CN102730183A - Novel solar airplane - Google Patents
Novel solar airplane Download PDFInfo
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- CN102730183A CN102730183A CN2012102295427A CN201210229542A CN102730183A CN 102730183 A CN102730183 A CN 102730183A CN 2012102295427 A CN2012102295427 A CN 2012102295427A CN 201210229542 A CN201210229542 A CN 201210229542A CN 102730183 A CN102730183 A CN 102730183A
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Abstract
The invention relates to a solar airplane which has a high lift-drag ratio and low energy consumption. In order to improve the lift-drag ratio, positive camber wings (9) with a large lift coefficient are adopted, a gravity center (12) of the positive camber wing is arranged right below a wing focus (13) so as to generate a large lift-drag ratio and a large rising moment, and meanwhile, the whole airplane has static stability; the lift-drag ratio of the airplane can be improved, and the whole airplane has static stability; the areas of the wings (9) are large enough, so more solar cell panels are suitable to be mounted, and enough energy is guaranteed to be stored for flights at night and on cloudy days; and meanwhile, in order to improve the structural strength of the airplane and lighten the structural weight, a structure of double wing surfaces (9) and (11) and double supporting wings (5) and (14) is adopted.
Description
Technical field:
The present invention relates to a kind of solar powered aircraft of high lift-drag ratio, belong to fixed wing aircraft technical field in the aviation aircraft
Technical background
Solar power has broad application prospects as a kind of renewable and clean energy resource.As the aircraft power source, is the research target that the mankind have directivity and frontier nature with solar power.
In the solar powered aircraft design, a technical difficult points that runs into is to increase the 1ift-drag ratio characteristic that how significantly to improve aircraft under the little situation at structural weight.Solar powered aircraft has adopted tradition or all-wing aircraft aerodynamic arrangement mostly at present; Realize the trim of wing zero lift moment by modes such as horizontal tail, canard or S aerofoil profiles; This has just brought lift and drag losses, has reduced full machine 1ift-drag ratio, can not give full play to positive camber aerofoil profile high lift-drag ratio characteristic.
Summary of the invention
The present invention relates to have high lift-drag ratio, the solar powered aircraft of low energy consumption.In order to improve 1ift-drag ratio, this aircraft adopts the big positive camber wing of lift coefficient, and center of gravity is located under being configured in the wing focus; To produce big 1ift-drag ratio and nose-up pitching moment; Make full facility that static stability is arranged simultaneously, can improve the 1ift-drag ratio of aircraft, can make full facility that static stability is arranged again.Wing area is enough big, is suitable for installing more solar panel, guarantees to store the enough energy and supplies night and cloudy day flight to use.In order to improve aircaft configuration intensity, alleviate structural weight simultaneously, adopt double-vane face double bracing wing structure.
According to an aspect of the present invention, a kind of solar powered aircraft is provided, has it is characterized in that comprising:
Fuselage;
Be fixed in the lower aerofoil on the fuselage;
The positive camber wing, it is connected with said lower aerofoil through a pair of braced wing;
Said a pair of braced wing.
Description of drawings
Fig. 1 illustrates to have shown the single solar powered aircraft that can fly round the clock according to an embodiment of the invention.
The specific embodiment
The present invention relates to have high lift-drag ratio, the solar powered aircraft of low energy consumption.In order to improve 1ift-drag ratio, this aircraft adopts the big positive camber wing (9) of lift coefficient, and center of gravity (12) is located under being configured in wing focus (13), thereby produces big 1ift-drag ratio and nose-up pitching moment, makes full facility that static stability is arranged simultaneously.Can improve the 1ift-drag ratio of aircraft, can make full facility that static stability is arranged again.The area of wing (9) is enough big, is suitable for installing more solar panel, guarantees to store the enough energy and supplies night and cloudy day flight to use.In order to improve aircaft configuration intensity, alleviate structural weight simultaneously, adopt double-vane face (9,11), the double bracing wing (5,14) structure.
In order to have the high lift-drag ratio ability, fully excavate the boat performance of a specified duration of solar powered aircraft, the single solar powered aircraft that flies round the clock according to an embodiment of the invention comprises following characteristic: high aspect ratio, straight wing, the no dihedral angle, bicycle gear.Center of gravity is located under being disposed at the wing focus.
Particularly, the single solar powered aircraft that flies round the clock according to an embodiment of the invention comprises following characteristic:
-positive camber wing (9)
In order to make aircraft have big 1ift-drag ratio, the single solar powered aircraft that can fly round the clock according to an embodiment of the invention adopts the positive camber wing.The center of gravity of all-wing aircraft (12) is configured under the full mechanical coke point (13), and producing nose-up pitching moment, the zero lift moment of trim positive camber wing can improve the 1ift-drag ratio of aircraft, can make full facility that static stability is arranged again.
-trim fuselage
Fuselage (6) is fixed in lower aerofoil (11).Can help like this center of gravity (12) is disposed at full mechanical coke point (13) below, reach the trim of full machine moment, realize high lift-drag ratio.Help strengthening fuselage intensity simultaneously.Driving compartment (10) visual field is good.
