JP3641437B2 - Wing outer plate mounting structure - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to an aircraft wing structure, and more particularly to an attachment structure between an outer plate and an internal structure.
[0002]
[Prior art]
The main wing outer wing at the tip of the main wing of the aircraft gains lift during flight and functions to support the aircraft in the air. The tail wing arranged behind the aircraft is composed of a horizontal tail and a vertical tail, and the horizontal tail balances the aerodynamic force acting on the aircraft around the center of gravity of the aircraft to maintain vertical stability. . The vertical tail keeps the direction of the aircraft stable and controls the sideslip of the aircraft. Therefore, the main wing outer wing and the tail wing are essential wings for the aircraft to fly safely.
[0003]
The wing of a conventional large machine is composed of a girder extending in the longitudinal direction of the wing and an internal structure such as a rib arranged perpendicular to the girder, an outer plate, and a number of stringers fixed to the outer plate from the inside of the wing. A multi-stringer structure is 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 bullet 2 collides with an object. As shown in FIG. 12 (1), when the explosive bomb 2 lands on the outer plate 1 of the object, the glaze 3 of the explosive bomb 2 explodes, and as shown in FIG. 12 (2), a blast generated by the explosion At the same time, the small pieces 4 are released from the explosive bullets and scattered into the inner space of the object.
[0005]
FIG. 13 is a cross-sectional view showing a state when the explosive bullet 2 collides with the wing 5. As shown in FIG. 13 (1), when the explosive bomb 2 lands on the outer plate 6 of the wing 5, the explosive of the explosive bomb 2 explodes, and as shown in FIG. 13 (2), along with the blast generated by the explosion Small pieces 4 are released from the explosive shell 2 and scattered into the inner space of the wing 5. The blast fills the inner space of the wing 5 and, as shown in FIG. 13 (3), gives an excessive pressure to the outer plate 6, the girders and stringers that are reinforcing bodies, and the thin-walled member. Damage the member. The blast continues to apply pressure to the member until the member is destroyed and all the blast is out of the wing. As a result, as shown in FIG. 13 (4), members including the outer plate 6 are scattered. Thus, the wing 5 is fatally damaged by the explosive shell 2.
[0006]
[Problems to be solved by the invention]
As mentioned above, if the major structural members that determine the shape of the wing, such as the skin, are damaged, the wing will not be able to maintain the airfoil and a safe flight of the aircraft cannot be guaranteed.
[0007]
When a explosive bullet lands on the wing of an aircraft and explodes, as shown in FIG. 13 (3), structural members such as the outer plate 6 are deformed by the blast, and further, through holes are formed in the structural member by the small pieces 4. . Particularly in the case of a wing having a thin outer plate such as a main wing outer wing and a tail wing of a large aircraft, the outer plate is separated from the inner structure by the blast, and the outer plate is destroyed extensively. If the skin is destroyed over a wide area, the girder, ribs, etc. will be severely damaged.
[0008]
In order to prevent the outer plate from being peeled off from the internal structures such as girders and ribs as much as possible by the blast generated in the wing, the connection between the outer plate and the internal structure is prevented from being damaged by the blast. A structure is required.
[0009]
An object of the present invention is to provide a blade outer plate mounting structure capable of preventing the outer plate from being peeled off from the internal structure by a blast caused by a explosive bomb.
[0010]
[Means for Solving the Problems]
The present invention is an aircraft wing skin attachment structure in which an internal structure is covered by a skin,
A fastener member having a shaft portion and a head portion formed at one end of the shaft portion and having an outer diameter sufficiently larger than the outer diameter of the shaft portion;
The internal structure has a connecting portion along the outer plate, and a convex portion projecting inward from the central portion of the connecting portion, and has a T-shaped rib shear tie in cross section.
