JP3973474B2 - Aircraft wing leading edge manufacturing method - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
  The present invention relates to a wing leading edge structure used in an aircraft.MadeIt relates to a manufacturing method.
[0002]
[Prior art]
In general, an anti-icing mechanism for preventing freezing is provided at a wing leading edge portion (hereinafter simply referred to as a wing leading edge portion) of an aircraft main wing, horizontal tail wing, rudder, or the like. This anti-icing mechanism performs anti-icing by guiding warm air from an engine compressor or the like to the blade front edge portion through a warm air supply pipe and flowing the warm air along the exterior portion of the blade front edge portion.
[0003]
The wing leading edge is desired to be lighter, and a lower manufacturing cost is also desired. For this reason, the blade leading edge is desired to reduce the number of parts and to simplify processing.
[0004]
As a prior art of such a blade leading edge and a method for manufacturing the blade leading edge, for example, there is a blade leading edge described in JP-A-11-34993 and a method for manufacturing the blade leading edge.
[0005]
The blade leading edge portion of the above publication will be described below with reference to FIGS. FIG. 7 is a partially cutaway perspective view showing the conventional blade leading edge. FIG. 8 is a cross-sectional view taken along the line AA in FIG.
[0006]
In general, an aircraft main wing includes a main wing main body side structure (not shown) and a wing leading edge portion 101 attached to the front of the main wing main body side structure. The blade leading edge portion 101 is disposed over the entire length in the longitudinal direction of the main wing (hereinafter referred to as the blade length direction). As shown in FIG. 7, the conventional blade leading edge portion 101 has an exterior portion 102, a rib 103, a warm air flow path 104, and a warm air supply pipe 105.
[0007]
The exterior portion 102 extends along the blade length direction. Moreover, the exterior part 102 demarcates the outer edge of the wing | tip front edge part 101, and is curved and formed in the desired shape.
[0008]
A plurality of ribs 103 are provided along the blade length direction. Each rib 103 extends in a direction intersecting with the blade length direction. Each rib 103 has a central partition wall 106 extending in the blade length direction at the center in the vertical direction in FIG. Each rib 103 is connected to the adjacent rib 103 by a central partition wall 106. Therefore, the central partition wall 106 divides the space between the ribs 103 adjacent to each other vertically.
[0009]
Each rib 103 has a rear partition wall 107 at the boundary with the main wing body side structure on the rear side. The rear partition 107 is connected to the rear partition 107 of the adjacent rib 103. The rear partition wall 107 is provided with a hole 108 that allows the warm air flow path 104 and the main wing main body side structure to communicate with each other.
[0010]
Each rib 103 has a front partition wall 109 extending toward the front side (the side opposite to the main wing main body side structure supporting the load of the airframe). The front partition wall 109 is connected to the front partition wall 109 of the adjacent rib 103. Accordingly, the front partition wall 109 extends over the entire blade length direction. The front partition wall 109 is bifurcated forward. The two ends of the bifurcated front partition wall 109 are connected to the exterior portion 102. Accordingly, the warm air supply pipe 105 is defined by the front partition wall 109 and the exterior portion 102. Further, the front partition wall 109 has a hole 110 for communicating the warm air flow path 104 and the warm air supply pipe 105 as shown in FIG.
[0011]
A plurality of warm air flow paths 104 are arranged along the blade length direction. The warm air flow path 104 is a space defined by two adjacent ribs 103 and the inside of the exterior portion 102. The warm air flow path 104 is divided into upper and lower portions by a central partition wall 106.
[0012]
The warm air supply pipe 105 is connected to a warm air supply source such as an engine compressor (not shown). Since the warm air supply pipe 105 is defined by the front partition wall 109 and the exterior part 102 as described above, it extends over the entire blade length direction. Accordingly, the warm air supply pipe 105 supplies the warm air from the warm air supply source to the entire blade length direction.
[0013]
The blade leading edge having the above configuration is supplied with warm air from the warm air supply pipe 105 through the hole 110 to the warm air flow path 104. Then, warm air flows in the warm air flow path 104. The warm air passing through the warm air flow path 104 is exhausted to the main wing main body side structure side through the hole 108. By such warm air flow, the blade leading edge 101 can be protected from ice.
[0014]
Such a blade leading edge 101 is manufactured as follows. Below, with reference to FIG.9 and FIG.10, the manufacturing method of the blade front edge part 101 is demonstrated. FIG. 9 is a partially cutaway perspective view showing the laminated body before superplastic forming. 10 is a cross-sectional view taken along a cutting line AA in FIG. FIG. 11 is a cross-sectional view showing the laminate formed by superplastic forming.
[0015]
In the method for manufacturing the blade leading edge 101, first, a laminated body 200 in which four plate-like superplastic titanium alloy plates 121, 122, 123, and 124 are overlapped is formed. As shown in FIGS. 9 and 10, the laminate 200 is configured such that the plate materials 122 and 123 are sandwiched between the plate material 121 and the plate material 124. A plurality of release materials 132 are disposed at predetermined positions between the plate material 121 and the plate material 122 and between the plate material 123 and the plate material 124. Further, release materials 131, 133, and 134 are disposed at predetermined positions between the plate materials 122 and 123. Further, the plate material 122 and the plate material 123 are formed with holes 110 where the release material 131 and the release material 132 overlap. Further, holes 108 are formed in the plate material 122 and the plate material 123 where the release material 132 and the release material 134 overlap. With the above configuration, the laminated body 200 is joined to portions other than where the release materials 131, 132, 133, and 134 are disposed.
