JP2002293295A - Wing reinforcing body - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a wing reinforcing body lightweight with little influence of blast by an explosive and reducing damage caused by fragments of the explosive. SOLUTION: A stringer 33 comprises a stringer body 33a whose outline in a cross section perpendicular to an axis is almost trapezoidal, and a guard plate 43 bonded through a film-like adhesive 44 from the outside of the stringer body 33a. The stringer body 33a comprises a core 41 formed of a foam synthetic resin material, and an outer layer 42 formed of CFRP covering the core 41 over the whole circumferential direction. The stringer body 33a is thus formed in thick-walled closed cross section structure, so that strength to torsion can be made high in comparison with a stringer of conventional open cross section structure such as J-shape in which the minimum circumscribed circle radius in the cross section is the same. Moreover, the guard plate 43 can reduce the damage of the stringer body 33a caused by the fragments of the explosive.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

The present invention relates to a wing reinforcement for an aircraft.

[0002]

2. Description of the Related Art A wing outer wing at the tip of a main wing of an aircraft obtains lift during flight and serves to support the aircraft in the air. The tail mounted on the rear of the aircraft is composed of a horizontal tail and a vertical tail. . 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] The tail fin of a conventional large-sized aircraft is composed of a girder extending in the longitudinal direction of the wing, a rib arranged perpendicularly to the spar, a skin, and a number of stringers fixed to the skin from the inside of the wing. Multi-stringer structures are often used. In the multi-stringer structure, a bending moment and a shearing force act on the skin and the stringer, similarly to the girder. A torsional moment acts on the outer plate and the girder.

FIG. 11 is a cross-sectional view showing a state where the explosive bomb 2 collides with an object. As shown in FIG. 11A, 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. 11B, the blast generated by the explosion 4 pieces from explosive bombs
Is released and scattered in the inner space of the object.

FIG. 12 is a cross-sectional view showing a state when the explosive bomb 2 collides with the wing 5. As shown in FIG. 12A, when the explosive bomb 2 lands on the outer plate 6 of the wing 5, the explosive bomb 2
The explosive explodes, and as shown in FIG. 12 (2), the small pieces 4 are released from the explosive bomb 2 together with the blast generated by the explosion, and scattered into the inner space of the wing 5. The blast fills the inner space of the wing 4 and scatters the outer plate 6 and the thin member as shown in FIG. The small pieces 4 damage these members, such as forming through holes in structural members such as stringers, girders and ribs. Thus, the wings 5
Suffers fatal damage.

[0006]

As described above, when through holes are formed in the main structural members of the wing, such as stringers, girders, and ribs, the strength of the entire wing is reduced. In multi-stringer wings, the skin, stringer and spar share the primary load acting on the wing, so that damage to these structural members does not ensure safe flight of the aircraft.

When the explosive bomb lands on the wing of the aircraft and explodes, as shown in FIG. 12 (3), the structural member such as the outer plate 6 is deformed by the blast, and the small piece 4 forms a through hole in the structural member. It is formed. In particular, 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 scattered by the blast. If the skin splatters,
The remaining stringers and other structural members must share the load acting on the wing. In addition, such a reduction in the strength and rigidity of the wing may cause flutter, making it extremely difficult to continue flight.

Therefore, there is a need for a wing reinforcing material that minimizes a decrease in strength of the entire wing even if the outer plate is scattered by the blast. For this purpose, damage from explosive bombs can be dealt with by adding additional reinforcements, attaching bulletproof armor to the wings, and using a metal material such as titanium alloy for the structural member made of composite material. However, the weight of the wings is greatly increased and is not suitable as the tail wing and the outer wing of a large aircraft.

SUMMARY OF THE INVENTION It is an object of the present invention to provide a wing reinforcing member which is light in weight, less affected by a blast due to an explosive bomb, and can reduce damage due to a small piece of the explosive bomb.

[0010]

According to the present invention, there is provided a reinforcing member fixed to an outer plate of an aircraft wing from an inner side of the wing, wherein a core made of a foamed synthetic resin material has a fiber made of a synthetic resin. A reinforced body of a wing, comprising a reinforced body that is covered by an outer layer made of a composite material impregnated with the rubber over the entire circumference and fixed to an outer plate.

