CN104590544A - Aerofoil structure of fixed-wing unmanned aerial vehicle - Google Patents
Aerofoil structure of fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN104590544A CN104590544A CN201510043458.XA CN201510043458A CN104590544A CN 104590544 A CN104590544 A CN 104590544A CN 201510043458 A CN201510043458 A CN 201510043458A CN 104590544 A CN104590544 A CN 104590544A
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Abstract
The invention discloses an aerofoil structure of a fixed-wing unmanned aerial vehicle. The aerofoil structure of a fixed-wing unmanned aerial vehicle comprises an aerofoil body. According to the invention, the upper surface of the aerofoil body is a convex surface curved upwards and the lower surface of the aerofoil body is a convex surface curved downward; the aerofoil body is formed by fixedly connecting a front aerofoil section located beside the wing root of the aerofoil body and a rear aerofoil section located beside the wing tail of the aerofoil body; vertical projection of the front aerofoil is rectangular while vertical projection of the rear aerofoil is trapezoidal; the angle range of a sweepback angle on a front edge of the rear aerofoil section is 7-10 degree and the angle range of a dihedral angle on the rear aerofoil section is 2-5 degrees. An unmanned aerial vehicle having the aerofoil structure of a fixed-wing unmanned aerial vehicle is characterized by being stable in flying and low in power consumption.
Description
Technical field
The present invention relates to a kind of aircraft field, more particularly, particularly relate to a kind of wing structure of fixed-wing unmanned vehicle.
Background technology
Fixed-wing unmanned vehicle is a kind of based on radio telecommand or the not manned craft by self programming control, and now, unmanned vehicle develops rapidly as a kind of new concept aircraft.Fixed-wing unmanned vehicle is by carrying multiple sensors, and can realize image real-time Transmission, high-risk areas detecting function, be the important supplement of satellite remote sensing and traditional remote sensing.Tradition adopts the fixed-wing unmanned vehicle of biconvex profile wing structure, and its wing outwards stretches in the horizontal direction, and flight attitude is unstable, and captured photographic quality is poor.Therefore, how to make fixed-wing unmanned vehicle flight attitude photographic quality that is more stable, shooting better become the development new direction of fixed-wing unmanned vehicle.
Summary of the invention
The object of the present invention is to provide a kind of wing structure of fixed-wing unmanned vehicle, use the unmanned vehicle of this kind of wing structure to have flight stability, the feature that power is few.
The technical solution used in the present invention is as follows:
A kind of wing structure of fixed-wing unmanned vehicle, comprise wing-body, the upper surface of described wing-body is projection curved surface, the lower surface of wing-body is lower convexity curved surface, described wing-body is formed by fixedly connecting with the back segment wing being positioned at wing-body wing tail side by the leading portion wing being positioned at wing-body wing root side, the vertical projection of described leading portion wing is rectangle, the vertical projection of described back segment wing is trapezoidal, the leading edge sweep angular range of back segment wing is 7 ~ 10 degree, and the dihedral angle angular range of back segment wing is 2 ~ 5 degree.
Further, the leading edge sweep angle of described back segment wing is 8.6 degree.
Further, the dihedral angle angle of described back segment wing is 2.5 degree.
Further, the upper surface of described wing-body is from wing-body leading edge projection curved surface, and the lower surface of wing-body is from wing-body leading edge lower convexity curved surface.
Further, the length ratio scope of described leading portion wing and back segment wing is 1:0.9 ~ 1.1.
Further, the projection height of described wing-body and lower convexity height ratio scope are 2 ~ 4:1.
Further, the projection height of described wing-body and lower convexity height ratio scope are 2.97:1.
Further, the material of described wing-body is carbon cloth, Ba Ersha cork wood and aviation laminate.
Compared with prior art, the beneficial effect that the present invention has is:
The wing structure of a kind of fixed-wing unmanned vehicle of the present invention, comprise wing-body, the upper surface of wing-body is projection curved surface, lower surface is lower convexity curved surface, wing-body is formed by fixedly connecting with the back segment wing being positioned at wing tail side by the leading portion wing being positioned at wing root side, and the vertical projection of leading portion wing is rectangle, and the vertical projection of back segment wing is trapezoidal, the leading edge sweep angular range of back segment wing is 7 ~ 10 degree, and the dihedral angle angular range of back segment wing is 2 ~ 5 degree.By the sweepback of the back segment leading edge of a wing is anti-upper, better alleviate the stressed of the windward side of wing, avoid breakking away, unmanned vehicle is flown more stable, the unmanned vehicle of this wing structure can also glide, and decreases part flying power, and mission time is extended.