The head of the fastener member is fitted and locked in the recess of the outer plate, the shaft portion of the fastener member is locked to the connecting portion of the rib shear tie, and the outer plate and the rib shear tie are fastened by the fastener member,
A stringer is joined to the outer plate, and a portion that contacts the rib shear tie of the stringer is provided with a fastening portion that extends in parallel to the convex portion of the rib shear tie,
The fastener member's head is fitted and locked in the recess of the fastening portion of the reinforcing body, and the shaft portion of the fastener member is locked to the convex portion of the rib shear tie, and the stringer and rib shear tie are fastened by the fastener member. And
The wing outer plate mounting structure is characterized in that the fastener member for fastening the outer plate and the rib shear tie, and the fastener member for fastening the stringer and the rib shear tie are arranged and used so as to extend in directions in which the axes intersect each other. It is.
[0011]
According to the present invention, the outer plate is fastened to the rib shear tie constituting the internal structure using the fastener member. The fastener member has a head fitted into a recess in the outer plate, and does not affect aerodynamic characteristics of the wing such as lift. Further, the head of the fastener member has a sufficiently large outer diameter with respect to the shaft portion, and can receive the pulling force of the fastener member with respect to the outer plate in a wide area of the outer plate. The pull-out strength can be increased. That it is sufficiently large is about twice or more. Therefore, even if a force to peel the outer plate from the inner structure having rib shear ties is applied due to a pressure difference between the outer and inner blades, for example, due to a pressure difference between the inside and outside of the blade, the inner structure of the outer plate is resisted against this force. The connected state to the body can be reliably maintained.
A stringer is joined to the outer plate, and the stringer and the rib shear tie are fastened by a fastener member. In this way, the force for separating the outer plate from the internal structure is shared not only by the fastener member that directly fastens the outer plate and the internal structure, but also by the fastener member that fastens the stringer and the internal structure via the stringer, The pull-out force acting between the fastener member that directly fastens the outer plate and the inner structure and the outer plate can be reduced. Thereby, the pull-out strength of the fastener member with respect to the outer plate can be further increased.
Also, the fastener member that fastens the stringer and the rib shear tie has a sufficiently large outer diameter with respect to the shaft portion, and can receive the pulling force of the fastener member against the stringer in a wide area of the reinforcing body. The pull-out strength of the fastener member with respect to the stringer can be increased. As a result, the mounting strength of the outer plate can be further increased.
In addition, the fastener member that fastens the outer plate and the rib shear tie and the fastener member that fastens the stringer and the rib shear tie are arranged and used so that their axes extend in directions intersecting each other. Therefore, the force acting in the axial direction of the fastener that fastens the outer plate and the rib shear tie is suitably received by the fastener that fastens the stringer and the rib shear tie, and the force acting on the fastener that fastens the outer plate and the rib shear tie is reduced. Can do.
[0012]
Further, the present invention is characterized in that the connecting region portion connected to the rib shear tie of the outer plate has a thickness dimension larger than the remaining portion of the outer plate.
[0013]
According to the present invention, the connecting region portion connected to the rib shear tie of the outer plate has a thickness dimension larger than the remaining portion of the outer plate. Therefore, the strength of the connecting region portion is increased, and the fastener member is pulled out from the outer plate. The fastening between the outer plate and the internal structure having the rib shear tie is maintained against strong force. Moreover, instead of increasing the thickness of the entire outer plate, the thickness is increased only in the connection region where partial high strength is required, so the entire blade is made as light as possible and the mounting strength of the outer plate is increased. be able to.
[0014]
Further, according to the present invention, between the head portion of the fastener member and the outer plate, a receiving portion into which the head portion is fitted, and projecting radially outward from the receiving portion to be locked to the outer surface of the outer plate. A washer member having a locking portion is interposed.
[0015]
According to the present invention, a washer member is interposed between the fastener head and the outer plate, and the washer distributes the pulling force of the fastener member to the outer plate to a wider area of the outer plate by the washer. Can do. Therefore, the pull-out strength of the fastener member with respect to the outer plate can be further increased. In addition, the washer member has a receiving portion and a locking portion, and the head portion of the fastener member is held in a state where it is fitted in the recess of the outer plate, which affects aerodynamic characteristics. There is no.
