CN108100225A - A kind of tapered wing - Google Patents
A kind of tapered wing Download PDFInfo
- Publication number
- CN108100225A CN108100225A CN201711158300.2A CN201711158300A CN108100225A CN 108100225 A CN108100225 A CN 108100225A CN 201711158300 A CN201711158300 A CN 201711158300A CN 108100225 A CN108100225 A CN 108100225A
- Authority
- CN
- China
- Prior art keywords
- wing
- tapered
- tapered wing
- leading edge
- trailing edge
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/10—Constructional aspects of UAVs for stealth, e.g. reduction of cross-section detectable by radars
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Aerials With Secondary Devices (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The present invention relates to field of airplane structure, more particularly to a kind of tapered wing.By the way that tapered wing leading edge (3) is designed as wedge shape, the mirror-reflection of tapered wing leading edge (3) is reduced, strong scattering source is become into weak scattering source；By the way that tapered wing trailing edge (4) shape is designed as zigzag, make the azimuth that trailing edge (4) generates edge diffraction identical with the azimuth of the leading edge of a wing (3) generation mirror-reflection, by the main energetic control of the radar return of aircraft in a small number of very narrow orientation, RCS wave crest quantity is reduced；Further, absorbent structure is set between (4) two sawtooth of trailing edge, by loss of the electromagnetic energy of incidence wave through generated various weakness and magnetic hysteresis in absorbing material, is converted into heat and loses.The tapered wing of the present invention improves the Stealth Fighter of wing in terms of shape is stealthy with Material-stealth two.
Description
Technical field
The present invention relates to field of airplane structure, more particularly to a kind of tapered wing.
Background technology
It is increasingly perfect for the Detection Techniques of aircraft due to the development of military needs and modern science and technology, it is right
Viability of the aircraft in war constitutes serious threat, and Stealth Fighter has become the one of military spacecraft survival ability
A important indicator, and be an important criterion for weighing following military spacecraft advance.
As a kind of important component of aircraft, wing is also a kind of important electromagnetic scattering source.Under radar wave irradiation,
The leading edge of a wing can generate mirror-reflection.For tapered wing, trailing edge can also generate edge diffraction in different orientations, this is just
Larger challenge is brought to the stealth for reducing wing.
The content of the invention
The object of the present invention is to provide a kind of electromagnetic scattering energy that aircraft wing can be greatly reduced, and improve flight
The tapered wing designing scheme of the Stealth Fighter of device.
The technical scheme is that：
A kind of tapered wing, the projection line of the wing tip end face of tapered wing in the horizontal plane is with wing root end face in the level
Projection line on face is parallel, which is characterized in that the leading edge of the tapered wing aerofoil profile is in wedge shape, and the cusp of the wedge shape is
The stationary point of the aerofoil profile, the upper vertex of the wedge shape are the peak of the aerofoil profile, and the lower vertex of the wedge shape is described
The minimum point of aerofoil profile.
Optionally, the trailing edge of the tapered wing is serrated, and including multiple sawtooth, each sawtooth is in the horizontal plane
Including two sides, wherein projection line of a line with the wing tip end face of the tapered wing on the horizontal plane is parallel, another
Projection line of the side with the tapered wing leading edge on the horizontal plane is parallel.
Optionally, absorbent structure, multiple sawtooth and the suction ripple are provided between two adjacent sawtooth
Structure forms the trailing edge of the complete tapered wing.
Invention effect：
The tapered wing of the present invention reduces the mirror-reflection of the leading edge of a wing, so as to be greatly reduced from the angle of configuration design
The electromagnetic scattering energy of aircraft wing improves the Stealth Fighter of aircraft.
Description of the drawings
Fig. 1 is the structure diagram of tapered wing of the present invention；
Fig. 2 is the schematic cross-section of tapered wing of the present invention.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown is for only for ease of the description present invention and simplifies description rather than instruction or imply signified dress
It puts or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
1 and 2 pair of tapered wing of the invention is described in further details below in conjunction with the accompanying drawings.
The present invention provides a kind of tapered wing, the projection line and the wing of 1 end face of wing tip of the tapered wing in the horizontal plane
The projection line of 2 end face of root in the horizontal plane is parallel.
Specifically, the leading edge 3 of tapered wing aerofoil profile is in wedge shape, and the cusp of wedge shape is the stationary point of aerofoil profile, wedge shape
Upper vertex is the peak of aerofoil profile, and the lower vertex of wedge shape is the minimum point of aerofoil profile.In the present embodiment, it is preferred to use wedge shape
The leading edge of a wing 3 greatly reduces the mirror-reflection of the leading edge of a wing 1.