According to the present invention, the reinforcing body has a core made of a foamed synthetic resin material covered with an outer layer made of a composite material obtained by impregnating a synthetic resin into a fiber material, over the entire circumferential direction. As described above, since the outer layer has a cylindrical shape and is closed in a cross section perpendicular to the axis, and the reinforcing body is formed in a thick-walled closed cross-sectional structure, the conventional J-shape having the same minimum circumscribed circle radius in the cross section is used. The strength against torsion can be increased as compared with the reinforcing body having the open cross-sectional structure. Therefore, for example, even if the outer plate is damaged by some factor and a load due to wind pressure acts on the reinforcing member, the deformation of the reinforcing member can be prevented. Further, since the foamed synthetic resin material and the composite material can be easily molded by a mold, a wing reinforcement having a complicated shape can be easily molded.

Further, the present invention is characterized in that a protective layer made of a material that covers the reinforcing body from the outside and has a product of density and elastic modulus larger than the composite material is provided.

According to the present invention, the reinforcing member is provided with a protective layer which covers the reinforcing member body from the outside and is made of a material having a value of a product of density and elastic modulus larger than that of the composite material covering the core. Therefore, even if a small piece collides with the reinforcing member due to some factor, at least damage to the reinforcing member main body can be prevented. This can prevent the strength of the entire wing from being reduced due to damage to the reinforcement.

Further, the present invention is characterized in that the protective layer is made of a plate material and is adhered to a reinforcing body.

According to the present invention, the protective layer made of a plate material is
Since it is adhered to the reinforcing body, a uniform protection strength can be obtained as compared with the case where it is joined by a fastener that penetrates a protective layer such as a rivet. Further, the protection layer can be easily attached to the reinforcing body.

[0016]

FIG. 1 is a perspective view showing an aircraft 11 using a wing reinforcement according to an embodiment of the present invention. The wing reinforcing member of the present embodiment includes the tail wing 15 and the main wing outer wing 1.
3 is used. The wing outer wing 13 obtains lift during the flight, and serves to support the aircraft in the air.
4. The tail unit 15 disposed behind the aircraft 11 includes a horizontal tail unit 12 and a vertical tail unit 16. The horizontal tail unit 12 balances the aerodynamic force acting on the fuselage around the center of gravity of the fuselage, thereby stabilizing the pitch direction. Work to keep The vertical tail 16 serves to maintain the stability of the fuselage in the yaw direction and to control the skidding of the fuselage.

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 disposed between the leading edge 23 and the trailing edge 24. The bucket 22 has a trailing edge 24
It is directly connected to the motor so that it can be angularly displaced.

FIG. 3 is a perspective view showing the internal structure 21a of the horizontal stabilizer 21 of the horizontal stabilizer 12. As shown in FIG. Internal structure 21
The front spar 26 extends in the longitudinal direction of the horizontal tail unit (hereinafter sometimes referred to as “wing”) 12, extends in the longitudinal direction of the wing 12, and is disposed on the chord-wise trailing edge side of the front spar 26. The rear spar 27 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; 26, a leading edge reinforcing member 29a disposed on the chord direction leading edge side, a trailing edge reinforcing member 29b extending in the longitudinal direction of the wing and disposed on the chord direction trailing edge side of the rear spar 27, and a leading edge reinforcing member 29a. A plurality of first connecting members 30a for connecting to the spar 26;
9b and a plurality of second connecting members 30b connecting the rear spar 27
It is comprised including. Front girder 26, rear girder 27, rib 28,
The leading edge reinforcing member 29a, the trailing 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.

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 is fixed 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, side by side in the chord direction of the wing 12, and fixed 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 inter-spar structure 25 includes a front girder 26, a rear girder 2
7 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.

FIG. 5 is a sectional view showing a stringer 33 according to an embodiment of the present invention. The stringer 33 includes a stringer main body 33a and a stringer main body 33a.
Protective plate 43 adhered via film adhesive 44
It is composed of

The stringer body 33a has a trapezoidal outer shape in a cross section perpendicular to the axis, and has a core 41 made of a foamed synthetic resin material, for example, polyetherimide or polyethacrylimide.
And an outer layer 42 made of a carbon fiber reinforced resin material (abbreviation: CFRP) that covers the core 41 over the entire circumference. 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.

The stringer main body 33a has a substantially trapezoidal outer shape in a cross section perpendicular to the axis, and when viewed in a cross section perpendicular to the axis, the side 31b, which is the longer side of the two parallel sides of the trapezoid, Cocuure (cocu) is applied to the outer plate 32 from the inner side of the wing.
re) Bonded by bonding.

The cocure bonding is performed by curing the stringer 3 on the outer plate 32 without curing the formed outer plate 32 and the stringer 33.
This is a bonding method in which the outer plate 32 and the stringer 33 are individually cured by bringing the stringer 3 into close contact with each other, and at the same time, a synthetic resin impregnated in the stringer 33 is bonded as an adhesive. In cocure bonding, a curing step is performed twice, such as secondary bonding, which is a bonding method in which a separately cured outer plate and a stringer are bonded using an adhesive, and further the outer plate and the stringer are cured. It is not necessary to perform the above, and the outer plate 32 and the stringer 33 can be bonded in one curing step.