Accompanying drawing explanation
Fig. 1 is structural representation Fig. 1 of the present invention;
Fig. 2 is structural representation Fig. 2 of the present invention;
Fig. 3 is wing profile figure of the present invention.
Detailed description of the invention
Below in conjunction with detailed description of the invention, technical scheme of the present invention is described in further detail, but does not form any limitation of the invention.
With reference to shown in Fig. 1 ~ 3, the wing structure of a kind of fixed-wing unmanned vehicle of the present invention, comprise wing-body 1, the upper surface of wing-body 1 is projection curved surface 5, the lower surface of wing-body 1 is lower convexity curved surface 6, wherein, described wing-body 1 is formed by fixedly connecting with the back segment wing 3 being positioned at wing-body 1 wing tail side by the leading portion wing 2 being positioned at wing-body 1 wing root side, the vertical projection of leading portion wing 2 is rectangle, the vertical projection of back segment wing 3 is trapezoidal, the leading edge sweep angular range of back segment wing 3 is 7 ~ 10 degree, the dihedral angle angular range of back segment wing 3 is 2 ~ 5 degree.By by back segment wing 3 leading-edge sweep, alleviate the forward space resistance of wing, and by anti-on back segment wing 3, if aircraft is when flying, the wind area that the dihedral angle can make aircraft meet to side, sideslip direction wing is more much bigger than opposite side wing area, make aircraft produce the strength of oppositely breakking away, thus reach the effect revised rapidly and break away, avoid breakking away, unmanned vehicle flight is more stable, therefore, when utilizing this kind of unmanned vehicle execution to take photo by plane, captured picture effect is better.The wing structure of unmanned vehicle of the present invention can also make aircraft glide, and decreases part flying power, extends mission time.The wing structure of this unmanned vehicle of the present invention can also bear space, larger task storehouse to place more capture apparatus, thus meets different shooting demands.
The leading edge sweep angle of back segment wing 3 is 8.6 degree, utilizes the sweepback angle of back segment wing 3, can reduce wing-body 1 forward space resistance when flying.
The dihedral angle angle of back segment wing 3 is 2.5 degree, the best results that back segment wing 3 utilizes the dihedral angle of this angle value to make the correction of wing-body 1 to break away, and stress balance is best.
The upper surface of wing-body 1 is from wing-body 1 leading edge projection curved surface 5, and the lower surface of wing-body 1 is from wing-body 1 leading edge lower convexity curved surface 6.Projection curved surface 5 and the lower convexity curved surface 6 of this spline structure, can make the static pressure of lower convexity curved surface 6 be greater than projection curved surface 5 static pressure, makes aircraft better rise.
Leading portion wing 2 is 1:0.9 ~ 1.1 with the length ratio scope of back segment wing 3, and the length ratio of leading portion wing 2 and back segment wing 3 is within the scope of this, and stressed effect is better.Wherein, leading portion wing 2 is respectively 470mm and 450mm with the length of back segment wing 3, and when leading portion wing 2 is 1:0.957 with the length ratio of back segment wing 3, stressed effect is best.
Projection height and the lower convexity height ratio scope of wing-body 1 are 2 ~ 4:1, the projection height of wing-body 1 and lower convexity height ratio are within the scope of this, make the static pressure of lower convexity curved surface 6 and projection curved surface 5 static pressure proportion relatively good, make the lift of aircraft better.Wherein, projection height is 23.18mm, and lower convexity height is 7.79mm, and projection height and lower convexity height ratio scope are 2.97:1, and static pressure and projection curved surface 5 static pressure proportion of the lower convexity curved surface 6 of this ratio are best, make the lift of aircraft best.
The material of wing-body 1 is carbon cloth, Ba Ersha cork wood and aviation laminate, and the wing quality utilizing these materials to do is lighter and firm in structure, and flight effect is good.
The foregoing is only preferred embodiment of the present invention, all do within the scope of the spirit and principles in the present invention any amendment, equivalent to replace and improvement etc., all should be included within protection scope of the present invention.
