Structural stealth integrated missile wing and forming method

Abstract

The invention discloses a structure stealth integrated missile wing and a forming method, the structure stealth integrated missile wing comprises a main joint, a wing body and a wing tip, and the main joint is connected with the wing body in an embedded part mode when the missile wing is formed; the section of the wing body is in a fin shape, the wing body comprises an outer wing body skin, an inner framework structure and a filling structure, the front end area of the wing body is a radar wave irradiation area, the surface layer of the wing body skin in the area is sunken and thinned, and the surface layer of the wing body skin is covered and filled with a front edge wave-absorbing composite material. The section of the front edge of the missile wing is the fin-shaped arc surface, the reflection intensity of radar waves can be greatly reduced, the stealth function can be achieved only by adopting the composite stealth layer capable of absorbing electromagnetic waves compared with a front edge stealth arc area, the wave-absorbing prepreg and the wave-absorbing foam are integrally formed, and the wave-absorbing effect is good. The technical problem of implementation of a stealth coating and the cost of anti-falling maintenance are avoided, meanwhile, the manufacturing cost of the missile wing is lower, the light weight effect is obvious, and the missile has the farther voyage.

Description

Technical Field

[0001] The present invention relates to the technical field of missile wing structures, and in particular to a missile wing with integrated stealth structure and a forming method thereof. Background Art

[0002] With the continuous development and widespread application of radar and other reconnaissance equipment detection technology, the stealth performance of weapons and equipment has become crucial. As an important component of missiles, the stealth effect of missile wings has a significant impact on the combat effectiveness of missiles.

[0003] Conventional stealth technology is to spray absorbing coating materials on the outer surface of the wing, which can achieve a certain stealth effect, but the required coating is relatively thick, generally about 2mm. If it is too thin, the stealth effect will be poor. Spraying a thicker coating directly on the leading edge of the wing will significantly change the aerodynamic shape of the wing, increase weight, and affect flight performance; reducing the leading edge size before spraying will cause the cross-sectional size of the substrate to become smaller, affecting the strength and stiffness of the wing.

[0004] At the same time, the absorbing coating has a poor bond with the substrate and is easy to fall off, requiring frequent maintenance and re-coating, which is difficult to maintain. Using structural adhesive to reinforce between the coating and the substrate will increase the difficulty of construction and the cost of use, and the coating thickness is difficult to control, so the coating stealth has great limitations. Summary of the invention

[0005] The purpose of the present invention is to solve the shortcomings of the prior art and to propose a missile wing with integrated stealth structure and a forming method. Its purpose is to comprehensively apply structural materials with wave-absorbing functions to realize the integration of wing structure forming and stealth function, so as to solve the above-mentioned technical problems while achieving the effect of improving rigidity and reducing weight.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions: A missile wing with integrated stealth structure, comprising a main joint, a wing body and a wing tip, wherein the main joint is connected to the wing body in the form of a pre-embedded part when the wing is formed; The wing-fuselage cross-section is fin-shaped, including an external wing-fuselage skin and an internal skeleton structure and filling structure. The front end area of ​​the wing-fuselage is the radar wave irradiation area, where the wing-fuselage skin surface is concave and thin, and its surface is covered and filled with a leading edge absorbing composite material.

[0007] Preferably, the upper end side of the leading edge absorbing composite material is the outermost point C of the upper wing surface, the lower end side of the leading edge absorbing composite material is the outermost point D of the lower wing surface, and the projection area of ​​point C, the trailing edge of the wing body and point D in the vertical direction is covered by the projection area of ​​point C, the leading edge of the wing body and point D in the vertical direction.

[0008] Preferably, the skeleton structure includes a front beam and a rear beam, both of which are U-shaped structures made of carbon fiber composite materials. The front beam and the rear beam divide the wing body into three areas: front, middle and rear. The above three areas are filled with conformal filling structures.

[0009] Preferably, the filling structure comprises wing-fuselage leading edge foam, wing-fuselage middle foam and wing-fuselage trailing edge foam, and the wing-fuselage leading edge foam, wing-fuselage middle foam and wing-fuselage trailing edge foam are respectively and conformally filled in the above-mentioned front, middle and rear three regions.