-wing braced wing
Support (5,14) through two wings and realize the connection between the upper and lower wing (9,11); When improving full machine structural strength,, make full machine down-shift of working center for the installation of driving engine (3,4) provides support; Reach the trim of full machine moment, realize high lift-drag ratio.Simultaneously, solar panels side inside and outside the support aerofoil can be installed, when the solar light irradiation angle is low, receive more solar energy.
-maneuverability pattern
According to one embodiment of present invention, a pair of spoiler (1,2) is set, as the control in the horizontal course of aircraft at wing (9) two ends.In the control in horizontal course, can strengthen control through the control of two driving engines on the braced wing (3,4) thrust size difference.And vertical pitch control subsystem of aircraft then is through regulating the size of driving engine total thrust, realizing the up-down of aircraft.
Parameter according to a specific embodiment of the present invention comprises:
The long 28m of total weight 540kg upper span
The long 10m of last chord-length 1.4m lower span
Following chord-length 1m goes up the high 9m of bottom wing
Braced wing chord length 0.5m
Sweepback angle χ: consider from the flat performance that flies of low speed, choose straight wing for improving 1ift-drag ratio.
Rudder face: only a pair of spoiler (1,2) is set, as the control in the horizontal course of aircraft at wing.
Driving engine: adopt two solar-electricity power engines, parallel symmetrical placement is in two wing braced wings.Engine thrust increases, and the realization aircraft altitude is climbed; Engine thrust reduces, and realizes that the height of aircraft reduces.Through left and right sides asymmetrical thrust size, strengthen the control in the horizontal course of aircraft simultaneously.
Alighting gear: adopt bicycle gear, bicycle gear (7,8) is installed in this ventral, lower aerofoil bottom.It can be for the aircaft configuration of aircraft broad provides stable support, thereby improves the stationarity of takeoff and landing.
The center of gravity allocation position is apart from wing focal length H: by the zero lift moment decision of selected positive camber wing.As a specific embodiment, the distance of center of gravity (12) is chosen in about 7m place under the focus (13), under trim condition, can give full play to the 1ift-drag ratio advantage of positive camber wing.
One, compared with prior art, advantage that the present invention had and effect
Through the checking of repeatedly taking a flight test that the inventor carries out, show that this solar powered aircraft has the following advantages:
1, the novel layouts method that adopts has realized full machine power and moment trim, has given full play to the high lift-drag ratio characteristic of positive camber aerofoil profile, reduces energy consumption, makes aircraft have better fore-and-aft stability simultaneously.
2, high aspect ratio wing has improved the 1ift-drag ratio of aircraft, can improve the horizontal lateral stability of aircraft simultaneously.Reduce the aircraft induced drag.
3, the supporting construction that is adopted has alleviated the structural weight of high aspect ratio wing greatly.
4, the manipulation mode is simply effective, and energy consumption is low.。
In sum, aircraft according to the present invention is the solar powered aircraft of a excellent combination property, has good 1ift-drag ratio characteristic, and road-holding property is better with stability simultaneously.
Claims (7)
1. solar powered aircraft is characterized in that comprising:
Fuselage (6);
Be fixed in the lower aerofoil (11) on the fuselage (6);
Positive camber wing (9), it is connected with said lower aerofoil (11) through a pair of braced wing (5,14); Said a pair of braced wing (5,14).
2. solar powered aircraft according to claim 1 is characterized in that further comprising:
A pair of driving engine (3,4) is installed in respectively on the said a pair of braced wing (5,14), is used to provide thrust.
3. solar powered aircraft according to claim 1 is characterized in that:
The center of gravity of said solar powered aircraft (12) is configured under the full mechanical coke point (13), to produce nose-up pitching moment, the zero lift moment of trim positive camber wing.
4. according to the described solar powered aircraft of one of claim 1-3, it is characterized in that further comprising:
Be installed in the bicycle gear (7,8) of fuselage (6) bottom and lower aerofoil (11) bottom, the aircaft configuration that is used to said solar powered aircraft provides stable support, thereby improves the stationarity of takeoff and landing.
5. according to the described solar powered aircraft of one of claim 1-3, it is characterized in that further comprising:
Be separately positioned on a pair of spoiler (1,2) at the two ends of said positive camber wing (9), be used for the control in the horizontal course of aircraft.
6. according to the described solar powered aircraft of one of claim 1-3, it is characterized in that:
Thrust through controlling said a pair of driving engine (3,4) is poor, strengthens the control in horizontal course.
