CN102407938B - Wing installed with variant wingtip winglet and working mode thereof - Google Patents
Wing installed with variant wingtip winglet and working mode thereof Download PDFInfo
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- CN102407938B CN102407938B CN2011103176666A CN201110317666A CN102407938B CN 102407938 B CN102407938 B CN 102407938B CN 2011103176666 A CN2011103176666 A CN 2011103176666A CN 201110317666 A CN201110317666 A CN 201110317666A CN 102407938 B CN102407938 B CN 102407938B
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Abstract
The invention discloses a wing installed with variant wingtip winglet and a working mode thereof. In the invention, a rotary ultrasonic motor is utilized to directly realize conversion of winglet inclination angle, the rotary ultrasonic motor and a screw mechanism are utilized to realize conversion of winglet height and back sweep angle, and a variable flow control mechanism is utilized to improve flying efficiency of airplane in different flying states. The invention has light and simple structure, and can realize multi-parameter conversion of wingtip and greatly improve aerodynamic performance of airplane during takeoff, landing, climbing and cruising periods.
Description
Technical field
The present invention relates to a kind of wing that the variant winglet is installed, this wing is applicable to low subsonic flight condition.Belong to the aeronautical technology class.
Background technology
Aircraft taking off, landing, cruising phase need different aerodynamic characteristics, and current winglet is only for the cruising condition design, frame mode can not change, and is difficult to guarantee that aircraft all has aeroperformance preferably at each mission phase." the aeroplane wing tip winglet designs " that Jiang Yongquan writes (Jiang Yongquan. the design of aircraft winglet. the first edition. Beijing: aircraft industry press, 2009, the 52-74 page) studied the impact of winglet parameters on the wing aeroperformance: in certain scope, the height of winglet increases, can reduce the induced drag of aircraft, when the winglet height, during 0.07 times of the span, can make induced drag reduce 13%; The leaning angle of winglet increases (the increase span), can increase the slope of lift curve of aircraft, and increases fore-and-aft stability; The winglet sweepback angle in-30 ° to 60 ° scopes on the airplane ascensional force line slope without impact, but can change the pitching stability of aircraft, the sweepback angle of winglet will be greater than the sweepback angle of wing as far as possible, generally at 37 °.Aircraft is taking off and the landing stage, need large lift in order to increase take-off weight, climbing speed and landing safety, so in certain scope, increase height, leaning angle and the sweepback angle of winglet, in order to increase wing area, aspect ratio and slope of lift curve.Aircraft, in cruising phase, needs energy efficient, so the leaning angle of winglet reduces, plays the effect of eddy diffusion device, in order to reduce the induced drag of aircraft.
More than comprehensive, need a kind of wing that the variant winglet is installed of development, promote the mobile control effect of wingtip to wing, improve the aeroperformance of aircraft at each mission phase.
Summary of the invention
The object of the present invention is to provide a kind of wing and mode of operation thereof that the variant winglet is installed.
A kind of wing and mode of operation thereof that the variant winglet is installed, the winglet leaning angle that it is characterized in that comprising host wing framework, winglet framework, is installed between host wing framework and winglet framework changes mechanism, winglet rotating beam, is installed on the sweepback angle change mechanism between winglet framework and winglet rotating beam; Above-mentioned host wing framework is connected and is formed by host wing rib and host wing roof beam structure; Above-mentioned winglet framework is by the first winglet rib, the second winglet rib and be installed on two height slider tube assemblies between the winglet rib and the first threaded shaft sleeve and electric machine assembly and form; Wherein height slider tube assembly is comprised of height sliding support and height bracket sleeve, and height sliding support one end and the first winglet rib are fixed, and the other end stretches into an end of height bracket sleeve, and the other end of height bracket sleeve and the second winglet rib are fixed; Above-mentioned the first threaded shaft sleeve and electric machine assembly are comprised of the first rotary-type ultrasound electric machine, the first screw thread rotation axle and the first screw thread bush, the first rotary-type ultrasound electric machine is installed on the first winglet rib, its output shaft is connected with an end of the first screw thread rotation axle, the other end of the first screw thread rotation axle stretches into an end of the first screw thread bush and is mated, and the other end of the first screw thread bush and the second winglet rib are fixed; Above-mentioned winglet leaning angle changes mechanism and is comprised of following mode: the host wing framework is provided with a pair of motor mounting rack, the winglet framework is provided with a pair of variant winglet leaning angle support, a pair of rotary-type ultrasound electric machine is installed on respectively on above-mentioned motor mounting rack, and output shaft connects variant winglet leaning angle support; Above-mentioned winglet rotating beam is installed on above-mentioned the second winglet rib by articulated manner; Above-mentioned sweepback angle changes mechanism and is comprised of following mode: the second threaded shaft sleeve and electric machine assembly also is installed between the second winglet rib and winglet rotating beam; This second threaded shaft sleeve and electric machine assembly are comprised of the second rotary-type ultrasound electric machine, the second screw thread rotation axle and the second screw thread bush, the second rotary-type ultrasound electric machine is installed on the second winglet rib, its output shaft is connected with an end of the second screw thread rotation axle, the other end of the second screw thread rotation axle stretches into an end of the second screw thread bush and is mated, and the other end of the second screw thread bush is connected with revolute pair by sliding pair with the winglet rotating beam.
