CN114194374A - Wing and machining method thereof - Google Patents
Wing and machining method thereof Download PDFInfo
- Publication number
- CN114194374A CN114194374A CN202111536815.8A CN202111536815A CN114194374A CN 114194374 A CN114194374 A CN 114194374A CN 202111536815 A CN202111536815 A CN 202111536815A CN 114194374 A CN114194374 A CN 114194374A
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- Prior art keywords
- wing
- edge
- wave
- trailing edge
- leading edge
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Links
- 238000000034 method Methods 0.000 title claims description 7
- 238000003754 machining Methods 0.000 title description 3
- 239000000463 material Substances 0.000 claims abstract description 27
- 239000011358 absorbing material Substances 0.000 claims abstract description 19
- 230000002401 inhibitory effect Effects 0.000 claims abstract description 13
- 238000007493 shaping process Methods 0.000 claims abstract description 4
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 6
- 239000006096 absorbing agent Substances 0.000 claims description 6
- 239000000805 composite resin Substances 0.000 claims description 6
- 239000011152 fibreglass Substances 0.000 claims description 6
- 239000002131 composite material Substances 0.000 claims description 3
- 238000004804 winding Methods 0.000 claims description 3
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 4
- 238000003672 processing method Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 6
- 230000001629 suppression Effects 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 238000002310 reflectometry Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000003973 paint Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
Abstract
The invention provides a wing and a processing method thereof, relating to the technical field of aviation, wherein the wing comprises: the broadband wave absorbing wing comprises a wing body, a wing front edge and a wing rear edge, wherein the wing front edge and the wing rear edge are respectively positioned on two sides of the wing body, and the wing front edge is provided with an endowing piece made of broadband wave absorbing materials; the trailing edge of the wing is provided with the shaping piece made of the traveling wave inhibiting material, and the broadband wave absorbing material and the traveling wave inhibiting material are respectively applied to the front edge and the rear edge, so that the wing has an obvious attenuation effect on electromagnetic waves, the intensity of a scattering source can be effectively reduced, and the low detectability of the aircraft is improved.
Description
Technical Field
The invention belongs to the technical field of aviation, and particularly relates to a wing and a machining method thereof.
Background
Subsonic aircraft, due to their slow flight speed, are easily detected and attacked, and therefore, need to improve their own low detectability. The wing is a component providing lift and also a main scattering source in the forward and lateral directions, and the design needs to consider low detectability requirements.
Disclosure of Invention
In order to solve the problem of poor low detectability performance of a subsonic aircraft in the related art, the invention provides a wing and a processing method thereof, and the technical scheme is as follows:
in a first aspect, there is provided an airfoil comprising: the wing body, the wing leading edge and the wing trailing edge are respectively positioned at two sides of the wing body,
wherein, the leading edge of the wing is provided with an endowing piece made of broadband wave-absorbing material;
the trailing edge of the wing is provided with a shaped piece made of traveling wave inhibiting material.
Optionally, the broadband wave-absorbing material is a carbonyl iron type wave-absorbing agent composite resin and rubber composite material.
Optionally, the traveling wave suppression material is carbonyl iron type wave absorber composite resin.
Optionally, the trailing edge is of a smaller thickness than the leading edge.
Optionally, the thickness of the wing leading edge is 1.5-2.5 mm.
Optionally, the thickness of the trailing edge of the wing is 0.3-0.6 mm.
Optionally, the wing body is made of a carbon fibre material.
Optionally, the leading and trailing edges of the wing provided with the shaped pieces and the outer surface of the wing body are wrapped with glass reinforced plastic.
In a second aspect, there is provided a method of manufacturing an airfoil, the method comprising:
forming a wing body, and forming a wing leading edge and a wing trailing edge on two sides of the wing body;
sticking an endowing piece made of a broadband wave-absorbing material on the front edge of the wing;
and adhering a shaping piece made of traveling wave inhibiting material on the trailing edge of the wing.
Optionally, the method further comprises:
and winding glass fiber reinforced plastics on the front edge and the rear edge of the wing adhered with the shape endowing pieces and the outer surface of the wing body.
The wing designed by the invention is respectively applied with the broadband wave-absorbing material and the traveling wave inhibiting material at the front edge and the rear edge, has obvious attenuation effect on electromagnetic waves, can effectively reduce the intensity of a scattering source when applied to an aircraft, and improves the low detectability of the aircraft.
