CN106403729A - Structural wave-absorbing missile wing with high stealth performance - Google Patents
Structural wave-absorbing missile wing with high stealth performance Download PDFInfo
- Publication number
- CN106403729A CN106403729A CN201611049119.3A CN201611049119A CN106403729A CN 106403729 A CN106403729 A CN 106403729A CN 201611049119 A CN201611049119 A CN 201611049119A CN 106403729 A CN106403729 A CN 106403729A
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- CN
- China
- Prior art keywords
- wing
- missile
- missile wing
- wave
- absorbing
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/04—Stabilising arrangements using fixed fins
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention relates to a structural wave-absorbing missile wing with high stealth performance. The structural wave-absorbing missile wing comprises a wing tip (1), a missile wing front edge (2) and a wing surface (3), wherein the wing tip (1) and the missile wing front edge (2) are made of a foam wave-absorbing material which is formed by compounding a polymethacrylimide (PMI) foam material and functional graphene; the wing surface (3) is formed by processing a carbon fiber material; and after being separately processed, the wing tip (1) and the missile wing front edge (2) are pasted on the wing surface (3) to form the wave-absorbing missile wing, and glass fiber reinforced plastic is wound on the outer surface of the wave-absorbing missile wing. According to the structural wave-absorbing missile wing with high stealth performance, the adopted structural wave-absorbing material has attenuation effect on electromagnetic waves, can effectively improve stealth performance of a missile while applied to the missile wing; and meanwhile, weight of the missile is reduced, and penetration capability of the missile is improved.
Description
Technical field
The invention belongs to subsonic speed air-to-ground guided missile field is and in particular to a kind of structure of high Stealth Fighter inhales ripple missile wing.
Background technology
Subsonic speed air-to-ground guided missile is slower due to flying speed, is easily detected and under attack by enemy radar, accordingly, it would be desirable to carry
The high Stealth Fighter of its own.Missile wing be provide lift part, be also before to lateral main scattering source, need to examine during design
Consider stealthy requirement.
, typically by the way of the traditional antiradar coatings of coating, traditional antiradar coatings have for existing stealthy missile wing leading edge, wing tip
Have the characteristics that weight is big, construction process requirement is high, during construction, antiradar coatings thickness is difficult to control in missile wing edge, affect missile wing
Stealth Fighter.
Content of the invention
The present invention devises a kind of subsonic speed air-to-ground guided missile missile wing possessing high Stealth Fighter, and disclosure satisfy that guided missile is total
Body and pneumatic demand.
In view of the problems referred to above of prior art, according to one side disclosed by the invention, the present invention adopts following technology
Scheme：
A kind of structure of high Stealth Fighter inhales ripple missile wing, including wing tip (1), missile wing leading edge (2) and aerofoil (3)；
Wherein, wing tip (1) and missile wing leading edge (2) are made using foam wave-suction material, and foam wave-suction material is by poly- methyl-prop
Alkene acid imide (PMI) foamed material is composited with functionalization graphene, in polymethacrylimide foam material foaming ring
Functionalization graphene material is added, polymethacrylimide foam material plays light structures supporting role, function fossil in section
Black alkene plays absorbent effect, finally foam wave-suction material is processed into wing tip (1) and missile wing leading edge (2)；Aerofoil (3) is by carbon fiber
Materials processing is made；After wing tip (1) and missile wing leading edge (2) machine respectively, it is pasted onto on aerofoil (3) and is combined into suction ripple bullet
The wing, then inhaling ripple missile wing outer surface fw frp.
Beneficial effect：
The structure of the high Stealth Fighter of the present invention inhales ripple missile wing, and the structural wave-absorbing material being adopted has decay to electromagnetic wave
Effect, applies and can effectively improve guided missile Stealth Fighter on missile wing, reduce the weight of guided missile simultaneously, improves the prominent anti-of guided missile
Ability.
Brief description
Fig. 1 foam wave-suction material electromagnetic wave attenuation performance
Fig. 2 high Stealth Fighter structure inhales ripple missile wing
Fig. 3 9.4GHz Horizontal Polar Diagram
Fig. 4 15GHz Horizontal Polar Diagram
Specific embodiment
With reference to embodiment, the present invention is described in further detail, but embodiments of the present invention not limited to this.
Fig. 1 is foam wave-suction material electromagnetic wave attenuation performance map, and this absorbing material has broadband absorbing ability, in 3-4GHz
Between reflectivity be less than -5dB, other frequency range reflectivity be respectively less than -10dB, 9-18GHz reflectivity be less than -15dB.
Fig. 2 is missile wing structure chart, is made using foam wave-suction material+carbon fibre material.Missile wing is mainly by missile wing leading edge, the wing
Point, aerofoil three part composition, missile wing leading edge and wing tip are missile wing strong scattering areas, reduce RCS using absorbing material, with PMI foam
Material is matrix material, for carrying and disperseing wave absorbing agent, adds functionalization graphene material as absorbent, is formed to have and hold
Loading capability structural wave-absorbing material.For reduces cost, missile wing remainder adopts carbon fibre material.Missile wing leading edge, wing tip, carbon fiber
After material sections machine respectively, in outer surface wrap fiberglass.