[0019]
The present invention is characterized in that the outer plate and the rib shear tie are bonded.
According to the present invention, since the outer plate and the rib shear tie are bonded, the force for peeling the outer plate from the internal structure is shared not only by the fastener member that directly fastens the outer plate and the rib shear tie, but also by the bonding portion. The pull-out force acting between the fastener member that directly fastens the plate and the rib shear tie and the outer plate can be reduced. Thereby, the pull-out strength of the fastener member with respect to the outer plate can be further increased.
[0020]
DETAILED DESCRIPTION OF THE INVENTION
FIG. 1 is a perspective view showing an aircraft 11 using a wing skin attachment structure according to an embodiment of the present invention. The wing outer plate mounting structure of the present embodiment is used for the tail wing 15 and the main wing outer wing 13. The main wing outer wing 13 is a front end portion of the main wing 14 of the aircraft 11 that functions to obtain lift during flight and support the aircraft in the air. The tail 15 arranged behind the aircraft 11 includes a horizontal tail 12 and a vertical tail 16, and the horizontal tail 12 balances the aerodynamic force acting on the aircraft around the center of gravity of the aircraft to stabilize the pitch direction. Work to keep. The vertical tail 16 serves to maintain the stability of the aircraft in the yaw direction and to control the skidding of the aircraft.
[0021]
FIG. 2 is a perspective view showing the horizontal tail 12 of the aircraft 11. The horizontal tail 12 includes a horizontal stabilizer 21 fixed to the airframe and a movable blade 22 that can be displaced. The horizontal stabilizer 21 includes a front edge portion 23, a rear edge portion 24, and an inter-blade structure portion 25 disposed between the front edge portion 23 and the rear edge portion 24. The moving 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 tail 12. The internal structure 21a extends in the longitudinal direction of the horizontal girder (hereinafter sometimes referred to as “wing”) 12 and is disposed in the longitudinal direction of the wing 12 and on the trailing edge side of the front girder 26 in the chord direction. The rear spar 27 to be arranged extends in the chord direction, is arranged at a predetermined interval in the longitudinal direction of the wing 12, and is connected to the front spar 26 and the rear spar 27. A leading edge reinforcing member 29a that extends and is disposed on the leading edge side of the leading string 26 in the chord direction; a trailing edge reinforcing member 29b that extends in the longitudinal direction of the blade 12 and is disposed on the trailing edge side of the trailing string 27; A plurality of first connecting members 30a that connect the reinforcing member 29a and the front beam 26 and a plurality of second connecting members 30b that connect the rear edge reinforcing member 29b and the rear beam 27 are configured. 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 an internal structural member. The outer tail body 31 is connected so as to cover these internal structural members from the outside, and the horizontal tail 12 is configured.
[0023]
FIG. 4 is an enlarged perspective view showing the structure of the horizontal tail 12 between the front beam 26 and the rear beam 27 by enlarging the section IV of FIG. 2. The outer skin 31 extends to the outer plate 32 and the outer plate 32 between the front spar 26 and the rear spar 27 in the longitudinal direction of the wing 12 and is aligned from the inside of the wing 12 along the chord direction of the wing 12. A plurality of stringers 33 which are reinforcing bodies to be formed are included. The outer plate 32 and the stringer 33 are bonded with a cure. Cocure bonding is a synthesis in which the formed outer plate 32 and the stringer 33 are not cured, the stringer 33 is brought into close contact with the outer plate 32, and the outer plate 32 and the stringer 33 are individually cured and simultaneously impregnated into the stringer 33. This is a bonding method in which a resin is used as an adhesive.
[0024]
The stringer 33 is made of a carbon fiber reinforced resin material (abbreviation: CFRP), and the outer shape in the cross section perpendicular to the axis is uniformly substantially trapezoidal. When viewed in the cross section perpendicular to the axis, the stringer 33 is long. 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 such as carbon fiber is impregnated with a synthetic resin such as an epoxy resin. As a result, when the explosive blast explodes inside the wing, the blast due to the explosion flows smoothly around the outer periphery of the stringer 33. Therefore, 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 at right angles to the axis. However, the stringer 33 may have a polygonal shape such as a triangle and a semicircular shape such that a blast caused by an explosion flows smoothly around the outer periphery of the stringer 33. .