[0016]
When the laminate 200 is formed, the laminate 200 is superplastically molded by the superplastic molding apparatus 300 shown in FIG. In this superplastic forming, a superplastic forming gas is injected into the laminate 200. This superplastic forming gas flows into the region where the release material 131 is disposed. Then, the superplastic forming gas flows into the region where the release material 132 is disposed through the hole 110. Subsequently, the superplastic forming gas flows into the region where the release material 134 is disposed through the hole 108.
[0017]
Due to the inflow of warm air into the laminate 200, the region where the release material 131 is disposed expands, and the warm air supply pipe 105 is formed. Further, the region where the release material 132 and the release material 134 are disposed also expands, and the rib 103 and the warm air flow path 104 are formed.
[0018]
In this way, the blade leading edge 101 is formed to have an anti-icing mechanism while having a small number of parts.
[0019]
[Problems to be solved by the invention]
However, in order to manufacture the conventional blade leading edge portion 101, it is necessary to arrange the release materials 131 to 134 with high accuracy. For this reason, the manufacture of the blade leading edge portion 101 has a high required processing accuracy and may increase the processing cost. Further, since the plurality of release materials 131 to 134 are arranged, the processing work is complicated.
[0021]
  In addition, the present inventionEyesThe present invention provides an aircraft wing leading edge manufacturing method for easily manufacturing an aircraft wing leading edge.InThe
[0022]
[Means for Solving the Problems]
  In order to solve the above problems and achieve the object, the aircraft wing leading edge of the present inventionManufacturing methodIs configured as follows.
[0038]
  A method for manufacturing an aircraft wing leading edge according to an aspect of the present invention is as follows.:
  a).Composed of superplastic materialRectangular shape of the same dimensionsOverlapping the first and second exterior elements in the form of a plate,
  b).The first and second exterior elements;At multiple locations separated from each other along the longitudinal directionMultiple joints extending linearly in the direction intersecting the longitudinal directionUltrasonic bondingTo join the first exterior element and the second exterior element to form an exterior part,
  c).Gas supply means for supplying gasBy,In the exteriorGas is fed into a plurality of regions defined by the joints adjacent to each other, the first exterior element, and the second exterior element.In a while,Push the exterior part into the female recess with the male part with the second exterior element facing the male part,By superplastic formingInflating the plurality of areasForming a plurality of warm air flow paths andIn the female recessBend andIn addition, a plurality of convex portions corresponding to each of the plurality of regions in the exterior portion by the convex portions that the female concave portion corresponds to each of the plurality of regions and has a position in the vicinity of both ends and the bottom of the concave portion. Form the
  d). First2 of the exterior elementsCut the protruding portions of the plurality of convex portions into the plurality of warm air flow paths inflated from the plurality of regionsForm a warm air inlet hole and a warm air outlet hole,
  Exterior part forming process: and
  a). The exterior partThe outer wing main body side structure is connected to one end portion in a direction intersecting the longitudinal direction. A main wing connecting portion at the other end in a direction intersecting the longitudinal direction, and a front portion facing the curved exterior portion connected to the exterior connecting portion.A support body,
  b).Provided at the front part of the support part body at a predetermined interval in the longitudinal direction of the support part body.Warm air supply pipeTo supportA supply pipe support;
  c).Provided with a predetermined interval across the longitudinal direction of the support body.A rib for reinforcing the support body;
  The exterior support part that hasprecisionCasting process to cast: and
  The exterior support partThe supply pipe support ofTo the warm air supply pipeAnd curved to the exterior connection part of the exterior support partThe exterior partConnect both ends ofAssembly process:
  It has.
[0039]
The said manufacturing method can form the said warm air flow path by flowing gas into the area | region defined by the plate-shaped 1st and 2nd exterior element, and the linear junction part adjacent to each other. For this reason, the said manufacturing method can manufacture the said warm air flow path, without requesting | requiring high process precision. Moreover, the said junction part is formed in linear form. For this reason, the said manufacturing method can form a junction easily even when a some junction is manufactured.
[0040]
Furthermore, since the exterior support part is cast, the supply pipe support part and the rib can be integrally formed, and therefore the exterior support part can be easily manufactured with a small number of steps.
[0041]
Furthermore, assembling the blade leading edge portion 10 simply attaches the exterior portion and the warm air supply pipe to the exterior support portion. For this reason, the aircraft wing leading edge portion can be easily assembled without requiring the attachment of fine parts or complicated work.
[0042]
Moreover, the said manufacturing method can form the said junction part by ultrasonic bonding.
[0043]
In this manufacturing method, the first exterior element and the second exterior element can be joined in an overlapped state. For this reason, the aircraft wing leading edge can be manufactured more easily. Moreover, since the said joining uses ultrasonic joining, it can join, without wash | cleaning the said 1st and 2nd exterior element specially. For this reason, this manufacturing method can manufacture the said aircraft wing leading edge part still more easily.
[0044]
Further, in the above manufacturing method, an end portion of each joint portion is disposed so as to face an edge portion of the exterior portion, and the gas supply unit is disposed at an edge portion of the exterior portion and is adjacent to each other. Gas can be fed into a plurality of regions defined by the joint, the first exterior element, and the second exterior element.