[0010] Preferably, the cross-sectional shape of the wingtip is consistent with that of the wing body, and its end face is a plane, which is the irradiation surface of the radar wave. The wingtip includes a wingtip skin, a wingtip absorbing foam and a foam film. The wingtip absorbing foam is filled in the wingtip skin, and the wingtip absorbing foam is connected to the wing body through the foam film.

[0011] Preferably, the joint between the leading edge absorbing composite material and the wing-fuselage skin has a smooth transition without a step difference, the thickness of the leading edge absorbing composite material is less than 1 mm, and the wing-fuselage skin is made of fiberglass.

[0012] Preferably, the wing-fuselage leading edge foam, the wing-fuselage middle foam and the wing-fuselage trailing edge foam are made of polymethacrylimide foam PMI and are processed into prefabricated parts by CNC.

[0013] Preferably, the wing tip absorbing foam is made of polymethacrylimide (PMI) mixed with graphene absorbing foam.

[0014] Preferably, the axial length of the wing tip absorbing foam is L, and the value range of L is 80-100 mm.

[0015] A method for forming a missile wing with integrated structural stealth, the method comprising the following steps: Step 1: Cut the carbon fiber and epoxy prepreg of the wing-fuselage skin, front beam and rear beam, the absorbing prepreg of the leading edge absorbing composite material layer, the glass fiber and epoxy prepreg of the wing tip skin according to the material drawing, and CNC process the wing-fuselage leading edge foam, wing-fuselage middle foam, wing-fuselage trailing edge foam and wing tip absorbing foam; Step 2: Lay the front beam and the rear beam stack on the foam in the middle of the wing body, and then assemble them with the wing body leading edge foam, the wing body trailing edge foam, the wing tip absorbing foam and the main joint in the female mold; Step 3: Take the assembled components out of the mold cavity, use prepreg to lay layers on the assembled foam, put them into a vacuum bag after laying 4-6 layers, and pre-compact them once by vacuuming. The glass fiber and epoxy prepreg of the wing tip and the carbon fiber and epoxy prepreg of the wing body are overlapped in each layer, and the overlapping areas of adjacent layers are staggered; Step 4: After the radar-absorbing prepreg is laid on the leading edge, the wing blank with all the layers laid is placed into the lower mold cavity of the female mold, the female mold and the upper mold are closed, and the wing blank is moved to the press, and heated and pressurized to cure and shape according to the curing process curve; Step 5: After curing is completed and cooling is completed, the upper mold of the female mold is opened and the wing is taken out to complete the formation of the missile wing with integrated structure and stealth.

[0016] Compared with the prior art, the present invention has the following beneficial effects: (1) The cross-section of the leading edge of the wing of the present invention is a fin-shaped arc surface, which can greatly reduce the reflection intensity of radar waves. Therefore, the leading edge stealth arc area only needs to adopt a composite material stealth layer that absorbs electromagnetic waves to achieve the stealth function. The rear of the leading edge is narrowed within the stealth arc, which is a blind spot for radar wave detection. The wing tip surface is a plane, and its fiberglass skin is a wave-transmitting layer, and the wing tip foam is a wave-absorbing stealth layer. The wing tip foam wave is axially longer and can absorb all radar waves. The leading edge circular area stealth combined with the wing tip foam stealth makes the surface of the wing facing the direction of radar wave irradiation have sufficient stealth function; (2) The combined force formed by the carbon fiber composite front beam, rear beam, skin and PMI foam makes the wing body have high rigidity, and the deformation caused by bending moment and torque during flight is very small, ensuring that the stealth wing shape and aerodynamic shape are not affected; (3) The integrated molding of radar-absorbing prepreg and radar-absorbing foam avoids the technical difficulties in implementing the stealth coating and the cost of anti-shedding maintenance. At the same time, the manufacturing cost of the missile wing is lower, and the lightweight effect is obvious, which enables the missile to have a longer range. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more specifically and intuitively illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art are briefly introduced below.