[0026]
The inter-spar structure 25 includes a front beam 26, a rear beam 27, and a plurality of ribs 28, and further includes an outer plate 32 and a stringer 33 between the front beam 26 and the rear beam 27. A portion 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 sometimes referred to as “scattering plate”). 34 is a separate body from the remaining portion 32 a of the outer plate 32. The scattering plate 34 is not fixed to the front beam 26, the rear beam 27 and the rib 28. The scattering plate 34 and the stringer 33 are cocure bonded. The blade outer plate mounting structure of the present invention is used for the rib 28 and outer plate 32 mounting structure.
[0027]
FIG. 5 is a cross-sectional view taken along section line S5-S5 in FIG. The scattering plate 34 protrudes outward as the outer peripheral portion 35 moves outward from the wing. The scattering plate 34 and the remaining portion 32a of the outer plate 32 are cocure bonded.
[0028]
6 is an enlarged cross-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 fibers are impregnated with an epoxy resin. For example, the outermost layer portion 37 is made of a material of ± 45 degrees in which the fiber direction, which is the direction in which the fibers extend, is ± 45 degrees with respect to the longitudinal direction of the blade 12. 12 is formed by laminating a plurality of zero degree materials parallel to the longitudinal direction of 12 and 90 degree materials and ± 45 degree materials whose fiber directions are perpendicular to the longitudinal direction of the blades 12.
[0029]
The scattering plate 34 is formed by laminating a plurality of layer portions made of a composite material in which an epoxy resin is impregnated into carbon fibers. The plurality of layers are mainly made of a ± 45 degree material in which the fiber direction forms 45 degrees with respect to the longitudinal direction of the blade. The composite material including carbon fiber is light and high in strength, and does not require a fastener and an adhesive for forming the scattering plate 34. The thickness T1 of the scattering plate 34 is formed to be thinner than the thickness T2 of the remaining portion 32a.
[0030]
The layer portion of the outer peripheral portion 41 of the scattering plate 34 is laminated so as to project outward in a stepped manner from the inside of the wing 12 toward the outside. At least the portion 43 of the remaining portion 32a of the outer plate 32 to be bonded to the scattering plate 34 is laminated so that the layer portion protrudes outward in a stepped manner from the outside of the wing toward the inside. Each layer portion of the scattering plate 34 is bonded to the layer portion of the remaining portion 32a that is lowered by one step toward the inside of the wing with respect to the layer portion of the scattering plate 34.
[0031]
FIG. 7 is an enlarged perspective view of section VII in FIG. 8 is a cross-sectional view taken along section line S8-S8 in FIG. The rib 28 includes a rib shear tie 51 and a web 71 (see FIG. 10). The rib shear tie 51 protrudes inward of the wing 12 from a flat plate-like connecting portion 51a extending in the chord direction C1 of the wing 12 and a central portion of one surface facing the inner side of the wing 12 of the connecting portion 51a. The outer shape of the cross section perpendicular to the axis having a flat plate-like convex portion 51b extending in the longitudinal direction C1 of the connecting portion 51a is a T-shaped member. The rib shear tie 51 and the outer plate 32 are fastened by a fastener 52. The convex part 51b of the rib shear tie 51 and the rib 28 are connected. The web 71 is plate-shaped and joined to the convex portion 51 b of the rib shear tie 51. The outer plate 32 is connected to the rib 28 by being connected to the rib shear tie 51.
[0032]
The fastener 52 includes a cylindrical shaft portion 52a and a substantially truncated cone-shaped head portion 52b which is provided on one end side of the shaft portion 52a and whose diameter increases as the distance from the shaft portion 52a increases. The head 52b of the fastener 52 is formed such that the outer diameter D1 thereof is about twice or more the outer diameter D2 of the shaft portion 52a.