[0045]
For this reason, by the said manufacturing method, gas can be simultaneously supplied to the several area | region defined by the said junction part adjacent to each other, and a 1st exterior element, and a 2nd exterior element. For this reason, a plurality of warm air channels can be superplastically formed at a time. Therefore, the warm air flow path is easy and can be more reliably formed.
[0046]
Moreover, in the above manufacturing method, each of the joint portions may be formed along a direction orthogonal to the longitudinal direction of the exterior portion.
[0047]
With the above manufacturing method, the required processing accuracy when forming the joint can be lowered.
[0048]
The exterior support portion may be precision cast.
[0049]
According to the above manufacturing method, even when the exterior support part has a complicated shape such as a supply pipe support part, the exterior support part can be easily manufactured with a small number of steps.
[0050]
In the casting, a mold formed by stereolithography can be used.
[0051]
With the above manufacturing method, the mold is formed by stereolithography. For this reason, even when the exterior support portion has a complicated shape portion such as a supply pipe support portion, the exterior support portion can be easily manufactured with a small number of steps.
[0052]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, an embodiment of the present invention will be described with reference to FIGS. FIG. 1 is a partially cutaway perspective view showing a blade leading edge 10 according to the present embodiment.
[0053]
The blade leading edge portion 10 includes an exterior portion 20, an exterior support portion 30, and a warm air supply pipe 40. First, the exterior part 20 is demonstrated with reference to FIG. FIG. 2 is a partially cutaway perspective view showing the exterior portion 20.
[0054]
The exterior portion 20 includes first and second exterior elements 21 and 22, a plurality of joint portions 23, a plurality of warm air flow paths 24, a plurality of warm air inlet holes 25, and a plurality of warm air outlet holes 26. ing.
[0055]
The first and second exterior elements 21 and 22 are configured by bending a rectangular plate material into a substantially U-shaped cross section. These first and second exterior elements 21 and 22 are formed in a plate shape from a superplastic material such as 5083-O, for example. In FIG. 1, the longitudinal direction of the first exterior element 21 is indicated by the reference symbol X.
[0056]
The second exterior element 22 is disposed such that its longitudinal direction substantially coincides with the longitudinal direction X of the first exterior element 21. Further, the second exterior element 22 is disposed inside the first exterior element 21. In other words, the second exterior element 22 is disposed such that its outer surface and the inner surface of the first exterior element 21 face each other.
[0057]
The plurality of joints 23 are disposed between the first exterior element 21 and the second exterior element 22. More specifically, the plurality of joint portions 23 are disposed between the inner surface of the first exterior element 21 and the outer surface of the second exterior element.
[0058]
In addition, each joint 23 is disposed substantially entirely in the direction intersecting the longitudinal direction X between the first exterior element 21 and the second exterior element 22. At the same time, each joint 23 is arranged at a predetermined distance from each other so as not to contact the adjacent joint 23. More specifically, each joint 23 extends in a direction substantially parallel to the adjacent joint 23 with a predetermined interval. The joint portion 23 having such an arrangement joins the first exterior element 21 and the second exterior element 22.
[0059]
Each warm air flow path 24 is defined by a joint portion 23, a first exterior element 21, and a second exterior element 22 that are adjacent to each other. For this reason, each warm air flow path 24 is extended substantially parallel to the direction where the junction part 23 is extended. That is, each warm air flow path 24 extends in a direction intersecting the longitudinal direction X.
[0060]
As shown in FIG. 2, the plurality of warm air inlet holes 25 are provided at the top of the second exterior element 22 having a U-shaped cross section. In addition, each warm air inlet hole 25 is disposed at a position corresponding to each warm air flow path 24 in the longitudinal direction of the exterior portion 20.
[0061]
The plurality of warm air outlet holes 26 are provided on both ends of the second exterior element 22 having a U-shaped cross section. In addition, each warm air inlet hole 25 is disposed at a position corresponding to each warm air flow path 24 in the longitudinal direction of the exterior portion 20. For this reason, it can be said that two warm air outlet holes 26 are provided corresponding to each warm air flow path 24.
[0062]
Here, the exterior support part 30 will be described with reference to FIG. 1 again. The exterior support part 30 includes a support part main body 31, a supply pipe support part 32, a rib 33, and an opening 34.
[0063]
The support part main body 31 has the dimension along the longitudinal direction substantially the same as the exterior part 20. Further, as shown in FIG. 3, the support portion main body 31 includes a front portion 35 that faces the exterior portion 20 in a direction intersecting the longitudinal direction of the support portion main body 31, an exposed portion 36 that is exposed to the outside, and an exterior portion. 20 has an exterior connecting portion 37 to which 20 is connected, and a main wing connecting portion 39 for connecting to the main wing body side structure of the aircraft.
[0064]
The front portion 35 has an acute angle portion 38 having a surface 38a and a surface 38b. The acute angle portion 38 is configured such that the angle formed by the surface 38a and the surface 38b has an acute angle. The tip of the front portion 35 in the direction intersecting the longitudinal direction, that is, the tip of the acute angle portion 38 has a space between the exterior portion 20.