7. solar powered aircraft according to claim 6 is characterized in that:
Through regulating driving engine total thrust size, control vertical pitching of aircraft, realize the up-down of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210229542.7A CN102730183B (en) | 2012-07-03 | 2012-07-03 | Novel solar airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210229542.7A CN102730183B (en) | 2012-07-03 | 2012-07-03 | Novel solar airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102730183A true CN102730183A (en) | 2012-10-17 |
| CN102730183B CN102730183B (en) | 2015-01-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210229542.7A Expired - Fee Related CN102730183B (en) | 2012-07-03 | 2012-07-03 | Novel solar airplane |
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| CN (1) | CN102730183B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102910292A (en) * | 2012-10-31 | 2013-02-06 | 无锡同春新能源科技有限公司 | Bionic unmanned scout for killing mosquitos |
| CN103612768A (en) * | 2013-11-29 | 2014-03-05 | 无锡同春新能源科技有限公司 | Solar unmanned aerial vehicle for sowing chemical weeding fine particles at low altitude above rice field |
| CN103803056A (en) * | 2013-10-25 | 2014-05-21 | 苏州艾锐泰克无人飞行器科技有限公司 | Interceptor arranged on top of fuselage of unmanned aerial vehicle (UAV) |
| CN103803057A (en) * | 2013-12-20 | 2014-05-21 | 中国航天空气动力技术研究院 | Tandem-wing solar unmanned plane pneumatic configuration structure |
| CN104085527A (en) * | 2014-07-09 | 2014-10-08 | 李庆宏 | Cuboid-shaped aircraft with upper support large flat plate |
| CN104176232A (en) * | 2014-08-18 | 2014-12-03 | 张文艳 | Three-wing glider |
| CN105836110A (en) * | 2016-04-11 | 2016-08-10 | 西北工业大学 | An improved taking-off and landing device used for a small unmanned aerial vehicle |
| CN106314767A (en) * | 2016-10-20 | 2017-01-11 | 中国航天空气动力技术研究院 | Lightweight undercarriage for solar powered unmanned air vehicle |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
| TWI763447B (en) * | 2021-04-20 | 2022-05-01 | 林瑤章 | Flying device with double wings |
Citations (5)
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| US3640489A (en) * | 1968-07-26 | 1972-02-08 | Karl Jaeger | Vertical takeoff and landing aircraft |
| US4568043A (en) * | 1983-10-21 | 1986-02-04 | Schmittle Hugh J | Ultra-light aircraft with freely rotating rigid wing |
| US5054721A (en) * | 1989-03-22 | 1991-10-08 | Translab, Inc. | Vertical takeoff aircraft |
| CN2506536Y (en) * | 2001-11-16 | 2002-08-21 | 珠海翌洋航空技术有限公司 | Pilotless solar energy aerobat |
| CN100358776C (en) * | 2005-08-02 | 2008-01-02 | 西北工业大学 | Miniature airplane pitch operating method and control mechanism |
-
2012
- 2012-07-03 CN CN201210229542.7A patent/CN102730183B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3640489A (en) * | 1968-07-26 | 1972-02-08 | Karl Jaeger | Vertical takeoff and landing aircraft |
| US4568043A (en) * | 1983-10-21 | 1986-02-04 | Schmittle Hugh J | Ultra-light aircraft with freely rotating rigid wing |
| US5054721A (en) * | 1989-03-22 | 1991-10-08 | Translab, Inc. | Vertical takeoff aircraft |
| CN2506536Y (en) * | 2001-11-16 | 2002-08-21 | 珠海翌洋航空技术有限公司 | Pilotless solar energy aerobat |
| CN100358776C (en) * | 2005-08-02 | 2008-01-02 | 西北工业大学 | Miniature airplane pitch operating method and control mechanism |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102910292A (en) * | 2012-10-31 | 2013-02-06 | 无锡同春新能源科技有限公司 | Bionic unmanned scout for killing mosquitos |
| CN103803056A (en) * | 2013-10-25 | 2014-05-21 | 苏州艾锐泰克无人飞行器科技有限公司 | Interceptor arranged on top of fuselage of unmanned aerial vehicle (UAV) |
| CN103612768A (en) * | 2013-11-29 | 2014-03-05 | 无锡同春新能源科技有限公司 | Solar unmanned aerial vehicle for sowing chemical weeding fine particles at low altitude above rice field |
| CN103803057A (en) * | 2013-12-20 | 2014-05-21 | 中国航天空气动力技术研究院 | Tandem-wing solar unmanned plane pneumatic configuration structure |
| CN103803057B (en) * | 2013-12-20 | 2016-06-01 | 中国航天空气动力技术研究院 | Row's wing sun power UAV aerodynamic layout structure |
| CN104085527A (en) * | 2014-07-09 | 2014-10-08 | 李庆宏 | Cuboid-shaped aircraft with upper support large flat plate |
| CN104176232A (en) * | 2014-08-18 | 2014-12-03 | 张文艳 | Three-wing glider |
| CN105836110A (en) * | 2016-04-11 | 2016-08-10 | 西北工业大学 | An improved taking-off and landing device used for a small unmanned aerial vehicle |
| CN106314767A (en) * | 2016-10-20 | 2017-01-11 | 中国航天空气动力技术研究院 | Lightweight undercarriage for solar powered unmanned air vehicle |
| CN106314767B (en) * | 2016-10-20 | 2019-02-19 | 中国航天空气动力技术研究院 | A kind of lightweight undercarriage for solar energy unmanned plane |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
| TWI763447B (en) * | 2021-04-20 | 2022-05-01 | 林瑤章 | Flying device with double wings |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102730183B (en) | 2015-01-07 |
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