FIG. 6A is a sectional view showing the stringer body 33a, and FIG. 6B is a sectional view showing the stringer body 33a.
FIG. The outer layer 42 has a substantially trapezoidal cylindrical first outer layer 42a that covers the core 41 almost uniformly over the entire circumferential direction, and a cross section perpendicular to the axis of the first outer layer 42a.
The cross section perpendicular to the axis is substantially U, covering almost three sides except for the side forming the shorter side of the two parallel sides of the trapezoid.
When viewed in a cross section perpendicular to the axis of the second outer layer 42b and the first outer layer 42a, the side surface forming the shorter side of the two parallel sides of the trapezoid, and the axis perpendicular to the second outer layer 42b. When viewed in a cross section, a laminated structure having a third outer layer 42c having a substantially U-shaped cross section perpendicular to the axis, which covers almost uniformly the side surfaces forming two oblique sides except for two parallel sides of the trapezoid. ing.

When viewed in a cross section perpendicular to the axis of the second outer layer 42b, the projecting portion 51 is formed so as to be parallel to the longer outer surface of the two parallel sides of the trapezoid. Outer layer 42
c are provided at the circumferential end portions so as to extend in directions away from each other. By providing such an overhang portion 51, the bonding area between the stringer 33 and the outer plate 32 is increased, and the adhesive force between the stringer 33 and the outer plate 32 can be increased. Further, since the foamed synthetic resin material and CFRP are easily formed by a mold and do not require a jig, the stringer body 33a having a complicated shape can be easily and inexpensively manufactured.

The first outer layer 42a and the second outer layer 42b are mainly made of a 0 ° unidirectional material, for example, having an elastic modulus of 240 to 30.
Using a plurality of composite materials obtained by impregnating carbon fibers of about 0 GPa with an epoxy resin, the fiber direction in which the fibers of the first outer layer 42a extend is made parallel to the axial direction of the stringer body 33a. As a part of the second outer layer 42b and the third outer layer 42c as the outermost layer, a ± 45 ° woven material, for example, a composite material obtained by impregnating carbon fiber having an elastic modulus of about 240 to 300 GPa with an epoxy resin is used. 2 outer layer 42
A part of b and the fiber direction of the third outer layer 42c make an angle of 45 degrees with the axial direction of the stringer body 33a. By providing the outer layer 42 with such a laminated structure, the strength against torsion and buckling can be increased, and when the outer plate 32 is damaged by any factor,
Even if a load due to wind pressure acts on the stringer 33, the deformation of the stringer body 33a can be prevented.

FIG. 7 is a sectional view showing the stringer body 33a and the protection plate 43. Protective plate 43 as protective layer
Comprises a first protection plate 43a, a second protection plate 43b, and a third protection plate 43c. First to third protection plates 43a to 43c
Is viewed in a section perpendicular to the axis of the stringer body 33a,
Each of the two parallel sides of the trapezoid is adhered to the side surface except for the side surface that forms the longer side via a film-like adhesive 44.

As the protective plate 43, a material having an impedance ρE, which is a product of the density ρ and the elastic modulus E, is larger than the composite material covering the core 41 is used. In the present embodiment,
As the protective plate 43, a plate material made of a titanium alloy and having a thickness of 0.5 mm is used. Thus, even if a small piece collides with the stringer 33 due to some factor, at least the damage of the stringer main body 33a can be prevented, and the stringer 33
It is possible to prevent the strength of the entire wing from being reduced due to the damage of the wing.
Also, by dividing the protection plate 43 into three parts,
Not only can be easily processed, but also the protection plate 4
In the case where the small piece collides with the small piece 3, the damage of the protection plate 43 can be limited to one of the divided protection plates where the small piece actually collides.

The protection plate 43 includes a stringer body 33a.
Therefore, uniform protection strength can be obtained as compared with the case where the fastener is joined by a fastener that penetrates a protection plate such as a rivet. Further, the protection plate 43 can be easily attached to the stringer body 33a.

Although the protective plate 43 is made of a plate material made of a titanium alloy, a material having a higher impedance than the composite material covering the core 41, such as stainless steel or an aramid fiber composite material having a large penetration resistance for preventing small pieces from penetrating, is used. May be used. The density ρ of CFRP, a titanium alloy and stainless steel, which is a composite material covering the core 41,
Table 1 shows the values of the elastic modulus E and the impedance ρE.