[0018] Figure 1 is a schematic diagram of the structure of a wing of an embodiment of the present invention; Figure 2 is a schematic diagram of the structure inside the wing skin of an embodiment of the present invention; Figure 3 The embodiment of the present invention Figure 1 Cross-section view at the middle AA position; Figure 4 The embodiment of the present invention Figure 1 Cross-section view of the middle BB position; Figure 5 The wing blank of the embodiment of the present invention is placed into a mold, Figure 1 Cross-section view at the AA position.

[0019] In the figure: main joint 1, wing body 2, wing tip 3, leading edge absorbing composite material 4; Wing-body skin 201, trailing edge 202, front beam 203, rear beam 204, wing-body leading edge foam 205, wing-body middle foam 206, wing-body trailing edge foam 207; Wing tip skin 301, wing tip wave absorbing foam 302, foam film 303; Female mold lower mold 501 and female mold upper mold 502. DETAILED DESCRIPTION

[0020] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0021] Reference Figure 1-5 , a missile wing with integrated stealth structure, comprising a main joint 1, a wing body 2 and a wing tip 3, wherein the main joint 1 is connected to the wing body 2 in the form of an embedded part when the wing is formed; The main joint 1 is a machined part, and is connected to the wing-body 2 as a pre-embedded part when the wing is formed. Its function is to connect to the body compartment, and the wing-body 2 is responsible for stealth shielding.

[0022] The cross-sectional shape of the wing-fuselage 2 is fin-shaped, and includes an external wing-fuselage skin 201 and an internal skeleton structure and a filling structure. The front end area of ​​the wing-fuselage 2 is a radar wave irradiation area, where the surface layer of the wing-fuselage skin 201 is concave and thin, and its surface layer is covered and filled with a leading edge absorbing composite material 4.

[0023] The wing-body 2 has a uniform cross-section in the axial direction and a fin-shaped cross-section. One end of the full arc is the leading edge. The area between the outermost point C of the upper wing surface and the outermost point D of the lower wing surface is the radar wave irradiation area. The thickness of the carbon fiber wing-body skin 201 in this area becomes thinner, and the surface layer is filled with the leading edge absorbing composite material 4. Its full arc shape can greatly reduce the reflection intensity of radar waves, and combined with the effect of the 1mm thick absorbing layer, the stealth effect of the wing-body is achieved.

[0024] In this embodiment, the upper end side of the leading edge absorbing composite material 4 is the outermost point C of the upper wing surface, and the lower end side of the leading edge absorbing composite material 4 is the outermost point D of the lower wing surface. The projection area of ​​point C, the trailing edge 202 of the wing body 2 and point D in the vertical direction is covered by the projection area of ​​point C, the leading edge of the wing body 2 and point D in the vertical direction.

[0025] The joint between the leading edge absorbing composite material layer 4 and the wing-body skin 201 has a smooth transition without step difference. The area formed by the trailing edge 202, the outermost point C of the upper wing surface, and the outermost point D of the lower wing surface needs to be hidden behind the leading edge absorbing composite material layer 4. To ensure the hiding effect, the wing-body 2 needs sufficient flight stiffness.

[0026] In this embodiment, the skeleton structure includes a front beam 203 and a rear beam 204. The front beam 203 and the rear beam 204 are both U-shaped structures made of carbon fiber composite materials. The front beam 203 and the rear beam 204 divide the wing body 2 into three areas: front, middle and rear. The above three areas are filled with conformal filling structures.

[0027] In this embodiment, the filling structure includes a wing-fuselage leading edge foam 205, a wing-fuselage middle foam 206 and a wing-fuselage trailing edge foam 207. The wing-fuselage leading edge foam 205, the wing-fuselage middle foam 206 and the wing-fuselage trailing edge foam 207 are respectively filled in the above-mentioned front, middle and rear three areas in a conformal manner.

