JP3600179B2 - Internal pressure release structure of wing - Google Patents

Description

[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to a structure of a wing of an aircraft, and particularly to a structure for releasing internal pressure of a wing.
[0002]
[Prior art]
The wing outer wing at the tip of the wing of the aircraft functions to gain lift during flight and support the aircraft in the air. The tail mounted behind the aircraft consists of a horizontal tail and a vertical tail.The horizontal tail balances the aerodynamic force acting on the fuselage around the center of gravity of the fuselage to maintain vertical stability. . The vertical tail keeps the aircraft stable in direction and controls the aircraft's sideslip. Thus, the outer wings and tails are essential wings for an aircraft to fly safely.
[0003]
A conventional large aircraft wing has a multi-layer structure including a spar extending in the longitudinal direction of the wing, ribs arranged perpendicular to the spar, a skin, and a number of stringers fixed to the skin from the inside of the wing. Stringer structures are often used. In the multi-stringer structure, a bending moment and a shearing force act on the outer plate and the stringer, similarly to the spar, and a torsional moment acts on the outer plate and the spar.
[0004]
FIG. 12 is a cross-sectional view showing a state when the explosive bomb 2 collides with the target. As shown in FIG. 12 (1), when the explosive bomb 2 lands on the outer plate 1 of the object, the explosive 3 of the explosive bomb 2 explodes, and as shown in FIG. 12 (2), the blast generated by the explosion At the same time, the small pieces 4 are released from the explosive bombs and scatter into the inner space of the target object.
[0005]
FIG. 13 is a cross-sectional view showing a state when the explosive bomb 2 collides with the wing 5. When the explosive bomb 2 lands on the outer plate 6 of the wing 5 as shown in FIG. 13A, the explosive of the explosive bomb 2 explodes, and as shown in FIG. A small piece 4 is released from the explosive bomb 2 and scatters in the inner space of the wing 5. The blast fills the inner space of the wing 5 and exerts excessive pressure on the outer plate 6, the girder and the stringer as the reinforcing material, and the thin-walled member, as shown in FIG. Damage to the components. The blast continues to apply pressure to the member until the member is destroyed and the blast has all exited the wing. As a result, as shown in FIG. 13D, members including the outer plate 6 are scattered. Thus, the wings 5 are fatally damaged by the explosive bullets 2.
[0006]
[Problems to be solved by the invention]
As noted above, damage to key structural components of the wing, such as skins, stringers, girders, and ribs, renders the wing unable to maintain its wing shape and cannot guarantee safe flight of the aircraft.
[0007]
When the explosive bomb lands on the wing of the aircraft and explodes, as shown in FIG. 13 (3), the structural member such as the outer panel 6 is deformed by the blast, and the small piece 4 forms a through hole in the structural member. . The blast destroys the skin extensively, especially on wings with thin skins such as the wing wings and tails of large aircraft. If the skin is extensively destroyed, the girders and ribs will be severely damaged.
[0008]
In order to prevent the wing from being destroyed as much as possible by the blast generated inside the wing, the members that do not apply much load such as axial force are actively destroyed at the time of the explosion, and from the place where the members were destroyed There is a need for a wing structure that escapes the blast and prevents major structural members of the wing and the joints between the members from being damaged by the blast.
[0009]
An object of the present invention is to provide an internal pressure release structure of a wing that can reduce damage caused by a blast due to a burst bomb.
[0010]
[Means for Solving the Problems]
The present invention relates to an aircraft wing having an internal structure covered with a skin,
The outer plate is partially formed separately from the rest,
A part of the outer plate has a lower bending rigidity than the remaining portion of the outer plate, and is bonded and joined to the remaining portion,
The remaining portion of the skin is a wing internal pressure release structure that is fastened to the internal structure using fasteners.
[0011]
According to the present invention, a part of the outer plate is formed separately from the remaining portion of the outer plate, has lower bending rigidity than the remaining portion of the outer plate, and is provided by being adhered to the remaining portion. With such a configuration, when the pressure in the wing rises, a portion of the outer plate having a low bending stiffness is deformed before the remaining portion of the outer plate having a high bending stiffness, thereby changing the bending stiffness. Therefore, stress can be concentrated on a portion where the part of the outer plate and the remaining part are joined. As a result, when the pressure in the wing rises and becomes equal to or higher than a predetermined pressure, the separation at the joined portion is advanced, and a part of the outer plate can be scattered. In this way, only a portion of the skin can be scattered without damaging the remaining portion of the skin. Therefore, it is possible to prevent large damage that affects most of the outer skin, and to prevent most of the outer skin from being scattered, and to maintain the shape of the wing, so that safe flight of the aircraft can be continued.