[0031]

[Table 1]

The impedance ρE of the material of the protection plate 43
Is desirably 3000 [Pa · N / mm 3] or more. The protection plate 43 includes first to third protection plates 43a to 43a.
Although the structure is divided into three parts 43c, it may be an integral type not divided.

In order to simplify the manufacturing process of the stringer 33, the outer plate 32 is bonded to the stringer 33, the stringer 33 is bonded to the protective plate 43, and the core 41 is formed to the outer layer 42.
And bonding at the same time.

As described above, the outer shape of the stringer 33 in the cross section perpendicular to the axis is substantially substantially trapezoidal, and when viewed in the cross section perpendicular to the axis, the side surface 31b which is the longer side of the two parallel sides of the trapezoid. Is adhered to the outer plate 32 from the inner side of the wing. For example, when the outer plate 32 is damaged by some factor, the wind flowing into the wing flows smoothly on the outer periphery of the stringer 33. The load acting on the stringer 33 can be reduced.

The stringer body 33a is made of a core 41 made of a foamed synthetic resin material and an outer layer 42 made of CFRP.
By doing so, it is possible to reduce the mass required for providing strength against predetermined torsion and buckling as compared with a stringer body having the same cross-sectional shape made of a metal material. Thereby, the cross-sectional area of the stringer 33 can be reduced or the cross-sectional area of the stringer 33 can be changed without changing the number of the stringers 33 fixed to the outer plate 32 between the front girder 26 and the rear girder 27. Without doing so, the number of stringers 33 can be reduced and the spacing between the stringers 33 can be increased.

In this embodiment, the stringer 33
Has a substantially trapezoidal cross section perpendicular to the axis, but when the outer plate 32 is damaged for some reason, a polygon such as a triangle and a semicircle such that the wind flowing into the wing flows smoothly around the stringer 33. A cross-sectional shape such as In this case, the protection plate has a shape corresponding to the stringer main body, and is divided or molded according to the stringer main body.

FIG. 8A shows the outer cover 3 in a state in which the outer plate 32 has been scattered by the explosion of the explosive bomb landing on the horizontal stabilizer 12.
FIG. 8B is a cross-sectional view illustrating a section II of FIG. 8A. As described above, the stringer 33 can prevent deformation due to the wind pressure of the blast generated by the explosion of the explosive bomb. Also, even if the outer plate 32 scatters, the stringer 33 does not deform, so that the horizontal tail 1
2 can prevent a reduction in strength against torsion and buckling of the whole. Further, by making the structure in which the core 41 is filled without making the stringer 33 have a hollow structure, when a small piece released from the explosive bomb penetrates the stringer 33, the blast enters the stringer 33 together with the small piece. Can prevent charging. Stringer 3
3 is fixed to the outer plate 32 by means of adhesive bonding, so that even if the outer plate 32
There is no scattering with.

FIG. 9A is a cross-sectional view showing the stringer 33 through which the small piece 81 discharged from the explosive bullet penetrates. In the unlikely event that the small piece 81 released from the explosive bullet penetrates the stringer body 33a through the first protection plate 43a of the stringer 33, a part of the first protection plate 43a separates from the stringer body 33a. However, the second protection plate 43b and the third protection plate 43c are not damaged and do not separate from the stringer main body 33a.

FIG. 9B is a cross-sectional view showing the stringer 33A through which the small pieces 81 released from the explosive bomb penetrate.
The stringer 33A shown in FIG. 9 (2) has the same stringer body 33a as the stringer 33 of the present embodiment.
The integrated protective plate 43A is bonded via a film-like adhesive 44. In the unlikely event that the small piece 81 released from the explosive bomb and the stringer 33A is viewed in a section perpendicular to the axis of the stringer body 33a, it is adhered to the side surface that forms one of the two oblique sides excluding the two parallel sides of the trapezoid. When passing through the first protection portion 82a of the protection plate 43A and the stringer body 33a, the first protection portion 43a
Is separated from the stringer body 33a, and the first part 8
Although the second protection portion 82b of the protection plate 43A connected to the second protection member 2a is separated from the stringer body 33a together with the first protection portion 82a, since the protection plate 43A is an integral type, FIG.
Compared to the first protective plate 43a shown in (1), the stringer does not separate much from the stringer body 33a in the axial direction of the stringer.