[0033]
The connection region portion 32b to which the rib shear tie 51 of the outer plate 32 is connected protrudes inward of the wing 12, and the thickness T3 thereof is thicker than the remaining portion 32a of the outer plate 32, and the axis of the head 52b of the fastener 52 It is formed to be twice or more the directional thickness T4. A plurality of insertion holes 36 penetrating the outer plate 32 in the thickness direction are formed in the connection region portion 32b of the outer plate 32 in a row at a predetermined interval in the chord direction C1. Further, on the outer side of the blade of the insertion hole 36 of the outer plate 32, a substantially truncated cone-shaped recess 54 is formed which increases in diameter toward the outer side of the blade 12. An insertion hole 53 corresponding to the insertion hole 36 of the connection region portion 32 b of the outer plate 32 is formed in the connection portion 51 a 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.
[0034]
The shaft portion 52a of the fastener 52 is inserted into the insertion hole 36 of the outer plate 32 and the insertion hole 53 of the rib shear tie 51, and the head portion 52b is a dimple washer (referred to as “washer”) used to prevent corrosion due to electricity. Is fitted) into the recess 54 of the connecting region portion 32b.
[0035]
Specifically, the washer 55 has a truncated cone-shaped receiving portion 55a and a locking portion 55b protruding outward in the radial direction from the receiving portion, and the receiving portion 55a of the washer 55 is a recess in the coupling region portion 32b. 54, the head 52 b of the fastener 52 is fitted into the receiving portion 55 a of the washer 55. The locking portion 55 b of the washer 55 is locked to the outer surface of the wing of the outer plate 32.
[0036]
At this time, the other end portion of the shaft portion 52 a of the fastener 52 protrudes from the connecting portion 51 a of the rib shear tie 51 toward the inside of the blade 12. The outer plate 32 and the rib shear tie 51 are fastened by attaching a regulating member 56 that regulates the axial displacement of the fastener 52 to the projecting other end. Further, the protruding other end portion may be deformed to be larger than the inner diameter of the insertion hole 53 of the rib shear tie 51 to restrict the displacement of the fastener 52 in the axial direction. In a state where the outer plate 32 and the rib shear tie 51 are fastened, the end surface of the head portion 52b of the fastener 52 is flush with the engaging portion 55b of the washer 55, and further, the outer surface of the wing 12 of the outer plate 32 is It is almost flush. Further, the outer plate 32 and the rib shear tie 51 are bonded by an adhesive 57.
[0037]
According to the blade outer plate mounting structure of the present embodiment, the outer plate 32 is fastened to the rib shear tie 51 using the fastener 52. The fastener 52 has a head 52b fitted in the recess 54 of the outer plate 32, and does not affect aerodynamic characteristics of the wing such as lift. Further, the head portion 52b of the fastener 52 has a sufficiently large outer diameter with respect to the shaft portion 52a, so that the pulling force of the fastener 52 with respect to the outer plate 32 can be received in a wide area of the outer plate 32, The pull-out strength of the fastener 52 with respect to the plate 32 can be increased. Therefore, even if a force for separating the outer plate 32 from the rib shear tie 51 is exerted by increasing the mounting strength of the outer plate 32, for example, due to a pressure difference between the inside and outside of the blade, the rib shear tie 51 of the outer plate 32 is resisted against this force. It is possible to reliably maintain the connected state.
[0038]
Further, according to the wing mounting structure of the present embodiment, the connecting region portion 32b connected to the rib shear tie 51 of the outer plate 32 has a larger thickness dimension than the remaining portion 32a of the outer plate 32. The strength of 32b is increased, and the fastening of the outer plate 32 and the rib shear tie 51 is maintained against the pulling force of the fastener 52 on the outer plate 32 with certainty. In addition, since the thickness dimension is increased only in the connecting region portion 32b that requires a partially high strength, rather than increasing the thickness dimension of the entire outer plate 32, the entire blade is made as light as possible, and the mounting strength of the outer plate 32 is increased. Can be high.