In addition, the remaining part of the outer plate is fastened to the internal structure using fasteners, so when the pressure in the wing rises and part of the outer plate scatters, the remaining part of the outer plate is damaged, And can be prevented from scattering. Therefore, it is possible to reliably prevent large damage affecting most of the outer panel and scattering of most of the outer panel.
[0012]
Further, the present invention is characterized in that a portion where a part of the outer plate is joined to a remaining portion of the outer plate protrudes outward toward the outside of the wing.
[0013]
According to the present invention, the part where the part of the outer plate and the remaining part are joined is formed so as to protrude outward as it goes outward from the wing. If stress is concentrated on a portion where the remaining portion is joined, the peeling easily progresses, so that a part of the outer plate can be easily scattered.
[0014]
Further, according to the present invention, a part of the outer plate and a remaining portion of the outer plate are formed by laminating a plurality of layer portions, and a portion where the part of the outer plate is joined to the remaining portion of the outer plate is a step. It is characterized by being formed in a shape.
[0015]
According to the present invention, the part where the part of the outer plate and the remaining part of the outer plate are joined is formed in a step shape. By forming the joining portion in a stepped manner in this way, the joining area can be increased as compared with the case where the joining portion is formed in a straight line. In order to reduce the rigidity of a part of the skin in comparison with the remaining part, even if the thickness is reduced, the well must be pitted without being damaged by pneumatic force acting on the skin during normal navigation. The joining force which can be obtained can be obtained. In this way, after obtaining sufficient bonding strength for normal navigation, bonding by bonding is vulnerable to shocking pressure such as blast, and a part of the outer plate can be easily scattered .
[0020]
BEST MODE FOR CARRYING OUT THE INVENTION
FIG. 1 is a perspective view showing an aircraft 11 using an internal pressure release structure of a wing according to one embodiment of the present invention. The internal pressure release structure of the wing according to the present embodiment is used for tail fin 15 and main wing outer wing 13. The main wing outer wing 13 is a tip of a main wing 14 of the aircraft 11 that functions to obtain lift during flight and support the aircraft in the air. The tail unit 15 arranged behind the aircraft 11 is configured to include a horizontal tail unit 12 and a vertical tail unit 16. The horizontal tail unit 12 balances the air force acting on the fuselage around the center of gravity of the fuselage, thereby stabilizing the pitch direction. It works to keep. The vertical stabilizer 16 functions to maintain the stability of the fuselage in the yaw direction and to control the skidding of the fuselage.
[0021]
FIG. 2 is a perspective view showing the horizontal stabilizer 12 of the aircraft 11. The horizontal stabilizer 12 includes a horizontal stabilizer 21 fixed to the fuselage and a movable blade 22 that can be displaced. The horizontal stabilizer 21 includes a leading edge 23, a trailing edge 24, and an inter-spar structure 25 arranged between the leading edge 23 and the trailing edge 24. The rotor blade 22 is directly connected to the trailing edge 24 so as to be angularly displaceable.
[0022]
FIG. 3 is a perspective view showing the internal structure 21 a of the horizontal stabilizer 21 of the horizontal stabilizer 12. The internal structure 21a extends in the longitudinal direction of the horizontal fin (hereinafter may be referred to as “wing”) 12 in the longitudinal direction of the wing 12, and extends in the longitudinal direction of the wing 12. The rear spar 27 to be arranged extends in the chord direction, is arranged at predetermined intervals in the longitudinal direction of the wing 12, and has a plurality of ribs 28 connected to the front spar 26 and the rear spar 27, in the longitudinal direction of the wing 12. A leading edge reinforcement member 29a extending on the chordwise leading edge side of the leading spar 26; a trailing edge reinforcing member 29b extending in the longitudinal direction of the wing 12 and being placed on the chordwise trailing edge side of the trailing spar 27; It includes a plurality of first connecting members 30a for connecting the reinforcing member 29a and the front spar 26, and a plurality of second connecting members 30b for connecting the rear edge reinforcing member 29b and the rear spar 27. The front girder 26, the rear girder 27, the rib 28, the front edge reinforcing member 29a, the rear edge reinforcing member 29b, the first connecting member 30a, and the second connecting member 30b are collectively referred to as internal structural members. The wing 12 is configured by connecting the outer cover 31 so as to cover these internal structural members from the outside.