[0028] In this embodiment, the cross-sectional shape of the wing tip 3 is consistent with the wing body 2, and its end face is a plane, which is the irradiation surface of the radar wave. The wing tip 3 includes a wing tip skin 301, a wing tip absorbing foam 302 and a foam film 303. The wing tip absorbing foam 302 is filled in the wing tip skin 301, and the wing tip absorbing foam 302 is connected to the wing body 2 through the foam film 303. The wing tip 3 is made stealthy by the absorbing foam 302.

[0029] In this embodiment, the joint between the leading edge absorbing composite material 4 and the wing-body skin 201 has a smooth transition without step difference. The thickness of the leading edge absorbing composite material 4 is less than 1 mm. The wing tip skin 301 is made of fiberglass with strong wave transmission performance and high strength.

[0030] In this embodiment, the wing-fuselage leading edge foam 205, the wing-fuselage middle foam 206 and the wing-fuselage trailing edge foam 207 are made of polymethacrylimide foam PMI and are processed into prefabricated parts by CNC.

[0031] In this embodiment, the wing tip absorbing foam 302 is made of polymethacrylimide (PMI) mixed with graphene absorbing foam.

[0032] In this embodiment, the axial length of the wing tip absorbing foam 302 is L, and the value range of L is 80-100 mm.

[0033] A method for forming a missile wing with integrated structural stealth, the method comprising the following steps: Step 1: Cut the carbon fiber and epoxy prepreg of the wing-fuselage skin 201, the front beam 203, and the rear beam 204, the absorbing prepreg of the leading edge absorbing composite material layer 4, the glass fiber and epoxy prepreg of the wing tip skin 301 according to the material drawing, and CNC process the wing-fuselage leading edge foam 205, the wing-fuselage middle foam 206, the wing-fuselage trailing edge foam 207, and the wing tip absorbing foam 302; Step 2: Lay the front beam 203 and the rear beam 204 on the wing-fuselage middle foam 206, and then assemble them with the wing-fuselage leading edge foam 205, the wing-fuselage trailing edge foam 207, the wing tip absorbing foam 302 and the main joint 1 in the female mold lower mold 501; Step 3: Take the assembled components out of the mold cavity, use prepreg to lay and wrap on the assembled foam, put it into a vacuum bag after laying 4-6 layers, and pre-compact it once by vacuuming. In the butt-jointed lamination area of ​​the glass fiber and epoxy prepreg of the wing tip 3 and the carbon fiber and epoxy prepreg of the wing body 2, each layer is overlapped, and the overlapping areas of adjacent layers are staggered; Step 4: After the radar absorbing prepreg is laid on the leading edge, the wing blank with all the layers laid is placed into the lower mold cavity of the female mold, the female mold upper mold 502 is closed, and the wing blank is moved to the press, and heated and pressurized to be cured and formed according to the curing process curve; Step 5: After curing is completed and cooling is completed, the upper mold of the female mold is opened 502, and the wing is taken out to complete the formation of the missile wing with integrated structure and stealth.

[0034] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A missile wing with integrated stealth structure, comprising a main joint (1), a wing body (2) and a wing tip (3), characterized in that: The main joint (1) is connected to the wing body (2) in the form of a pre-embedded part when the wing is formed; The cross-sectional shape of the wing-fuselage (2) is fin-shaped, and comprises an external wing-fuselage skin (201) and an internal skeleton structure and a filling structure. The front end area of ​​the wing-fuselage (2) is a radar wave irradiation area, and the surface layer of the wing-fuselage skin (201) in this area is concave and thin, and its surface layer is covered and filled with a leading edge absorbing composite material (4).

2. The missile wing with integrated stealth structure according to claim 1, characterized in that: The upper end side of the leading edge absorbing composite material (4) is the outermost point C of the upper wing surface, the lower end side of the leading edge absorbing composite material (4) is the outermost point D of the lower wing surface, and the projection area of ​​point C, the trailing edge (202) of the wing body (2) and point D in the vertical direction is covered by the projection area of ​​point C, the leading edge of the wing body (2) and point D in the vertical direction.