Drawings
FIG. 1 is a schematic view of a wing structure provided in an embodiment of the present invention;
FIG. 2 is a schematic diagram of wave-absorbing properties of a broadband wave-absorbing material provided by an embodiment of the invention;
fig. 3 is a schematic diagram of a traveling wave attenuation characteristic of a traveling wave suppression material according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of low detectable low frequency performance of an airfoil according to an embodiment of the invention;
fig. 5 is a schematic diagram of low detectable high frequency performance of an airfoil according to an embodiment of the invention.
Detailed Description
The invention relates to an aircraft wing and can meet the overall and aerodynamic requirements of an aircraft.
The invention provides an airfoil, as shown in fig. 1, comprising: the wing comprises a wing body 2, a wing front edge 1 and a wing rear edge 3, wherein the wing front edge 1 and the wing rear edge 3 are respectively positioned at two sides of the wing body 2,
wherein, the leading edge of the wing is provided with an endowing piece made of broadband wave-absorbing material; optionally, the broadband wave-absorbing material is a carbonyl iron type wave-absorbing agent composite resin and rubber composite material. The material has the characteristics of high magnetic loss performance, wide wave-absorbing frequency band and strong electromagnetic wave absorption capacity. Optionally, the thickness of the wing leading edge is 1.5-2.5 mm. Fig. 2 is a schematic diagram of the wave-absorbing performance of the broadband wave-absorbing material, and in fig. 2, the abscissa is frequency and the ordinate is reflectivity.
The trailing edge of the wing is provided with a shaped piece made of traveling wave inhibiting material. Optionally, the traveling wave suppression material is carbonyl iron type wave absorber composite resin. The broadband wave-absorbing material is different from a broadband wave-absorbing material in that the thickness of the material is small, and optionally, the thickness of the trailing edge of the wing is 0.3-0.6 mm. The material has the characteristics that the mirror reflection wave-absorbing performance is not outstanding, but the surface traveling wave can be effectively inhibited. Fig. 3 is a schematic diagram of the traveling wave attenuation characteristic of the traveling wave inhibiting material, and in fig. 3, the abscissa is the azimuth angle and the ordinate is the reflectivity.
Optionally, the wing body is made of a carbon fibre material.
Optionally, the leading and trailing edges of the wing are provided with shaped pieces, and the outer surface of the wing body is wrapped with glass fiber reinforced plastic for fixing and protecting the outer surface.
In the embodiment, the front edge is a wing strong scattering area, a broadband wave-absorbing material is adopted to reduce a radar scattering cross section, the rear edge mainly influences wing traveling wave scattering, a traveling wave inhibiting material is adopted to reduce the radar scattering cross section, and the rest of the wing is made of a carbon fiber material.
The invention also provides a processing method of the wing with high radar stealth performance, which comprises the following steps:
1) forming a wing body, and forming a wing leading edge and a wing trailing edge on two sides of the wing body;
2) sticking an endowing piece made of a broadband wave-absorbing material on the front edge of the wing;
3) and adhering a shaping piece made of traveling wave inhibiting material on the trailing edge of the wing.
4) And winding glass fiber reinforced plastics on the front edge and the rear edge of the wing adhered with the shape endowing pieces and the outer surface of the wing body.
5) And finally spraying a primer and a finish paint, thereby finishing the processing of the wing with high radar stealth performance.
Referring to fig. 4 and 5, the scattering source of the wing mainly includes the mirror reflection of the leading edge and the traveling wave scattering accumulated by the wing surface, the azimuth angle is 15 degrees, the electromagnetic wave is normally incident to the leading edge of the wing, the azimuth angle is-20 degrees to 0 degrees, the wing traveling wave scattering azimuth angle domain is formed, the radar scattering cross section curves of the wave absorbing wing and the metal material wing with the comparison structure are shown in fig. 4 and 5, the radar scattering cross section peaks of the leading edge of the loaded material wing are respectively reduced by 8.4dB (from 0.9dB to-7.5 dB) and 7.7dB (from 4.5dB to-3.2 dB) compared with the radar scattering cross section curve of the unloaded material wing; the RCS value of the wing loaded with the material in the traveling wave scattering angular region is reduced by about 5-15 dB compared with the state of the wing unloaded with the material, which shows that the structural wave-absorbing material has good effects on reducing the RCS of the wing leading edge mirror reflection and traveling wave scattering at low and high frequencies.