[0023]
FIG. 4 is an enlarged perspective view of section IV of FIG. 2 showing the structure of the horizontal stabilizer 12 between the front spar 26 and the rear spar 27. The skin body 31 extends in the longitudinal direction of the wing 12 and is fixed to the outer plate 32 and the outer plate 32 between the front spar 26 and the rear spar 27 along the chord direction of the wing 12 from the inside of the wing 12. It is configured to include a plurality of stringers 33 which are reinforcing members to be formed. The outer plate 32 and the stringer 33 are cocure-bonded. The cocure bonding is a method in which the stringer 33 is adhered to the outer plate 32 without curing the formed outer plate 32 and the stringer 33, and the outer plate 32 and the stringer 33 are individually cured and simultaneously impregnated in the stringer 33. This is a joining method of bonding a resin as an adhesive.
[0024]
The stringer 33 is made of a carbon fiber reinforced resin material (abbreviation: CFRP), has a substantially trapezoidal outer shape in a section perpendicular to the axis, and is longer than the two parallel sides of the trapezoid when viewed in the section perpendicular to the axis. The side surface forming one side is bonded to the outer plate 32 from the inner side of the wing. CFRP is a composite material in which a fiber material, for example, carbon fiber is impregnated with a synthetic resin, for example, an epoxy resin. Accordingly, when the explosive bomb explodes inside the wing, the blast due to the explosion flows smoothly around the stringer 33, and the load acting on the stringer 33 by the wind pressure can be reduced.
[0025]
In the present embodiment, the stringer 33 has a substantially trapezoidal cross section perpendicular to the axis. However, the stringer 33 may have a polygonal shape such as a triangle and a cross-sectional shape such as a semicircle such that a blast due to an explosion flows smoothly around the stringer 33. .
[0026]
The inter-spar structure 25 includes a front spar 26, a rear spar 27 and a plurality of ribs 28, and further includes an outer plate 32 and a stringer 33 between the front spar 26 and the rear spar 27. The internal pressure release structure of the wing according to the present invention comprises a part of the outer plate 32 between the front spar 26 and the rear spar 27, and between the rib 28A and the rib 28B adjacent to the rib 28A and extending in the same direction (hereinafter referred to as a rib). , May be referred to as a “scatter plate”.) 34 is realized separately from the remaining portion 32 a of the outer plate 32. The flying plate 34 is not fixed to the front spar 26, the rear spar 27 and the rib 28. The scattering plate 34 and the stringer 33 are cocure-bonded.
[0027]
According to the internal pressure release structure of the wing of the present embodiment, when the pressure in wing 12 increases for some reason and reaches a predetermined pressure or more, scatter plate 34 which is a part of outer plate 32 scatters. Therefore, it is possible to prevent damage to at least the majority of the outer plate 32 and to prevent most of the outer plate 32 from flying, and to maintain the shape of the wings 12, so that the aircraft can safely fly even after the splash plate 34 is scattered. You can continue.
[0028]
Further, according to the internal pressure release structure of the wing of the present embodiment, since scatter plate 34 is separate from remaining portion 32a of outer plate 32, when the pressure in wing 12 becomes a predetermined pressure or more, The flying plate 34 can easily fly.
[0029]
Further, according to the internal pressure release structure of the wing of the present embodiment, the scatter plate 34 and the remaining portion 32a are bonded to each other, so that when the pressure in the wing 12 exceeds a predetermined pressure, the scatter plate 34 is easily And the damage of the remaining portion 32a of the outer plate 32 due to the scattering of the scattering plate 34 can be prevented.
[0030]
FIG. 5 is a sectional view taken along section line S5-S5 in FIG. The flying plate 34 protrudes outward as the outer peripheral portion 35 goes outward of the wing. The flying plate 34 and the remaining portion 32a of the outer plate 32 are cocure-bonded.
[0031]
According to the internal pressure release structure of the wing of the present embodiment, the outer peripheral portion 35 of the scatter plate 34 protrudes outward as it goes to the outside of the wing 12, and thus acts from the outside of the wing 12 to the inside. By the force, the flying plate 34 can withstand without being damaged, and when the pressure in the wing 12 exceeds a predetermined pressure, the flying plate 34 can be easily scattered.