[0065]
The exposed part 36 constitutes the outer surface of the main wing of the aircraft together with the exterior part 20. Both end portions along the longitudinal direction of the exterior portion having a U-shaped cross section are attached to the exterior connection portion 37. In the exterior connection part 37, the exterior part 20 and the exterior support part 30 are connected by a known connection member such as a rivet, for example. In this connection, the exterior part 20 and the exterior support part 30 are disposed so that their longitudinal directions substantially coincide with each other.
[0066]
A plurality of main wing coupling portions 39 are provided at predetermined intervals over the entire longitudinal direction of the support portion main body 31. As shown in FIG. 4, these main wing connecting portions 39 are provided with screw holes 39a, and the main wing body side structure of the main wing and the blade leading edge portion 10 are detachably connected by screws. Can do. When the wing leading edge portion 10 is attached to the main wing main body side structure in this manner, the exterior portion 20 is positioned on the front side of the aircraft, and the exterior support portion 30 is positioned on the rear side of the aircraft. In particular, the front end of the exterior portion 20 is disposed so as to protrude toward the front of the aircraft.
[0067]
A plurality of supply pipe support portions 32 are provided at predetermined intervals over the entire longitudinal direction of the support portion main body 31. These supply pipe support portions 32 are arranged at positions facing the exterior portion 20, that is, at the front portion 35 in a direction intersecting the longitudinal direction of the support portion main body 31. These supply pipe support portions 32 support the warm air supply pipe 40. At this time, the warm air supply pipe 40 is disposed so as to be separated from the exterior portion 20 by a predetermined distance.
[0068]
A plurality of ribs 33 are provided at predetermined intervals over the entire longitudinal direction of the support portion main body 31. These ribs 33 reinforce the support body 31.
[0069]
The opening 34 is provided between the distal end of the support portion main body 31 and the exterior connection portion 37. A plurality of openings 34 are provided at predetermined intervals over the entire longitudinal direction of the support body 31. These openings 34 are a space defined by the exterior portion 20 and the front portion 35 of the support portion main body 31 and a space surrounded by the inner surface of the support portion main body 31 (the side where the ribs 33 are provided). Communication). Therefore, the opening 34 can flow through the warm air flow path 24 and allow the warm air discharged from the warm air outlet hole 26 to pass through the exterior support portion 30. Moreover, these openings 34 are distributed to such an extent that the strength of the exterior support part 30 is not impaired, and the exterior support part 30 is reduced in weight.
[0070]
In addition, the support part main body 31 mentioned above, the supply pipe support part 32, and the rib 33 are integrally formed. The front portion 35, the exposed portion 36, the exterior connecting portion 37, and the main wing connecting portion 39 of the support portion main body 31 are also integrally formed. The main wing connecting portion 39 is a connecting portion to the main wing main body side structure.
[0071]
The warm air supply pipe 40 is detachably supported by the supply pipe support portion 32 and is disposed over the entire longitudinal direction of the blade leading edge portion 10. The warm air supply pipe 40 is connected to a warm air supply source (not shown) and supplies warm air to the blade leading edge portion 10. Further, as shown in FIG. 3, the warm air supply pipe 40 is provided with a warm air discharge hole 41 at a position facing the warm air inlet hole 25 of the exterior portion 20. Thereby, the warm air supplied by the warm air supply pipe 40 can enter the warm air flow path 24 from the warm air inlet hole 25 and flow in the warm air flow path 24. The warm air flowing through the warm air flow path 24 is discharged from the warm air outlet hole 26. In this manner, the warm air supply pipe 40 and the warm air flow path 24 constitute an anti-icing mechanism and prevent the blade leading edge 10 from freezing.
[0072]
As shown in the above configuration, the blade leading edge 10 is
1) The exterior portion 20 is configured by joining and bending the plate-like first and second exterior elements 21 and 22,
2) The exterior support part 30 integrally constitutes a support part main body 31, a supply pipe support part 32, and a rib 33.
[0073]
With these two points, the blade leading edge portion 10 can be configured with a small number of parts while having an anti-icing mechanism, and the manufacturing cost can be suppressed.
[0074]
In addition, as shown in the above configuration, the blade leading edge portion 10 is configured such that the exterior portion 20 and the exterior support portion 30 are configured separately, and the exterior portion 20 and the exterior support portion 30 are detachably connected. ing. For this reason, the blade leading edge portion 10 can replace the exterior portion 20. For this reason, the blade leading edge 10 can reduce the cost for repair. Further, the blade leading edge portion 10 can maintain the exterior support portion 30 and / or the warm air supply pipe 40 with the exterior portion 20 removed. Therefore, the blade leading edge 10 can be easily maintained.
[0075]
Moreover, since the warm air supply pipe | tube 40 of this Embodiment is supported so that attachment or detachment is possible, replacement | exchange is easy.
[0076]
Moreover, since the exterior support part 30 of the present embodiment is detachable from the main wing body side structure, it can be easily replaced and / or maintained.
[0077]
In addition, in this Embodiment, although the junction part 23 is extended over the whole in the direction which cross | intersects the longitudinal direction X, if the following three points are satisfy | filled, it will not be limited in arrangement | positioning.
[0078]
1) The 1st and 2nd exterior elements 21 and 22 can be joined reliably.
[0079]
2) Warm air can be guided so that each warm air flow path 24 can flow throughout the exterior portion 20.