The trailing edge 4 of tapered wing is serrated, and including multiple sawtooth, each sawtooth includes two sides in the horizontal plane,
The projection line of 1 end face of wing tip of middle a line and tapered wing in the horizontal plane is parallel, and another a line exists with tapered wing leading edge 3
Projection line on horizontal plane is parallel.In the present embodiment, it is preferred to use the design of this 4 shape of trailing edge produces trailing edge 4
The azimuth that the azimuth of raw edge diffraction generates mirror-reflection with the leading edge of a wing 3 is identical, by the master of the radar return of aircraft
Energy hole is wanted to make the echo-signal between two wave crests very weak in a small number of very narrow orientation.Additionally, it is preferred that adjacent
Absorbing material is filled between two sawtooth, further reduces aircraft RCS, multiple sawtooth and absorbent structure structure by Material-stealth
Into the trailing edge 4 of complete tapered wing.
The leading edge 3 and trailing edge 4 of aircraft wing are main scattering sources, and the present invention enhances aircraft in terms of two
Stealth Fighter.In terms of Stealthy Technology：First, by the change to 3 shape of tapered wing leading edge, i.e., conventional cylinder shape
The leading edge of a wing 3 be designed to wedge shape, reduce the mirror-reflection of tapered wing leading edge 3, strong scattering source become into weak scattering source；
Secondly, by the design of 4 shape of tapered wing trailing edge, i.e., zigzag a line and the projection of 1 end face of wing tip in the horizontal plane
Parallel and another projection line of a line with the leading edge of a wing 3 in the horizontal plane of line is parallel, and trailing edge 4 is made to generate edge diffraction
Azimuth and the leading edge of a wing 3 generate mirror-reflection azimuth it is identical, the main energetic of the radar return of aircraft is controlled
In a small number of very narrow orientation, make the echo-signal between two wave crests very weak.Material-stealth technical aspect, by wing
Absorbent structure is set between 4 two sawtooth of trailing edge, the electromagnetic energy of incidence wave is passed through generated various weak in absorbing material
The loss of point and magnetic hysteresis, is converted into heat and loses.Two kinds of stealth technologies are complementary to one another, and ensure that higher stealthy of tapered wing
Performance.
The tapered wing of the present invention not only reduces the mirror-reflection of the leading edge of a wing 3 from the angle of configuration design, while to machine
Wing trailing edge 4 carries out configuration design so that it generates the orientation that the azimuth of edge diffraction generates mirror-reflection with the leading edge of a wing 3
Angle is identical, and RCS wave crest quantity is reduced with this.The tapered wing of the present invention carries in terms of shape is stealthy with Material-stealth two
The Stealth Fighter of high wing is greatly reduced the electromagnetic scattering energy of aircraft wing, ensure that preferable stealth effect, finally carry
The high Stealth Fighter of aircraft.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all should by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (3)
1. a kind of tapered wing, the projection line of wing tip (1) end face of tapered wing in the horizontal plane is with wing root (2) end face described
Projection line on horizontal plane is parallel, which is characterized in that the leading edge (3) of the tapered wing aerofoil profile is in wedge shape, the wedge shape
Cusp be the aerofoil profile stationary point, the upper vertex of the wedge shape is the peak of the aerofoil profile, the lower top of the wedge shape
Point is the minimum point of the aerofoil profile.
2. tapered wing according to claim 1, which is characterized in that the trailing edge (4) of the tapered wing is serrated, bag
Multiple sawtooth are included, each sawtooth includes two sides, wherein a line and the wing tip (1) of the tapered wing in the horizontal plane
Projection line of the end face on the horizontal plane is parallel, and another a line is with the tapered wing leading edge (3) on the horizontal plane
Projection line is parallel.
3. tapered wing according to claim 2, which is characterized in that be provided with suction between two adjacent sawtooth
Wave structure, multiple sawtooth and the absorbent structure form the trailing edge of the complete tapered wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711158300.2A CN108100225B (en) | 2017-11-20 | 2017-11-20 | Trapezoidal wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711158300.2A CN108100225B (en) | 2017-11-20 | 2017-11-20 | Trapezoidal wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108100225A true CN108100225A (en) | 2018-06-01 |
| CN108100225B CN108100225B (en) | 2021-10-22 |
Family
ID=62206370
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711158300.2A Active CN108100225B (en) | 2017-11-20 | 2017-11-20 | Trapezoidal wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108100225B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112597589A (en) * | 2020-12-24 | 2021-04-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Wing design method |
| CN112748414A (en) * | 2020-12-24 | 2021-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Wave absorbing screen for target RCS measurement |
| CN114194374A (en) * | 2021-12-15 | 2022-03-18 | 江西洪都航空工业股份有限公司 | Wing and machining method thereof |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112597589A (en) * | 2020-12-24 | 2021-04-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Wing design method |
| CN112748414A (en) * | 2020-12-24 | 2021-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Wave absorbing screen for target RCS measurement |
| CN112597589B (en) * | 2020-12-24 | 2022-09-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Wing design method |
| CN112748414B (en) * | 2020-12-24 | 2024-02-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Wave absorbing screen for measuring target RCS |
| CN114194374A (en) * | 2021-12-15 | 2022-03-18 | 江西洪都航空工业股份有限公司 | Wing and machining method thereof |
| CN114194374B (en) * | 2021-12-15 | 2024-04-02 | 江西洪都航空工业股份有限公司 | Wing and processing method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108100225B (en) | 2021-10-22 |
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