The wing designed by the invention is respectively applied with the broadband wave-absorbing material and the traveling wave inhibiting material at the front edge and the rear edge, has obvious attenuation effect on electromagnetic waves, can effectively reduce the intensity of a scattering source when applied to an aircraft, and improves the low detectability of the aircraft.
Claims (10)
1. An airfoil, comprising: the wing body, the wing leading edge and the wing trailing edge are respectively positioned at two sides of the wing body,
wherein, the leading edge of the wing is provided with an endowing piece made of broadband wave-absorbing material;
the trailing edge of the wing is provided with a shaped piece made of traveling wave inhibiting material.
2. The wing as claimed in claim 1,
the broadband wave-absorbing material is a carbonyl iron type wave-absorbing agent composite resin and rubber composite material.
3. The wing as claimed in claim 1,
the traveling wave inhibiting material is carbonyl iron type wave absorbing agent composite resin.
4. The wing as claimed in claim 1,
the thickness of the trailing edge is less than the leading edge.
5. The wing as claimed in claim 4,
the thickness of the wing leading edge is 1.5-2.5 mm.
6. The wing as claimed in claim 4,
the thickness of the trailing edge of the wing is 0.3-0.6 mm.
7. The wing as claimed in claim 1,
the wing body is made of carbon fiber material.
8. The wing as claimed in claim 1,
the wing leading edge and the wing trailing edge which are provided with the endowing pieces and the outer surface of the wing body are wound with glass fiber reinforced plastics.
9. A method of manufacturing an airfoil, the method comprising:
forming a wing body, and forming a wing leading edge and a wing trailing edge on two sides of the wing body;
sticking an endowing piece made of a broadband wave-absorbing material on the front edge of the wing;
and adhering a shaping piece made of traveling wave inhibiting material on the trailing edge of the wing.
10. The method of claim 9, further comprising:
and winding glass fiber reinforced plastics on the front edge and the rear edge of the wing adhered with the shape endowing pieces and the outer surface of the wing body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111536815.8A CN114194374B (en) | 2021-12-15 | 2021-12-15 | Wing and processing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111536815.8A CN114194374B (en) | 2021-12-15 | 2021-12-15 | Wing and processing method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114194374A true CN114194374A (en) | 2022-03-18 |
| CN114194374B CN114194374B (en) | 2024-04-02 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111536815.8A Active CN114194374B (en) | 2021-12-15 | 2021-12-15 | Wing and processing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114194374B (en) |
Citations (5)
| 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 |
| US20180127599A1 (en) * | 2014-11-12 | 2018-05-10 | Robert Lee Wentz | Method of passive reduction of radar cross-section using radar absorbing materials on composite structures |
| CN108100225A (en) * | 2017-11-20 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of tapered wing |
| CN111532417A (en) * | 2020-05-13 | 2020-08-14 | 北京机电工程研究所 | Aircraft radar stealth airfoil and preparation method thereof |
| CN112213337A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业股份有限公司 | Method for rapidly verifying performance of missile traveling wave restraining structure stealth material |
-
2021
- 2021-12-15 CN CN202111536815.8A patent/CN114194374B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180127599A1 (en) * | 2014-11-12 | 2018-05-10 | Robert Lee Wentz | Method of passive reduction of radar cross-section using radar absorbing materials on composite structures |
| 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 |
| CN108100225A (en) * | 2017-11-20 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of tapered wing |
| CN111532417A (en) * | 2020-05-13 | 2020-08-14 | 北京机电工程研究所 | Aircraft radar stealth airfoil and preparation method thereof |
| CN112213337A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业股份有限公司 | Method for rapidly verifying performance of missile traveling wave restraining structure stealth material |
Non-Patent Citations (2)
| Title |
|---|
| 孟新强等: ""RAM 技术在隐身飞行器薄型翼设计中的应用"", 《兵器材料科学与工程》, vol. 23, no. 4, pages 16 * |
| 马东立、武哲等: ""机翼涂敷吸波材料减缩雷达散射截面的研究"", 《航空学报》, vol. 21, no. 3, pages 241 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114194374B (en) | 2024-04-02 |
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