[0080]
3) Each joint portion 23 is constituted by a linear single portion or a plurality of portions extending in a direction intersecting the longitudinal direction of the first exterior element 21.
[0081]
If these conditions are satisfied, the joint portion 23 may be disposed intermittently in a direction intersecting the longitudinal direction X so that the adjacent warm air flow paths 24 communicate with each other. Moreover, the junction part 23 can be arrange | positioned so that the meandering warm air flow path 24 may be prescribed | regulated. In addition, it is preferable that each joining part 23 is comprised by the linear single part extended in the direction which cross | intersects the longitudinal direction of the 1st exterior element 21, in order to make a process easy.
[0082]
Note that the blade leading edge portion 10 of the present embodiment is connected to the main wing by screws at the main wing connecting portion 39. The wing leading edge 10 can be attached to and detached from the main wing main body side structure, and can be connected by any known connecting member as long as it can be connected with a desired strength.
[0083]
Further, in the present embodiment, the front portion 35 of the exterior support portion 30 has the acute angle portion 38, but may be configured in any shape.
[0084]
(Production method)
Hereinafter, a method for manufacturing the blade leading edge 10 having the above-described configuration will be described with reference to FIG. FIG. 5 is a perspective view showing the exterior part 20 before superplastic forming.
[0085]
The method for manufacturing the blade leading edge portion 10 of the present embodiment includes an exterior portion forming step for forming the exterior portion 20, a casting step for manufacturing the exterior support portion 30, and a warm air supply to the exterior support portion 30. And an assembly process for attaching the tube 40 and the exterior part 20. Below, the said exterior part formation process is demonstrated in detail.
[0086]
[Exterior forming process]
In the exterior part forming step, the following three operations are performed.
[0087]
(Operation a) The flat plate-like first and second exterior elements 21 and 22 are overlapped.
[0088]
(Operation b) The exterior portion 20 is formed by joining the first and second exterior elements 21 and 22.
[0089]
(Operation c) The warm air flow path 24 is formed by superplastic forming in the exterior portion 20 formed in the operation b, and the exterior portion 20 is curved.
[0090]
First, the operation a in the exterior part forming process will be described.
[0091]
(Work a)
In the operation a, first, the first exterior element 21 and the second exterior element 22 are prepared. The first exterior element 21 and the second exterior element 22 are flat members made of a superplastic material. The first exterior element 21 and the second exterior element 22 have substantially the same dimensions.
[0092]
Subsequently, the first exterior element 21 and the second exterior element 22 are overlapped. At this time, the first exterior element 21 and the second exterior element 22 are arranged so that their relative positions substantially coincide with each other. For this reason, the longitudinal direction of the 1st exterior element 21 and the 2nd exterior element 22 corresponds.
[0093]
In this way, when the operation a is completed, the operation b is subsequently performed. The operation b will be described below.
[0094]
(Work b)
In this operation b, the first exterior element 21 and the second exterior element 22 are joined by ultrasonic joining. This ultrasonic bonding is performed in a direction intersecting the longitudinal direction X in a state where the first exterior element 21 and the second exterior element 22 are overlapped. Thereby, the junction part 23 is formed in the direction which cross | intersects the longitudinal direction X of a 1st exterior element. In order to join the first exterior element 21 and the second exterior element 22 with certainty, the joint portion 23 is spaced apart from the adjacent joint portion 23 along the longitudinal direction of the second exterior element 22 by a predetermined distance. A plurality are formed. As described above, since a plurality of joints are arranged, each joint 23 and the joint 23 adjacent along the longitudinal direction of the second exterior element 22 have a parallel positional relationship.
[0095]
The plurality of joints 23 are adjacent to each other such that a warm air inlet hole 25 and a warm air outlet hole 26 described later are disposed between each joint 23 and the adjacent joint 23. The portion 23 is separated from the portion 23 by a predetermined distance along the longitudinal direction of the second exterior element 22.
[0096]
Further, as shown in FIG. 5, each joint 23 extends substantially linearly in the direction intersecting the longitudinal direction of the second exterior element 22. For this reason, the both ends of the junction part 23 are arrange | positioned in the vicinity of the both edge parts along the longitudinal direction of the exterior part 20, respectively.
[0097]
In addition, each end portion of the joint portion 23 is formed so as to be separated by a predetermined distance from both edges along the longitudinal direction of the exterior portion 20 in a direction orthogonal to the longitudinal direction of the exterior portion 20.
[0098]
In addition, although the said joining can be achieved by joining methods, such as well-known welding and adhesion | attachment, ultrasonic joining is preferable. When the joining is performed by ultrasonic joining, the first and second exterior elements 21 and 22 can be stacked. For this reason, it can prevent that the relative position of the 1st and 2nd exterior elements 21 and 22 shifts at the time of joining. Moreover, since the said joining should just be performed so that the junction part 23 may be extended linearly in the direction orthogonal to the longitudinal direction of the 2nd exterior element 22, it can process easily. In addition, since the above-mentioned joining only needs to keep the positional relationship between each joining part and the adjacent joining part in parallel, precise machining accuracy is not required and the machining operation can be easily performed.
[0099]
Moreover, since the said joining uses ultrasonic joining and can join without the said 1st and 2nd exterior element washing | cleaning specially, it can be performed without performing a complicated operation | work.
[0100]
In this way, when the operation b is completed, the operation c is subsequently performed. The operation c will be described below.