3. The missile wing with integrated stealth structure according to claim 2, characterized in that: The skeleton structure comprises a front beam (203) and a rear beam (204); the front beam (203) and the rear beam (204) are both U-shaped structures and are made of carbon fiber composite materials; the front beam (203) and the rear beam (204) divide the wing body (2) into three regions: front, middle and rear; and the three regions are filled using a conformal filling structure.

4. The missile wing with integrated stealth structure according to claim 3, characterized in that: The filling structure comprises a wing-fuselage leading edge foam (205), a wing-fuselage middle foam (206) and a wing-fuselage trailing edge foam (207), and the wing-fuselage leading edge foam (205), the wing-fuselage middle foam (206) and the wing-fuselage trailing edge foam (207) are respectively and conformally filled in the aforementioned front, middle and rear three regions.

5. The missile wing with integrated stealth structure according to claim 4, characterized in that: The cross-sectional shape of the wing tip (3) is consistent with that of the wing body (2), and its end face is a plane, which is an irradiation surface of radar waves. The wing tip (3) comprises a wing tip skin (301), a wing tip wave-absorbing foam (302) and a foaming film (303). The wing tip wave-absorbing foam (302) is filled in the wing tip skin (301), and the wing tip wave-absorbing foam (302) is connected to the wing body (2) via the foaming film (303).

6. The missile wing with integrated stealth structure according to claim 5, characterized in that: The joint between the leading edge absorbing composite material (4) and the wing-body skin (201) has a smooth transition and no step difference; the thickness of the leading edge absorbing composite material (4) is less than 1 mm; and the wing-body skin (201) is made of glass fiber reinforced plastic.

7. The missile wing with integrated stealth structure according to claim 6, characterized in that: The wing-body leading edge foam (205), the wing-body middle foam (206) and the wing-body trailing edge foam (207) are made of polymethacrylimide foam (PMI) and are processed into prefabricated parts using CNC.

8. The missile wing with integrated stealth structure according to claim 6, characterized in that: The wing tip wave-absorbing foam (302) is made of polymethacrylimide (PMI) mixed with graphene wave-absorbing foam.

9. The missile wing with integrated stealth structure according to claim 6, characterized in that: The wing tip wave-absorbing foam (302) has an axial length of L, and the value range of L is 80-100 mm.

10. The method for forming a missile wing with integrated stealth structure as claimed in claim 9, characterized in that: The molding method comprises the following steps: Step 1: Cut the carbon fiber and epoxy prepreg of the wing-fuselage skin (201), the front beam (203), and the rear beam (204), the absorbing prepreg of the leading edge absorbing composite material layer (4), the glass fiber and epoxy prepreg of the wing tip skin (301) according to the material drawing, and CNC process the wing-fuselage leading edge foam (205), the wing-fuselage middle foam (206), the wing-fuselage trailing edge foam (207), and the wing tip absorbing foam (302); Step 2: Lay the front beam (203) and the rear beam (204) on the wing-fuselage middle foam (206) and then assemble them with the wing-fuselage leading edge foam (205), the wing-fuselage trailing edge foam (207), the wing tip wave-absorbing foam (302) and the main joint (1) in the female mold lower mold (501); Step 3: Take the assembled components out of the mold cavity, and use prepreg to lay layers on the assembled foam. Place it in a vacuum bag after laying 4-6 layers, and pre-compact it once by vacuuming. In the lamination area where the glass fiber and epoxy prepreg of the wing tip (3) and the carbon fiber and epoxy prepreg of the wing body (2) are butt-jointed, each layer is overlapped, and the overlapping areas of adjacent layers are staggered; Step 4: After the absorbing prepreg is laid on the leading edge, the wing blank with all the layers laid is placed into the lower mold cavity of the female mold, the female mold upper mold is closed (502), and the wing blank is moved to a press, and heated and pressurized to cure and shape according to the curing process curve; Step 5: After curing is completed and cooling is completed, the upper mold of the female mold is opened (502), and the wing is taken out to complete the formation of the missile wing with integrated structure and stealth.

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