The strong scattering source of missile wing is mainly the mirror-reflection of leading edge, and 0 ° of azimuth is electromagnetic wave normal incidence missile wing edge,
Contrast foam wave-suction material missile wing and the RCS test value of metal material missile wing, Fig. 3, Fig. 4 are shown in 9.4GHz, 15GHz, orientation
During 0 ° of angle, foam wave-suction material missile wing RCS peakedness ratio metallic state low respectively 10dB (being reduced to -6.4dB from 3.7dB),
14dB (is reduced to -13.8dB from 2.9dB), and this shows that foam wave-suction material exists for the RCS reducing missile wing leading edge mirror-reflection
High frequency treatment has good effect.
Claims (1)
1. a kind of structure of high Stealth Fighter inhales ripple missile wing, including wing tip (1), missile wing leading edge (2) and aerofoil (3)；
Wherein, wing tip (1) and missile wing leading edge (2) are made using foam wave-suction material, and foam wave-suction material is by polymethyl acyl
Imines (PMI) foamed material is composited with functionalization graphene, in polymethacrylimide foam material foaming link
Add functionalization graphene material, polymethacrylimide foam material plays light structures supporting role, functionalization graphene
Play absorbent effect, finally foam wave-suction material is processed into wing tip (1) and missile wing leading edge (2)；Aerofoil (3) is by carbon fibre material
It is processed into；After wing tip (1) and missile wing leading edge (2) machine respectively, it is pasted onto on aerofoil (3) and is combined into suction ripple missile wing, then
Inhaling ripple missile wing outer surface fw frp.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611049119.3A CN106403729B (en) | 2016-11-24 | 2016-11-24 | A kind of structure suction wave missile wing of high Stealth Fighter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611049119.3A CN106403729B (en) | 2016-11-24 | 2016-11-24 | A kind of structure suction wave missile wing of high Stealth Fighter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106403729A true CN106403729A (en) | 2017-02-15 |
| CN106403729B CN106403729B (en) | 2018-07-31 |
Family
ID=58082187
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611049119.3A Active CN106403729B (en) | 2016-11-24 | 2016-11-24 | A kind of structure suction wave missile wing of high Stealth Fighter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106403729B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107726926A (en) * | 2017-09-12 | 2018-02-23 | 江西洪都航空工业集团有限责任公司 | A kind of stealthy/force-bearing type structure aerofoil |
| CN109612348A (en) * | 2018-11-23 | 2019-04-12 | 山东双科技股份有限公司 | A kind of composite material missile wing and its forming method |
Citations (6)
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|---|---|---|---|---|
| JPH1114299A (en) * | 1997-06-19 | 1999-01-22 | Nissan Motor Co Ltd | Wing for airframe |
| US6224013B1 (en) * | 1998-08-27 | 2001-05-01 | Lockheed Martin Corporation | Tail fin deployment device |
| EP1245921A1 (en) * | 2001-03-27 | 2002-10-02 | Oto Melara S.p.A. | Control group for directional fins on missiles and/or shells |
| CN104177745A (en) * | 2014-08-14 | 2014-12-03 | 中南大学 | Wave-absorbing type polymethacrylimide foam/chopped fiber composite material and preparation method thereof |
| CN104197790A (en) * | 2014-09-01 | 2014-12-10 | 北京航空航天大学 | Metal reinforced bar-fiber reinforced resin matrix composite material skin missile wing and manufacturing method thereof |
| CN105968397A (en) * | 2016-06-21 | 2016-09-28 | 江西洪都航空工业集团有限责任公司 | Empennage surface structure for improving low-frequency stealth performance |
-
2016
- 2016-11-24 CN CN201611049119.3A patent/CN106403729B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1114299A (en) * | 1997-06-19 | 1999-01-22 | Nissan Motor Co Ltd | Wing for airframe |
| US6224013B1 (en) * | 1998-08-27 | 2001-05-01 | Lockheed Martin Corporation | Tail fin deployment device |
| EP1245921A1 (en) * | 2001-03-27 | 2002-10-02 | Oto Melara S.p.A. | Control group for directional fins on missiles and/or shells |
| EP1245921B1 (en) * | 2001-03-27 | 2004-08-11 | Oto Melara S.p.A. | Control group for directional fins on missiles and/or shells |
| CN104177745A (en) * | 2014-08-14 | 2014-12-03 | 中南大学 | Wave-absorbing type polymethacrylimide foam/chopped fiber composite material and preparation method thereof |
| CN104197790A (en) * | 2014-09-01 | 2014-12-10 | 北京航空航天大学 | Metal reinforced bar-fiber reinforced resin matrix composite material skin missile wing and manufacturing method thereof |
| CN105968397A (en) * | 2016-06-21 | 2016-09-28 | 江西洪都航空工业集团有限责任公司 | Empennage surface structure for improving low-frequency stealth performance |
Non-Patent Citations (2)
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| 戴全辉等: "利用吸收体降低弹翼RCS的实验研究", 《微波学报》 * |
| 李友良等: "石墨烯在电磁屏蔽与吸波材料方面的应用及研究进展", 《新材料产业》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107726926A (en) * | 2017-09-12 | 2018-02-23 | 江西洪都航空工业集团有限责任公司 | A kind of stealthy/force-bearing type structure aerofoil |
| CN107726926B (en) * | 2017-09-12 | 2019-06-28 | 江西洪都航空工业集团有限责任公司 | A kind of stealthy/force-bearing type structure aerofoil |
| CN109612348A (en) * | 2018-11-23 | 2019-04-12 | 山东双科技股份有限公司 | A kind of composite material missile wing and its forming method |
| CN109612348B (en) * | 2018-11-23 | 2021-06-01 | 山东双一科技股份有限公司 | Composite material missile wing and forming method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106403729B (en) | 2018-07-31 |
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