FIG. 10A shows the outer cover 3 of the present embodiment.
FIG. 10 (2) is a cross-sectional view showing a conventional outer cover 31A. The conventional outer shell 31A includes an outer plate 32A and a stringer 91 made of a metal material having a substantially J-shaped cross section perpendicular to the axis. The spacing of the stringers required to provide strength against torsion and buckling of a given wing is L in the outer cover 31A shown in FIG. 10 (2), but is equal to L in the outer cover 31A shown in FIG. 10 (1). Then, the stringer interval is L + α. α is a value of 0 or more. Thus, the stringer body 3 of the present embodiment
The outer layer 42 of 3a has a cylindrical shape and is closed in a cross section perpendicular to the axis, and the stringer body 33a is formed in a thick closed cross-sectional structure. Since the strength against torsion can be increased as compared with the stringer 91 having an open cross-sectional structure, the interval between the stringers 33 provided on the outer cover 31 can be increased, in other words, the number of the stringers 33 can be reduced. A small piece released from a bullet is a stringer 3
3 can be reduced in probability.

[0041]

According to the first aspect of the present invention, the reinforcing body has a core made of a foamed synthetic resin material and an outer layer made of a composite material in which a fiber material is impregnated with a synthetic resin. Coated. As described above, since the outer layer has a cylindrical shape and is closed in a cross section perpendicular to the axis, and the reinforcing body is formed in a thick-walled closed cross-sectional structure, the conventional J-shape having the same minimum circumscribed circle radius in the cross section is used. The strength against torsion can be increased as compared with the reinforcing body having the open cross-sectional structure. Therefore, for example, even if the outer plate is damaged by some factor and a load due to wind pressure acts on the reinforcing member, the deformation of the reinforcing member can be prevented. Further, since the foamed synthetic resin material and the composite material can be easily molded by a mold, a wing reinforcement having a complicated shape can be easily molded.

According to the second aspect of the present invention, the reinforcing member is made of a material which covers the reinforcing member body from the outside and has a value of a product of density and elastic modulus larger than that of the composite material covering the core. Since the protective layer is provided, even if a small piece collides with the reinforcing member due to some factor, at least damage to the reinforcing member main body can be prevented. This can prevent the strength of the entire wing from being reduced due to damage to the reinforcement.

According to the third aspect of the present invention, since the protective layer made of a plate is adhered to the reinforcing member main body, the protective layer is more uniform in comparison with a case where the protective layer such as a rivet is joined by a fastener penetrating therethrough. Strength can be obtained. Further, the protection layer can be easily attached to the reinforcing body.

[Brief description of the drawings]

FIG. 1 is a perspective view showing an aircraft 11 using a wing reinforcement 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 shows the internal structure 2 of the horizontal stabilizer 21 of the horizontal stabilizer 12.
It is a perspective view which shows 1a.

FIG. 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. 5 is a cross-sectional view showing a stringer 33 according to an embodiment of the present invention.

FIG. 6A is a cross-sectional view showing a stringer main body 33a, and FIG. 6B is a perspective view showing the stringer main body 33a.

FIG. 7 is a sectional view showing a stringer main body 33a and a protection plate 43.

FIG. 8A is a cross-sectional view showing the outer cover 31 in a state where the outer plate 32 has been scattered by the explosion of the explosive landed on the horizontal stabilizer 12, and FIG. 8B is a sectional view of FIG. It is sectional drawing to which section II of 1) was expanded.

FIG. 9 (1) shows a small piece 81 released from an explosive bomb.
FIG. 9 is a cross-sectional view showing a stringer 33 penetrated by FIG.
(2) is a cross-sectional view showing the stringer 33A through which the small piece 81 released from the explosive bullet has penetrated.

FIG. 10 (1) shows an outer cover 31 of the present embodiment.
FIG. 10 (2) is a sectional view showing a conventional outer cover 3;
It is sectional drawing which shows 1A.

FIG. 11 is a cross-sectional view illustrating a state when a burst bomb collides with an object.

FIG. 12 is a cross-sectional view showing a state when the explosive bomb 2 collides with the wing 5;

[Explanation of symbols]

 32 outer plate 33 stringer 33a stringer body 41 core 42 outer layer 43 protective plate 44 adhesive

Claims (3)

[Claims] 1. A reinforcing member fixed to an outer plate of an aircraft wing from an inner side of the wing, wherein a core made of a foamed synthetic resin material has an outer layer made of a composite material in which a fiber material is impregnated with a synthetic resin. A reinforcement body that is covered over the entire circumference in the circumferential direction and is fixed to the outer plate. 2. The blade according to claim 1, further comprising a protective layer that covers the reinforcement body from the outside and that is made of a material having a value of a product of density and elastic modulus larger than that of the composite material. Reinforcement. 3. The wing reinforcement according to claim 2, wherein the protection layer is made of a plate material and is adhered to the reinforcement body.