Claims (8)
1. the wing structure of a fixed-wing unmanned vehicle, comprise wing-body (1), the upper surface of described wing-body (1) is projection curved surface (5), the lower surface of wing-body (1) is lower convexity curved surface (6), it is characterized in that, described wing-body (1) is formed by fixedly connecting by the leading portion wing (2) being positioned at wing-body (1) wing root side and the back segment wing (3) that is positioned at wing-body (1) wing tail side, the vertical projection of described leading portion wing (2) is rectangle, the vertical projection of described back segment wing (3) is trapezoidal, the leading edge sweep angular range of back segment wing (3) is 7 ~ 10 degree, the dihedral angle angular range of back segment wing (3) is 2 ~ 5 degree.
2. the wing structure of a kind of fixed-wing unmanned vehicle according to claim 1, is characterized in that, the leading edge sweep angle of described back segment wing (3) is 8.6 degree.
3. the wing structure of a kind of fixed-wing unmanned vehicle according to claim 1, is characterized in that, the dihedral angle angle of described back segment wing (3) is 2.5 degree.
4. the wing structure of a kind of fixed-wing unmanned vehicle according to claim 1, it is characterized in that, the upper surface of described wing-body (1) is from wing-body (1) leading edge projection curved surface (5), and the lower surface of wing-body (1) is from wing-body (1) leading edge lower convexity curved surface (6).
5. the wing structure of a kind of fixed-wing unmanned vehicle according to claim 1, is characterized in that, described leading portion wing (2) is 1:0.9 ~ 1.1 with the length ratio scope of back segment wing (3).
6. the wing structure of a kind of fixed-wing unmanned vehicle according to claim 1, is characterized in that, projection height and the lower convexity height ratio scope of described wing-body (1) are 2 ~ 4:1.
7. the wing structure of a kind of fixed-wing unmanned vehicle according to claim 1, is characterized in that, projection height and the lower convexity height ratio scope of described wing-body (1) are 2.97:1.
8. the wing structure of a kind of fixed-wing unmanned vehicle according to claim 1, is characterized in that, the material of described wing-body (1) is carbon cloth, Ba Ersha cork wood and aviation laminate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510043458.XA CN104590544A (en) | 2015-01-28 | 2015-01-28 | Aerofoil structure of fixed-wing unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510043458.XA CN104590544A (en) | 2015-01-28 | 2015-01-28 | Aerofoil structure of fixed-wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN104590544A true CN104590544A (en) | 2015-05-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510043458.XA Pending CN104590544A (en) | 2015-01-28 | 2015-01-28 | Aerofoil structure of fixed-wing unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043666A (en) * | 2016-08-24 | 2016-10-26 | 广州朱雀航空科技有限公司 | Wing of unmanned plane |
Citations (6)
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|---|---|---|---|---|
| CN2835081Y (en) * | 2005-10-10 | 2006-11-08 | 武川 | Aircraft wing structure |
| CN200939356Y (en) * | 2006-08-22 | 2007-08-29 | 青岛天骄无人机遥感技术有限公司 | Small remote monitoring pilotless plane |
| CN101254753A (en) * | 2007-02-28 | 2008-09-03 | 西北工业大学 | Solar pilotless plane |
| CN102774490A (en) * | 2012-04-10 | 2012-11-14 | 北京航空航天大学 | Novel long-endurance solar unmanned aerial vehicle |
| US20130264429A1 (en) * | 2012-01-17 | 2013-10-10 | Pavel Miodushevsky | Convertible airplane |
| CN204433030U (en) * | 2015-01-28 | 2015-07-01 | 梧州晟裕科技有限公司 | The wing structure of fixed-wing unmanned vehicle |
-
2015
- 2015-01-28 CN CN201510043458.XA patent/CN104590544A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2835081Y (en) * | 2005-10-10 | 2006-11-08 | 武川 | Aircraft wing structure |
| CN200939356Y (en) * | 2006-08-22 | 2007-08-29 | 青岛天骄无人机遥感技术有限公司 | Small remote monitoring pilotless plane |
| CN101254753A (en) * | 2007-02-28 | 2008-09-03 | 西北工业大学 | Solar pilotless plane |
| US20130264429A1 (en) * | 2012-01-17 | 2013-10-10 | Pavel Miodushevsky | Convertible airplane |
| CN102774490A (en) * | 2012-04-10 | 2012-11-14 | 北京航空航天大学 | Novel long-endurance solar unmanned aerial vehicle |
| CN204433030U (en) * | 2015-01-28 | 2015-07-01 | 梧州晟裕科技有限公司 | The wing structure of fixed-wing unmanned vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043666A (en) * | 2016-08-24 | 2016-10-26 | 广州朱雀航空科技有限公司 | Wing of unmanned plane |
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Application publication date: 20150506 |