;
An exhaust process for discharging air from a space formed by the upper mold, the lower mold, the notch mold, the front flexible mandrel, and the rear core jig;
A resin impregnation step of impregnating each dry preform with a thermosetting resin;
A heating step of heating and curing the impregnated resin;
A wing structure manufacturing method comprising: a demolding step of removing the upper mold, the lower mold, the notch mold, the front flexible mandrel, and the rear core jig. In the first dry preform arrangement step of the method for manufacturing a wing structure according to claim 2, 3 or 4,
A method for producing a blade structure, characterized in that a separately hard-formed girder part is arranged instead of the girder part dry preform.

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