[0101]
(Work c)
In the operation c, the warm air flow path 24 is formed by superplastic forming the exterior portion 20 formed in the operation b on the exterior portion 20 formed in the operation b with the superplastic forming apparatus 50 shown in FIG. At the same time, the exterior portion 20 is curved.
[0102]
The superplastic forming apparatus 50 includes a female mold 51, a male mold 52, and a gas supply mechanism 53 that is a gas supply means. Below, the structure of the female type | mold 51 and the male type | mold 52 is demonstrated in detail.
[0103]
The female mold 51 and the male mold 52 have the same dimension along the longitudinal direction as the exterior portion 20. The female die 51 has a recess 51a. The recess 51a has two edges 51b and 51c along the longitudinal direction of the female mold 51 (the front-rear direction of the paper surface in FIG. 8). Moreover, the recessed part 51a has the some entrance hole formation convex part 55b. These inlet hole forming convex portions 55 b are arranged at predetermined intervals along the longitudinal direction of the female die 51. The inlet hole forming convex portions 55b are arranged at substantially the same interval as the joint portion 23 described above. Further, the row of the inlet hole forming convex portions 55b is substantially parallel to the edge 51b, and is separated from the edge 51b by a predetermined distance in the direction from the edge 51b toward the bottom of the concave portion 51a.
[0104]
Moreover, the recessed part 51a has the some entrance hole formation convex part 55c. The inlet hole forming convex portions 55c are arranged at substantially the same interval as the above-described joint portion 23 along the longitudinal direction of the female mold 51, like the inlet hole forming convex portions 55b. The row of the inlet hole forming convex portions 55c is substantially parallel to the edge 51c, and is spaced a predetermined distance from the edge 51c in the direction from the edge 51c toward the bottom of the concave portion 51a. Note that the row of the inlet hole forming convex portions 55 b and the row of the inlet hole forming convex portions 55 c face each other in a direction orthogonal to the longitudinal direction of the female mold 51.
[0105]
Moreover, the recessed part 51a has the some exit hole formation convex part 55d in the bottom part. The outlet hole forming convex portions 55d are arranged at substantially the same intervals as the inlet hole forming convex portions 55b and 55c.
[0106]
Each of the inlet hole forming convex portions 55b and 55c and each of the outlet hole forming convex portions 55d are arranged so that the positions along the longitudinal direction of the female mold 51 (the front-rear direction of the page in FIG. 8) are substantially coincident. ing. In other words, the respective inlet hole forming convex portions 55 b and c and the respective outlet hole forming convex portions 55 d are arranged in a direction orthogonal to the longitudinal direction of the female mold 51.
[0107]
The male mold 52 has a dimension along the longitudinal direction which is substantially the same as that of the exterior portion 20. Further, when the male mold 52 completely overlaps the female mold 51, the plurality of holes 52b and c for accommodating the respective inlet hole forming convex portions 55b and c, and the plurality of holes for accommodating the respective outlet hole forming convex portions 55d. And a hole 52d. These holes 52b, c, d are arranged along the longitudinal direction of the male mold 52 at substantially the same intervals as the respective inlet hole forming convex portions 55b, c.
[0108]
The superplastic forming apparatus 50 is configured to be able to curve the exterior portion 20 into a desired shape by causing the above-described female mold 51 and male mold 52 to cooperate.
[0109]
The gas supply mechanism 53 has a gas inlet 54 through which gas can be injected over the entire longitudinal direction of the exterior portion 20. The gas supply mechanism 53 can inject gas from the gas inlet 54.
[0110]
In operation c, first, the exterior portion 20 is disposed on the female mold 51. In addition, the exterior part 20 is arrange | positioned so that the 2nd exterior element 22 may come inside when it curves. That is, the second exterior element 22 is disposed so as to face the male mold 52.
[0111]
At the same time, the gas inlet 54 of the gas supply mechanism 53 is disposed on the entire edge of the exterior portion 20 along the longitudinal direction. More specifically, the gas supply mechanism 53 is arranged such that the relative position with respect to the exterior portion 20 is adjusted so that the gas inlet 54 is located between the first exterior element 21 and the second exterior element 22. .
[0112]
Further, the exterior portion 20 is disposed on the female die 51 so that the respective inlet hole forming convex portions 55b and 55c and the respective outlet hole forming convex portions 55d are positioned between the joint portions 23 adjacent to each other. . The exterior portion 20 is disposed on the female die 51 so that the warm air outlet hole 26 is positioned inside the end portion of the joint portion 23 in the direction orthogonal to the longitudinal direction of the exterior portion 20. For this reason, the area | region where the junction part 23, the warm air exit hole 26, and the junction part 23 are not arrange | positioned is provided in the vicinity of the both edges along the longitudinal direction of the exterior part 20. FIG.
[0113]
Thus, when the exterior part 20 is arrange | positioned on the superplastic forming apparatus 50, the gas supply mechanism 53 will inject | pour gas between the 1st exterior element 21 and the 2nd exterior element 22 continuously. At the same time, the male mold 52 starts pressing the exterior part 20. By the gas injection, the gas is sent to a plurality of regions defined by the joint portion 23, the first exterior element 21, and the second exterior element 22. Thereby, the several area | region demarcated by the junction part 23, the 1st exterior element 21, and the 2nd exterior element 22 swells. Thereby, the said area | region is superplastic forming and the warm air flow path 24 is shape | molded. The exterior portion 20 has a plurality of protruding portions on the second exterior element 22 side at positions corresponding to the respective inlet hole forming convex portions 55b, 55c and the outlet hole forming convex portions 55d. Simultaneously with the formation of the warm air flow path 24, the exterior portion 20 is bent into a desired shape by the female mold 51 and the male mold 52.