[0039]
Further, according to the outer plate mounting structure of the wing of the present embodiment, the washer 55 is interposed between the head 52 b of the fastener 52 and the outer plate 32, and the fastener 52 is pulled out from the outer plate 32 by the washer 55. The force can be distributed to a wider area of the outer plate 32 by the washer 55. Therefore, the pull-out strength of the fastener 52 with respect to the outer plate 32 can be further increased. Moreover, the washer 55 has a receiving portion 55a and a locking portion 55b, and the head 52b of the fastener 52 is held in a state where it is fitted in the recess 54 of the outer plate 32, and the aerodynamics of the wing is maintained. Does not affect the characteristics.
[0040]
Further, according to the outer plate mounting structure of the wing of the present embodiment, the outer plate 32 and the rib shear tie 51 are bonded, and therefore the force for peeling the outer plate 32 from the rib shear tie 51 is directly applied to the outer plate 32 and the rib shear tie 51. Not only the fasteners 52 to be fastened but also the adhesive 57 can be used to reduce the pulling force that acts between the fasteners 52 that fasten the outer plate 32 and the rib shear tie 51 directly and the outer plate 32. As a result, the pull-out strength of the fastener 52 with respect to the outer plate 32 can be further increased.
[0041]
FIG. 9 is an enlarged perspective view of section IX of FIG. A flat plate-like fastening portion 61 extending in parallel with the convex portion 51 b is provided at an end portion of the stringer 33 that contacts the convex portion 51 b of the rib shear tie 51. The fastening portion 61 is provided with an insertion hole and a recess (not shown) penetrating in the thickness direction of the fastening portion 61, similar to the insertion hole 53 provided in the outer plate 32 described above, and the convex portion of the rib shear tie 51. 51 b is provided with an insertion hole corresponding to the insertion hole of the fastening portion 61 and penetrating in the thickness direction of the convex portion 51 b. The rib shear tie 51 and the stringer 33 are fastened using the fastener 62 similar to the fastener 52 in the same manner as the fastening of the outer plate 32 and the rib shear tie 51 described above.
[0042]
At this time, the axis of the fastener 52 that fastens the outer plate 32 and the rib shear tie 51 and the axis of the fastener 62 that fastens the stringer 33 and the rib shear tie 51 are in an intersecting positional relationship. The force acting in the direction of peeling, in other words, the force acting in the axial direction of the fastener 52 that fastens the outer plate 32 and the rib shear tie 51 also acts on the fastener 62 that fastens the stringer 33 and the rib shear tie 51. Therefore, the force acting on the fastener 52 can be reduced.
[0043]
According to the blade outer plate mounting structure of the present embodiment, the stringer 33 is joined to the outer plate 32, and the stringer 33 and the rib shear tie 51 are fastened by the fastener 62. Thus, not only the fastener 52 that directly fastens the outer plate 32 and the rib shear tie 51 but also the fastener 62 that fastens the stringer 33 and the rib shear tie 51 via the stringer 33, the force for peeling the outer plate 32 from the rib shear tie 51. The pulling-out force acting between the fastener 52 and the outer plate 32 that shares and directly fastens the outer plate 32 and the rib shear tie 51 can be reduced. As a result, the pull-out strength of the fastener 52 with respect to the outer plate 32 can be further increased. Further, the fastener 62 that fastens the stringer 33 and the rib shear tie 51 also has a head having a sufficiently large outer diameter with respect to the shaft portion, and also uses a washer 55. Therefore, the pulling force of the fastener 62 on the stringer 33 is increased. The stringer 33 can be received in a wide area, and the pull-out strength of the fastener 62 with respect to the stringer 33 can be increased. As a result, the mounting strength of the outer plate 32 can be further increased.
[0044]
The stringer 33 is bonded to the outer plate 32, and the end portion of the stringer 33 having the fastening portion 61 is also bonded to the connecting portion 51 a of the rib shear tie 51 with the outer plate 32. The acting force can be reduced.
