CN106403729B - A kind of structure suction wave missile wing of high Stealth Fighter - Google Patents
A kind of structure suction wave missile wing of high Stealth Fighter Download PDFInfo
- Publication number
- CN106403729B CN106403729B CN201611049119.3A CN201611049119A CN106403729B CN 106403729 B CN106403729 B CN 106403729B CN 201611049119 A CN201611049119 A CN 201611049119A CN 106403729 B CN106403729 B CN 106403729B
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- CN
- China
- Prior art keywords
- wave
- wing
- missile
- missile wing
- leading edge
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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 present invention relates to a kind of structures of high Stealth Fighter to inhale wave missile wing, including wing tip (1), missile wing leading edge (2) and aerofoil (3)；Wing tip (1) is made with missile wing leading edge (2) of foam wave-suction material, foam wave-suction material is combined by Polymethacrylimide (PMI) foamed material with functionalization graphene, and aerofoil (3) is processed by carbon fibre material；Wing tip (1) and missile wing leading edge (2) difference after processing is completed, are pasted onto on aerofoil (3) to be combined into and inhale wave missile wing, then inhaling wave missile wing outer surface fw frp.The structure of the high Stealth Fighter of the present invention inhales wave missile wing, and used structural wave-absorbing material has attenuating to electromagnetic wave, and guided missile Stealth Fighter can be effectively improved on missile wing by applying, while reduce the weight of guided missile, improve the penetration ability of guided missile.
Description
Technical field
The invention belongs to subsonic speed air-to-ground guided missile fields, and in particular to a kind of structure suction wave missile wing of high Stealth Fighter.
Background technology
Subsonic speed air-to-ground guided missile since flying speed is slower, easily by enemy radar detect and it is under attack, therefore, it is necessary to carry
The high Stealth Fighter of its own.Missile wing be to provide lift component and it is preceding to lateral main scattering source, when design need to examine
Consider stealthy requirement.
Existing stealthy missile wing leading edge, wing tip are generally by the way of the traditional antiradar coatings of coating, traditional antiradar coatings tool
Have the characteristics that weight is big, construction process requirement is high, antiradar coatings thickness is difficult to control in missile wing edge when construction, influences missile wing
Stealth Fighter.
Invention content
The present invention devises a kind of subsonic speed air-to-ground guided missile missile wing having high Stealth Fighter, and disclosure satisfy that guided missile is total
Body and pneumatic demand.
In view of the above problem of the prior art, according to one aspect of the present disclosure, the present invention uses following technology
Scheme：
A kind of structure suction wave missile wing of high Stealth Fighter, including wing tip (1), missile wing leading edge (2) and aerofoil (3)；
Wherein, wing tip (1) is made with missile wing leading edge (2) of foam wave-suction material, and foam wave-suction material is by poly- methyl-prop
Alkene acid imide (PMI) foamed material is combined with functionalization graphene, in polymethacrylimide foam material foaming ring
Functionalization graphene material is added in section, polymethacrylimide foam material plays light structures supporting role, function fossil
Black alkene plays absorbent, and foam wave-suction material is finally processed into wing tip (1) and missile wing leading edge (2)；Aerofoil (3) is by carbon fiber
Material is processed into；Wing tip (1) and missile wing leading edge (2) difference after processing is completed, are pasted onto on aerofoil (3) to be combined into and inhale wave bullet
The wing, then inhaling wave missile wing outer surface fw frp.
Advantageous effect：
The structure of the high Stealth Fighter of the present invention inhales wave missile wing, and used structural wave-absorbing material has decaying to electromagnetic wave
Effect, guided missile Stealth Fighter can be effectively improved on missile wing by applying, while reduce the weight of guided missile, improve the prominent anti-of guided missile
Ability.
Description of the drawings
Fig. 1 foam wave-suction material electromagnetic wave attenuation performances
Fig. 2 high Stealth Fighter structures inhale wave missile wing
Fig. 3 9.4GHz Horizontal Polar Diagrams
Fig. 4 15GHz Horizontal Polar Diagrams
Specific implementation mode
The present invention is described in further detail with reference to embodiment, embodiments of the present invention are not limited thereto.
Fig. 1 is foam wave-suction material electromagnetic wave attenuation performance map, which 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 of foam wave-suction material+carbon fibre material.Missile wing is mainly by missile wing leading edge, the wing
Point, aerofoil three parts composition, missile wing leading edge and wing tip are missile wing strong scattering areas, RCS are reduced using absorbing material, with PMI foams
Material is basis material, for carrying and disperseing wave absorbing agent, functionalization graphene material is added as absorbent, is formed to have and be held
Loading capability structural wave-absorbing material.To reduce cost, missile wing rest part uses carbon fibre material.Missile wing leading edge, wing tip, carbon fiber
Distinguish after processing is completed, in outer surface wrap fiberglass material sections.
The strong scattering source of missile wing is mainly up-front mirror-reflection, and 0 ° of azimuth is electromagnetic wave normal incidence missile wing edge,
The RCS test values of foam wave-suction material missile wing and metal material missile wing are compared, Fig. 3, Fig. 4 are shown in 9.4GHz, 15GHz, orientation
When 0 ° of angle, foam wave-suction material missile wing RCS peak values than metallic state difference lower 10dB (being reduced to -6.4dB from 3.7dB),
14dB (is reduced to -13.8dB) from 2.9dB, this shows that foam wave-suction material exists for reducing the RCS of missile wing leading edge mirror-reflection
High frequency treatment has good effect.
Claims (1)
1. a kind of structure of high Stealth Fighter inhales wave missile wing, including wing tip (1), missile wing leading edge (2) and aerofoil (3)；
Wherein, wing tip (1) is made with missile wing leading edge (2) of foam wave-suction material, and foam wave-suction material is by polymethyl acyl
Imines (PMI) foamed material is combined with functionalization graphene, in polymethacrylimide foam material foams link
Functionalization graphene material is added, polymethacrylimide foam material plays light structures supporting role, functionalization graphene
Play absorbent, foam wave-suction material is finally processed into wing tip (1) and missile wing leading edge (2)；Aerofoil (3) is by carbon fibre material
It is processed into；Wing tip (1) and missile wing leading edge (2) difference after processing is completed, are pasted onto on aerofoil (3) to be combined into and inhale wave missile wing, then
Inhaling wave 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 CN106403729A (en) | 2017-02-15 |
| CN106403729B true 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) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
Citations (6)
| 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 |
| 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 |
-
2016
- 2016-11-24 CN CN201611049119.3A patent/CN106403729B/en active Active
Patent Citations (6)
| 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 |
| 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)
| Title |
|---|
| 利用吸收体降低弹翼RCS的实验研究;戴全辉等;《微波学报》;20001231;第16卷(第5期);第456-462、508页 * |
| 石墨烯在电磁屏蔽与吸波材料方面的应用及研究进展;李友良等;《新材料产业》;20131231(第9期);第37-41页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106403729A (en) | 2017-02-15 |
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