[0032]
FIG. 6 is an enlarged sectional view of section VI of FIG. The remaining portion 32a of the outer plate 32 is formed by laminating a plurality of layer portions made of a composite material in which carbon fiber is impregnated with epoxy resin. For example, the outermost layer portion 37 is made of a ± 45 degree material whose fiber direction, which is the direction in which the fiber extends, forms ± 45 degrees with respect to the longitudinal direction of the blade 12. 12 are formed by laminating a plurality of 0-degree members parallel to the longitudinal direction of the blade 12 and 90-degree members and ± 45-degree members whose fiber directions are perpendicular to the longitudinal direction of the blade 12.
[0033]
The scattering plate 34 is formed by laminating a plurality of layer portions made of a composite material in which carbon fiber is impregnated with an epoxy resin. The plurality of layers are mainly made of a ± 45 ° material whose fiber direction forms 45 ° with respect to the longitudinal direction of the blade. The composite material containing carbon fibers is lightweight and high strength, and does not require fasteners and adhesives to form the flying plate 34. The thickness T1 of the scattering plate 34 is formed smaller than the thickness T2 of the remaining portion 32a.
[0034]
According to the internal pressure release structure of the wing of the present embodiment, the flying plate 34 has a lower bending rigidity than the remaining portion 32a of the outer plate 32. Therefore, when the pressure in the wing 12 increases, the flying plate 34 becomes larger than the remaining portion 32a. Since the scatter plate 34 is deformed first, stress concentrates on a portion where the scatter plate 34 and the remaining portion 32a are joined, so that when the pressure in the wing 12 exceeds a predetermined pressure, the scatter plate 34 , Can be easily scattered.
[0035]
The layer portion of the outer peripheral portion 35 of the scattering plate 34 is laminated so as to protrude outward in a stepwise manner from the inside to the outside of the wing 12. At least the layer portion of the remaining portion 32a of the outer plate 32 that is bonded to the flying plate 34 is laminated so as to protrude outward in a stepwise manner from the outside to the inside of the wing 12. The inner surface of the wing 12 of each layer portion of the outer peripheral portion 35 of the scatter plate 34 is scattered by the remaining portion 32a, which is one step lower toward the inside of the wing 12 than the layer portion of the scatter plate 34. The layer portion of the portion 43 bonded to the plate 34 is cocure bonded to the outer surface of the wing 12.
[0036]
According to the internal pressure release structure of the wing of the present embodiment, the layer portion for bonding scatter plate 34 and remaining portion 32a of outer plate 32 has a stepped shape as described above. The portion 35 is formed so as to protrude linearly outward from the inside to the outside of the wing 12. Similarly, at least a portion 43 of the remaining portion 32 a of the outer plate 32 which is bonded to the scattering plate 34 is a wing. As compared with the case where the shape protrudes linearly outward from the outside toward the inside of the wing 12, the bonding area in the direction from the inside to the outside of the wing 12 can be increased, and Even if the thickness dimension of the outer plate 32 is reduced, it is possible to obtain an adhesive force that can withstand the air force acting on the outer plate 32 without being damaged during normal navigation. Further, since the bonded portion is vulnerable to the impact pressure of the blast, the flying plate 34 can fly very easily.
[0037]
FIG. 7 is an enlarged perspective view of section VII of FIG. FIG. 8 is a sectional view taken along section line S8-S8 in FIG. A rib shear tie 51 connecting the rib 28 and the outer plate 32 has a flat plate-like connecting portion 51a extending in the chord direction C1 of the wing 12 and a center portion of one surface of the connecting portion 51a inward of the wing 12. The rib shear tie 51 is a T-shaped member having an outer shape in a cross section perpendicular to the axis, which has a protrusion 51b extending in the longitudinal direction C1 of the connecting portion 51a. The rib shear tie 51 is fastened to the outer plate 32 via a fastener 52. The fastener 52 has a cylindrical shaft portion 52a, and a substantially frustoconical head portion 52b provided at one end of the shaft portion 52a and increasing in diameter as the distance from the shaft portion 52a increases. The head 52b of the fastener 52 is formed such that its maximum diameter is a sufficiently large dimension that is at least twice the outer diameter of the shaft 52a.