[0114]
Subsequently, a plurality of protruding portions of the above-described second exterior element 22 are cut off from the exterior portion 20 curved as described above. Thereby, a plurality of warm air inlet holes 25 and warm air outlet holes 26 are formed in the second exterior element 22. Specifically, the warm air inlet hole 25 is formed by cutting out a portion projected by each outlet hole forming convex portion 56. Moreover, the warm air outlet hole 26 is formed by cutting out the part protruded by each inlet hole formation convex part 55b, c. By these, the exterior part 20 is shape | molded.
[0115]
Each warm air inlet hole 25 is formed at a substantially central position along a direction orthogonal to the longitudinal direction of the second exterior element 22.
[0116]
Further, a plurality of warm air outlet holes 26 are formed in the vicinity of both edges along the longitudinal direction of the second exterior element 22 at the same spacing as the warm air inlet holes 25 along the longitudinal direction of the second exterior element 22. . For this reason, the warm air inlet hole 25 and the warm air outlet hole 26 are formed side by side in a direction orthogonal to the longitudinal direction of the second exterior element 22. In other words, the second exterior element 22 is provided with the warm air outlet holes 26 at both ends in the direction orthogonal to the longitudinal direction of the second exterior element 22, and the warm air inlet holes 25 are provided between the warm air outlet holes 26. Therefore, the second exterior element 22 has a group of warm air inlet holes 25 and warm air outlet holes 26 (hereinafter referred to as a hole group) arranged in a row in a direction orthogonal to the longitudinal direction. I can say that. A plurality of the hole groups in a row are provided in parallel along the longitudinal direction of the second exterior element 22 with a predetermined distance therebetween.
[0117]
The arrangement of the warm air inlet hole 25 and the warm air outlet hole 26 arranged in the second exterior element 22 as described above can be rephrased as follows. It can be said that in the longitudinal direction of the second exterior element 22, one row composed of a plurality of warm air inlet holes 25 and two rows composed of a plurality of warm air outlet holes 26 are formed. In addition, the row | line | column of the warm air exit hole 26 is formed so that a predetermined distance may be separated from the both edges along the longitudinal direction of the 2nd exterior element 22 in the direction orthogonal to the longitudinal direction of the 2nd exterior element 22. FIG.
[0118]
Next, the casting process will be described.
[0119]
[Casting process]
In this casting process, first, a mold for casting the exterior support portion 30 is made by stereolithography. In addition, the said type | mold can be formed for the exterior support part 30 by well-known methods other than optical modeling. In addition, since the exterior support part 30 has the support part main body 31, the supply pipe support part 32, and the rib 33, it is a complicated shape. For this reason, when the said mold | type is formed by optical modeling, since the type | mold of the exterior support part 30 can be formed more easily, it is preferable. The mold is preferably formed by a lost wax method. The mold is preferably formed with high accuracy so that the exterior support 30 can be precision cast.
[0120]
Subsequently, the exterior support part 30 is cast by the mold. Since the exterior support part 30 is formed by casting, all members can be integrally formed. For this reason, the exterior support part 30 can be configured to have a plurality of members without performing complicated assembly operations. In addition, a casting process may be performed before, after, or simultaneously with an exterior part formation process.
[0121]
In addition, it is preferable that the said exterior support part 30 is precision cast. The precision casting forms a casting with high accuracy. For this reason, the precision cast exterior support portion 30 can be easily manufactured with a reduced number of processing after casting. In addition, the said exterior support part 30 can also be formed by well-known casting.
[0122]
Next, the assembly process will be described.
[0123]
[Assembly process]
This assembly process is performed after the exterior portion forming process and the casting process are completed. First, a separately manufactured warm air supply pipe 40 is attached to the supply pipe support section 32 on the exterior support section 30 formed by the casting process. A warm air discharge hole 41 is opened in the warm air supply pipe 40. These warm air discharge holes 41 are arranged at positions facing each of the plurality of warm air inlet holes 25 of the exterior portion when the blade leading edge portion 10 is completed.
[0124]
Subsequently, the exterior part 20 is attached to the exterior support part 30. The exterior portion 20 is connected to the exterior connection portion 37 of the exterior support portion 30 in a region where the warm air outlet hole 26 and the joint portion 23 in the vicinity of both edges along the longitudinal direction of the exterior portion 20 described above are not disposed. They are connected by a known connecting member such as a rivet.
[0125]
As described above, assembling the blade leading edge 10 only attaches the exterior part 20 and the warm air supply pipe 40 to the exterior support part 30. For this reason, the blade leading edge portion 10 can be easily assembled without requiring attachment of fine parts or complicated work. Thus, the blade leading edge 10 is completed when the assembly process is completed.