[0045]
FIG. 10 is a perspective view showing the rib 28. 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 can prevent the pressure in the wing between the bombed ribs 28 from rising, such as the outer plate 32 and the rib 28. Can prevent local damage.
[0046]
FIG. 11 is a schematic diagram showing the horizontal tail 12 on which the explosive bullet 81 has landed. As shown in FIG. 11 (1), when the explosive bullet 81 lands on the outer plate 32 of the horizontal tail 12, the glaze of the explosive bullet 81 explodes, and as shown in FIG. 11 (2), a blast generated by the explosion However, it extends into the internal space of the horizontal tail 12. When the pressure in the internal space rises due to this explosion and becomes equal to or higher than a predetermined pressure, as shown in FIG. 11 (3), the scattering plate 34 is scattered, and the portion of the outer plate 32 excluding the scattering plate 34 is removed. The internal pressure of the horizontal tail 12 is released in a state where the fastening to the internal structure 21 such as the rib 28 is held by the fasteners 52 and 62. 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 11 can continue to fly safely after the scattering plate 34 is scattered. Can do.
[0047]
【The invention's effect】
According to the first aspect of the present invention, the outer plate is fastened to the rib shear tie constituting the internal structure using the fastener member. The fastener member has a head fitted into a recess in the outer plate, and does not affect aerodynamic characteristics of the wing such as lift. Further, the head of the fastener member has a sufficiently large outer diameter with respect to the shaft portion, and can receive the pulling force of the fastener member with respect to the outer plate in a wide area of the outer plate. The pull-out strength can be increased. That it is sufficiently large is about twice or more. Therefore, even if a force to peel the outer plate from the inner structure having rib shear ties is applied due to a pressure difference between the outer and inner blades, for example, due to a pressure difference between the inside and outside of the blade, the inner structure of the outer plate is resisted against this force. The connected state to the body can be reliably maintained.
A stringer is joined to the outer plate, and the stringer and the rib shear tie are fastened by a fastener member. In this way, the force for separating the outer plate from the internal structure is shared not only by the fastener member that directly fastens the outer plate and the internal structure, but also by the fastener member that fastens the stringer and the internal structure via the stringer, The pull-out force acting between the fastener member that directly fastens the outer plate and the inner structure and the outer plate can be reduced. Thereby, the pull-out strength of the fastener member with respect to the outer plate can be further increased.
Also, the fastener member that fastens the stringer and the rib shear tie has a sufficiently large outer diameter with respect to the shaft portion, and can receive the pulling force of the fastener member against the stringer in a wide area of the reinforcing body. The pull-out strength of the fastener member with respect to the stringer can be increased. As a result, the mounting strength of the outer plate can be further increased.
In addition, the fastener member that fastens the outer plate and the rib shear tie and the fastener member that fastens the stringer and the rib shear tie are arranged and used so that their axes extend in directions intersecting each other. Therefore, the force acting in the axial direction of the fastener that fastens the outer plate and the rib shear tie is suitably received by the fastener that fastens the stringer and the rib shear tie, and the force acting on the fastener that fastens the outer plate and the rib shear tie is reduced. Can do.
[0048]
According to the second aspect of the present invention, the connecting region portion connected to the rib shear tie of the outer plate has a thickness dimension larger than that of the remaining portion of the outer plate. The fastening of the outer plate and the internal structure having the rib sheer tie is maintained against the pulling force of the fastener member against the above. Moreover, instead of increasing the thickness of the entire outer plate, the thickness is increased only in the connection region where partial high strength is required, so the entire blade is made as light as possible and the mounting strength of the outer plate is increased. be able to.
[0049]
According to the third aspect of the present invention, the washer member is interposed between the fastener head and the outer plate, and the washer pulls out the fastener member with respect to the outer plate, and the washer further widens the outer plate. Can be dispersed in the region. Therefore, the pull-out strength of the fastener member with respect to the outer plate can be further increased. In addition, the washer member has a receiving portion and a locking portion, and the head portion of the fastener member is held in a state where it is fitted in the recess of the outer plate, which affects aerodynamic characteristics. There is no.