[0038]
A connection region 32b connected to the connection portion 51a of the rib shear tie 51 of the outer plate 32 projects inward of the wing 12 over the chord direction C1 of the wing 12, and its thickness T3 is determined by the axis of the head 52b of the fastener 52. It is formed to have a dimension not less than the thickness T4 in the direction. A plurality of insertion holes 36 penetrating the outer plate 32 in the thickness direction are formed in the connecting region 32b of the outer plate 32 in two rows at a predetermined interval in the chord direction C1. On the outer side of the blade 12 in the insertion hole 36 of the outer plate 32, a substantially truncated cone-shaped recess 54 whose diameter increases toward the outside of the blade 12 is formed. An insertion hole 53 corresponding to the insertion hole 36 of the connection region 32b of the outer plate 32 is formed in the connection portion 51a of the rib shear tie 51. The outer plate 32 and the rib shear tie 51 are connected so that the insertion hole 36 of the outer plate 32 and the insertion hole 53 of the rib shear tie 51 are coaxial.
[0039]
The shaft portion 52a of the fastener 52 is inserted through the insertion hole 36 of the outer plate 32 and the 53 of the rib shear tie 51, and the head portion 52b has a dimple washer (hereinafter referred to as a "washer") used to prevent corrosion by electricity. ) 55 is inserted into the recess 54 of the insertion hole 36 with the interposition of 55. In detail, the washer 55 has a truncated cone-shaped receiving portion 55a and a locking portion 55b that protrudes radially outward from the receiving portion 55a, and the receiving portion 55a of the washer 55 is provided in the recess of the insertion hole 36. The head 52 b of the fastener 52 fits into the receiving portion 55 a of the washer 55. The end face of the head 52b of the fastener 52 is flush with the locking portion 55b of the washer 55, and is substantially flush with the outer surface of the wing of the outer plate 32. When the other end of the shaft portion 52a of the fastener 52 is fitted to the locking member 56, the fastener 52 is locked to the outer plate 32 and the rib shear tie 51, and the outer plate 32 and the rib shear tie 51 are fastened. Further, the outer plate 32 and the rib shear tie 51 are bonded by an adhesive 57.
[0040]
By increasing the head 52b of the fastener 52 and joining the outer plate 32 and the rib shear tie 51 by the fastener 52 with the washer 55 interposed therebetween, the stress acting on the outer plate 32 from the head 52b can be reduced. Therefore, the out-of-plane shear strength of the outer plate 32 can be improved.
[0041]
FIG. 9 is an enlarged perspective view of section IX of FIG. At the end of the stringer 33 that comes into contact with the convex portion 51b of the rib shear tie 51, a fastening portion 61 parallel to the convex portion 51b is provided. The fastening portion 61 is provided with an insertion hole and a recess similar to the insertion hole 36 and the recess 54 provided in the outer plate 32, and the projection 51 b is provided inside the wing of the rib shear tie 51 with a fastening portion 61. Insertion holes corresponding to the insertion holes are provided. The fastener 62 is used to fasten the rib shear tie 51 and the stringer 33 in the same manner as the fastening between the outer plate 32 and the rib shear tie 51 described above.
[0042]
At this time, the axis of the fastener 52 for fastening the outer plate 32 and the rib shear tie 51 and the axis of the fastener 62 for fastening the stringer 33 and the rib shear tie 51 are in an intersecting positional relationship. Since the force acting in the axial direction of the fastener 52 for fastening the outer plate 32 and the rib shear tie 51 also acts on the fastener 62 for fastening the stringer 33 and the rib shear tie 51, in other words, the fastener 52 Can be reduced.
[0043]
The stringer 33 is bonded to the outer plate 32, and the end of the stringer 33 having the fastening portion 61 is also bonded to a joint portion of the rib shear tie 51 with the outer plate 32, thereby further acting on the fastener 52. Power can be reduced.
[0044]
FIG. 10 is a perspective view showing the rib 28. The rib 28 includes a rib shear tie 51 and a web 71. The web 71 has a plate shape and is joined to the convex portion 51 b inward of the wing of the rib shear tie 51. A plurality of holes 72 are formed in the web 71. The blast generated by the explosion of the explosive bomb inside the wing can pass through these holes 72 and prevent the pressure in the wing between the impacted ribs 28 from increasing, and the outer plate 32 and the rib 28 etc. Can prevent local damage.