[0126]
In the method for manufacturing the blade leading edge portion 10 of the present embodiment, the warm air flow path 24 is defined by the plate-like first and second exterior elements 21 and 22 and the linear joint portions 23 adjacent to each other. It is formed by flowing gas into the region. For this reason, the said manufacturing method can manufacture the said warm air flow path, without requesting | requiring high process precision. Moreover, the said junction part is formed in linear form. For this reason, the said manufacturing method can form a junction easily even when a some junction is manufactured.
[0127]
Since the exterior support part is formed by stereolithography, the support part body can be easily manufactured with a small number of steps even when the exterior support part has a complicatedly shaped part such as a supply pipe support part.
[0128]
Furthermore, the exterior part, the exterior support part, and the warm air supply pipe are manufactured separately. For this reason, the blade leading edge manufactured by this manufacturing method can replace only the damaged member even when the above-mentioned members are damaged. For this reason, this manufacturing method is easy to maintain and can manufacture a low-cost blade leading edge.
[0129]
Although several embodiments have been specifically described so far with reference to the drawings, the present invention is not limited to the above-described embodiments, and all the embodiments performed without departing from the scope of the invention are not limited thereto. Including implementation.
[0130]
【The invention's effect】
The present invention can provide an aircraft wing leading edge that can be easily manufactured. Moreover, this invention can provide the manufacturing method of the aircraft wing front edge part which manufactures the front edge part of an aircraft wing easily.
[Brief description of the drawings]
FIG. 1 is a partially cutaway perspective view showing a blade leading edge according to an embodiment of the present invention.
FIG. 2 is a partially cutaway perspective view showing the exterior part of FIG. 1;
3 is a cross-sectional view taken along a cutting line AA in FIG. 1. FIG.
4 is a cross-sectional view taken along a cutting line BB in FIG. 1. FIG.
FIG. 5 is a perspective view showing an exterior part before superplastic forming.
FIG. 6 is a cross-sectional view showing a superplastic forming apparatus.
FIG. 7 is a partially cutaway perspective view showing a conventional blade leading edge.
FIG. 8 is a cross-sectional view taken along the line AA in FIG. 7;
FIG. 9 is a partially cutaway perspective view showing a laminated body before superplastic forming.
FIG. 10 is a cross-sectional view taken along a cutting line AA in FIG. 9;
FIG. 11 is a cross-sectional view showing a superplastic molded laminate.
[Explanation of symbols]
10 Wing leading edge
20 Exterior part
21 First exterior element
22 Second exterior element
23 joints
24 Warm air flow path
25 Warm air inlet hole
26 Warm air outlet hole
30 Exterior support
31 Support body
32 Supply pipe support
33 Ribs
40 Warm air supply pipe
41 Warm air exhaust hole
50 Superplastic forming equipment
51 female
52 male
53 Gas supply mechanism
54 Gas inlet

Claims (4)

a) . A rectangular flat plate-shaped first and second exterior element made of superplastic material and having the same dimensions are overlapped,
b) . The first exterior element and the second exterior element are ultrasonically joined to a plurality of joints extending linearly in a direction intersecting the longitudinal direction at a plurality of positions spaced apart from each other along the longitudinal direction of the first and second exterior elements. Join the exterior element to form the exterior part,
c) . The gas supply means for supplying a gas, a plurality of between-free write send gas to the region defined by the junction adjacent the first exterior component and a second exterior element to each other at the outer portion, the outer portion second The exterior element is directed to the male mold and pushed into the female recess by the male mold, and the plurality of regions are expanded by superplastic forming to form a plurality of warm air flow paths and the exterior section is curved into the female mold recess. In addition, a plurality of protrusions corresponding to each of the plurality of regions are formed on the exterior portion by the protrusions of the female recess corresponding to each of the plurality of regions. Forming part,
d) . Cutting out the protruding portions of the plurality of convex portions of the second exterior element to form a warm air inlet hole and a warm air outlet hole in the plurality of warm air flow paths inflated from the plurality of regions ;
Exterior part forming step: and a). A main wing main body side structure having an exterior connecting portion that has the same longitudinal dimension as that of the exterior portion and is connected to both ends of the curved exterior portion at one end in a direction intersecting the longitudinal direction. A support wing main body having a main wing connection portion connected to the other end portion in a direction intersecting the longitudinal direction and having a front portion facing the curved exterior portion connected to the exterior connection portion ; ,
b). A supply pipe support part that supports a warm air supply pipe provided at a predetermined interval in the longitudinal direction of the support part body at the front part of the support part body ;
c). A rib that is provided at a predetermined interval in the longitudinal direction of the support body and reinforces the support body;
A casting step of precisely casting the exterior support part having: and the supply part support part of the exterior support part to support the warm air supply pipe and the exterior part curved to the exterior connection part of the exterior support part An assembly process for connecting both ends of the aircraft: A method of manufacturing an aircraft wing leading edge comprising: The extended end portion of each joint portion is disposed so as to face the edge portion along the longitudinal direction of the exterior portion,
The gas supply means is disposed at the edge of the front Kigaiso portion, feeding the gas into a plurality of regions defined by said joint portion and the first exterior component and a second exterior elements adjacent to each other,
The method for manufacturing an aircraft wing leading edge according to claim 1 . The method of manufacturing an aircraft wing leading edge according to claim 1 , wherein each joint is formed along a direction orthogonal to the longitudinal direction of the exterior part. The aircraft wing leading edge manufacturing method according to claim 1 , wherein a mold formed by stereolithography is used in the precision casting.

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