[0052]
According to the fourth aspect of the present invention, since the outer plate and the rib shear tie are bonded to each other, the force for peeling the outer plate from the internal structure is not limited to the fastener member that directly fastens the outer plate and the rib shear tie. Accordingly, the pulling force acting between the fastener member and the outer plate that directly shares the outer plate and the rib shear tie can be reduced. Thereby, the pull-out strength of the fastener member with respect to the outer plate can be further increased.
[Brief description of the drawings]
FIG. 1 is a perspective view showing an aircraft 11 using a wing skin attachment structure according to an embodiment of the present invention.
2 is a perspective view showing a horizontal tail 12 of an aircraft 11. FIG.
3 is a perspective view showing an internal structure 21a of the horizontal stabilizer 21 of the horizontal tail 12. FIG.
FIG. 4 is a perspective view showing the structure of the horizontal tail 12 between the front beam 26 and the rear beam 27 by enlarging the section IV of FIG. 2;
5 is a cross-sectional view taken along section line S5-S5 in FIG.
6 is an enlarged cross-sectional view of section VI of FIG.
7 is an enlarged perspective view of section VII in FIG. 4. FIG.
8 is a cross-sectional view taken along section line S8-S8 in FIG.
9 is an enlarged perspective view of section IX in FIG. 4. FIG.
10 is a perspective view showing a rib 28. FIG.
FIG. 11 is a schematic diagram showing the horizontal tail 12 on which the explosive 81 has landed.
FIG. 12 is a cross-sectional view showing a state when the explosive bullet 2 collides with an object.
13 is a cross-sectional view showing a state when the explosive bullet 2 collides with the wing 5. FIG.
[Explanation of symbols]
12 Horizontal tail
26 Leader
27 Last digit
28 Ribs
32 Outer plate
32b Connection area
33 Stringer
34 Scatter plate
51 Livsia Thai
52,62 Fastener
52a Shaft
52b head
54 recess
55 Dimple Washer
57 Adhesive
61 Fastening part

Claims (4)

An aircraft wing skin mounting structure in which the internal structure is covered by the skin,
A fastener member having a shaft portion and a head portion formed at one end of the shaft portion and having an outer diameter sufficiently larger than the outer diameter of the shaft portion;
The internal structure has a connecting portion along the outer plate, and a convex portion projecting inward from the central portion of the connecting portion, and has a T-shaped rib shear tie in cross section.
The head of the fastener member is fitted and locked in the recess of the outer plate, the shaft portion of the fastener member is locked to the connecting portion of the rib shear tie, and the outer plate and the rib shear tie are fastened by the fastener member,
A stringer is joined to the outer plate, and a portion that contacts the rib shear tie of the stringer is provided with a fastening portion that extends in parallel to the convex portion of the rib shear tie,
The fastener member's head is fitted and locked in the recess of the fastening portion of the reinforcing body, and the shaft portion of the fastener member is locked to the convex portion of the rib shear tie, and the stringer and rib shear tie are fastened by the fastener member. And
The wing outer plate mounting structure is characterized in that the fastener member for fastening the outer plate and the rib shear tie, and the fastener member for fastening the stringer and the rib shear tie are arranged and used so as to extend in directions in which the axes intersect each other. .   2. The blade outer plate mounting structure according to claim 1, wherein the connecting region portion connected to the rib shear tie of the outer plate has a thickness dimension larger than that of the remaining portion of the outer plate.   Between the head part of the fastener member and the outer plate, a receiving part into which the head part is fitted, and a locking part that protrudes radially outward from the receiving part and is locked to the outer surface of the outer plate. The blade outer plate mounting structure according to claim 1 or 2, wherein a washer member is interposed.   The outer plate attachment structure of the wing according to any one of claims 1 to 3, wherein the outer plate and the rib shear tie are bonded.

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