[0045]
FIG. 11 is a schematic diagram showing the horizontal tail unit 12 on which the explosive bomb 81 has landed. As shown in FIG. 11 (1), when the explosive bomb 81 lands on the outer plate 32 of the horizontal stabilizer 12, the explosive of the explosive bomb 81 explodes, and as shown in FIG. 11 (2), the blast generated by the explosion However, it spreads in the internal space of the horizontal stabilizer 12. As a result of this explosion, the pressure in the internal space rises, and when it becomes equal to or higher than a predetermined pressure, as shown in FIG. 11 (3), the scatter plate 34 scatters, releasing the internal pressure of the horizontal tail 12. In this way, as shown in FIG. 11 (4), at least the remaining portion 32a of the outer plate 32 can be prevented from being damaged, and the aircraft can continue flying safely even after the scatter plate 34 is scattered. it can.
[0046]
【The invention's effect】
According to the first aspect of the present invention, when the pressure in the wing rises for some reason and reaches a predetermined pressure or more, a part of the outer plate is scattered, so that at least most of the outer plate is damaged. In addition, since most of the skins can be prevented from flying and the shape of the wings can be maintained, the aircraft can continue flying safely after the skins scatter.
In addition, the remaining part of the outer plate is fastened to the internal structure using fasteners, so when the pressure in the wing rises and part of the outer plate scatters, the remaining part of the outer plate is damaged, And can be prevented from scattering. Therefore, it is possible to reliably prevent large damage affecting most of the outer panel and scattering of most of the outer panel.
[0047]
According to the second aspect of the present invention, since the portion where the part of the outer plate is joined to the remaining portion projects outwardly toward the outside of the wing, when stress is concentrated at the joint portion, In addition, the peeling easily progresses, and a part of the outer plate can be easily scattered.
[0048]
According to the third aspect of the present invention, the joining area can be increased by forming the joining portion in a step shape. In order to reduce the rigidity of a part of the skin in comparison with the remaining part, even if the thickness is reduced, the well should be pitted without being damaged by pneumatic force acting on the skin during normal navigation. The joining force which can be obtained can be obtained. In addition, bonding by bonding is vulnerable to an impact pressure such as a blast, and a part of the outer plate can be easily scattered.
[Brief description of the drawings]
FIG. 1 is a perspective view showing an aircraft 11 using a wing internal pressure release structure according to an embodiment of the present invention.
FIG. 2 is a perspective view showing a horizontal stabilizer 12 of the aircraft 11;
FIG. 3 is a perspective view showing an internal structure 21a of a horizontal stabilizer 21 of the horizontal stabilizer 12.
4 is an enlarged perspective view of section IV of FIG. 2 showing a structure of the horizontal stabilizer 12 between the front spar 26 and the rear spar 27. FIG.
FIG. 5 is a sectional view taken along section line S5-S5 in FIG. 4;
FIG. 6 is an enlarged sectional view of section VI in FIG. 5;
FIG. 7 is an enlarged perspective view of section VII in FIG. 4;
FIG. 8 is a sectional view taken along section line S8-S8 in FIG. 7;
FIG. 9 is an enlarged perspective view of a section IX in FIG. 4;
FIG. 10 is a perspective view showing a rib 28;
FIG. 11 is a schematic diagram showing a horizontal tail unit 12 on which a burst bullet 81 has landed.
FIG. 12 is a cross-sectional view showing a state where a burst bomb collides with an object.
FIG. 13 is a cross-sectional view showing a state when the explosive bomb 2 collides with the wing 5;
[Explanation of symbols]
12 horizontal tail 26 front spar 27 rear spar 28 rib 32 outer plate 33 stringer 34 scattering plate 35 outer peripheral portion of the scattering plate

Claims (3)

An aircraft wing having an internal structure covered with a skin,
The outer plate is partially formed separately from the rest,
A part of the outer plate has a lower bending rigidity than the remaining portion of the outer plate, and is bonded and joined to the remaining portion,
The internal pressure release structure of the wing, wherein a remaining portion of the outer plate is fastened to the internal structure using a fastener. The internal pressure release structure of a wing according to claim 1, wherein a portion where a part of the outer plate is joined to a remaining portion of the outer plate protrudes outward toward the outside of the blade. A part of the skin and the remaining part of the skin are formed by laminating a plurality of layer portions, and a part where the part of the skin and the remaining part of the skin are joined is formed in a step shape. 3. The internal pressure release structure of a wing according to claim 2, wherein:

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