A kind of mode of operation that the wing of variant winglet is installed, it is characterized in that: in takeoff phase, drive the first screw thread rotation axle and rotate in the first screw thread bush by moving the first rotary-type ultrasound electric machine, make the total length elongation of the first screw thread rotation axle and the first screw thread bush, increase the height of winglet to 0.08-0.2 times of the span; Drive the second screw thread rotation axle and rotate in the second screw thread bush by moving the second rotary-type ultrasound electric machine, make the total length elongation of the second screw thread rotation axle and the second screw thread bush, and then drive the winglet rotating beam around hinge-point to inner rotary, increase by 45 °-60 °, the sweepback angle of winglet; By moving rotary-type ultrasound electric machine, variant winglet leaning angle support is rotated down around anchor shaft, increase the leaning angle to 90 ° of winglet, winglet and wing are in a plane;
In cruising phase, drive the first screw thread rotation axle and rotate in the first screw thread bush by moving the first rotary-type ultrasound electric machine, make the total length of the first screw thread rotation axle and the first screw thread bush shorten, the height that reduces winglet is to 0.05-0.1 times of the span; Drive the second screw thread rotation axle and rotate in the second screw thread bush by moving the second rotary-type ultrasound electric machine, make the total length of the second screw thread rotation axle and the second screw thread bush shorten, and then drive the winglet rotating beam and inwardly rotate around hinge-point, reduce the sweepback angle to 35 °-45 ° of winglet; By moving rotary-type ultrasound electric machine, variant winglet leaning angle support is rotated up around anchor shaft, reduce the leaning angle to 30 °-40 ° of winglet.
In the landing stage, drive the first screw thread rotation axle and rotate in the first screw thread bush by moving the first rotary-type ultrasound electric machine, make the total length elongation of the first screw thread rotation axle and the first screw thread bush, increase the height of winglet to 0.08-0.2 times of the span; Drive the second screw thread rotation axle and rotate in the second screw thread bush by moving the second rotary-type ultrasound electric machine, make the total length elongation of the second screw thread rotation axle and the second screw thread bush, and then drive the winglet rotating beam around hinge-point to inner rotary, increase the sweepback angle to 45 °-60 ° of winglet; By moving rotary-type ultrasound electric machine, variant winglet leaning angle support is rotated down around anchor shaft, increase the leaning angle to 90 ° of winglet, recover winglet and wing in a plane.
Each parameter variation range of above winglet, main " aeroplane wing tip winglet designs " of writing with reference to Jiang Yongquan (Jiang Yongquan. the design of aircraft winglet. the first edition. Beijing: aircraft industry press, 2009, the 52-185 page) decide, in actual application, construct by experiment different parameters combination for different type of machines, can make the control effect of winglet reach optimum.
The direct effect that the present invention obtains is: the aeroperformance of the lifting wing that the present invention can be larger.The present invention proposes the design plan of " variant winglet " thus---change in real time the geometric shape of winglet awing for different flight state, the pneumatic efficiency of aircraft cruising phase can not only be improved, the aeroperformance of aircraft in landing, ramp-up period can also be effectively improved.This scheme can be applicable to grow in the wing design of miniature self-service scout while navigating, development along with the high thrust ultrasound electric machine, also can be used in the mobile control of large airplane wingtip, in addition, according to statistics, 67% air crash occurs in and takes off and the landing stage, so the variant winglet has the potentiality that improve flight safety.Moreover the variant winglet can make aero-engine to realize climbing fast than low thrust, thereby reduces fuel oil consumption, reduces engine noise, increasing service life of engine etc.
The accompanying drawing explanation
Fig. 1 is assembly drowing of the present invention;
Number in the figure title: 1, host wing rib, 2, motor mounting rack, 3, rotary-type ultrasound electric machine, 4, variant winglet leaning angle support, the 5, first winglet rib, 6, the height sliding support, 7, height bracket sleeve, the 8, second winglet rib 9, the first screw thread bush, the 10, first screw thread rotation axle, 11, winglet rotating beam, 12, the second screw thread bush, the 13, second screw thread rotation axle, the 14, second rotary-type ultrasound electric machine, 15, host wing roof beam structure, the 16, first rotary-type ultrasound electric machine.
The specific embodiment
Below in conjunction with accompanying drawing and implementation process, the present invention will be further described.
As shown in Figure 1, the invention provides a kind of wing and mode of operation thereof that the variant winglet is installed, it comprises:
Host wing rib 1 is fixed together with host wing roof beam structure 15, forms the framework of host wing.Motor mounting rack 2 is connected with host wing roof beam structure 15 respectively, in order to the extended mainframe wing.Rotary-type ultrasound electric machine 3 is fixed on motor mounting rack 2, by variant winglet leaning angle support 4, connects the variant winglet, and variant winglet leaning angle support 4 is fixedly connected with the rotating shaft of rotary-type ultrasound electric machine 3, in order to change the leaning angle of winglet.
The first winglet rib 5 and the second winglet rib 8 form the framework of winglet, and winglet rib 5 is connected with variant winglet leaning angle support 4, and the variant winglet is thus connected on host wing.The first rotary-type ultrasound electric machine 16, height sliding support 6 and the first winglet rib 5 are connected; The first screw thread rotation axle 10 is fixedly connected with the rotating shaft of the first rotary-type ultrasound electric machine 16, and the first screw thread bush 9 is connected cooperation by screw thread with the first screw thread rotation axle 10; Height sliding support 6 is inserted in height bracket sleeve 7 and sliding block joint with it; The other end of the first screw thread bush 9, height bracket sleeve 7 is fixed on the second winglet rib 8.By moving first rotary-type ultrasound electric machine 16 drive the first screw thread rotation axles 10, in the first screw thread bush 9, rotate, make the total length of the first screw thread rotation axle 10 and the first screw thread bush 9 elongate or shorten, make the distance between the first winglet rib 5 and the second winglet rib 8 elongate or shorten, and then can change the height of winglet.
The second rotary-type ultrasound electric machine 14 is fixed on the second winglet rib 8, and the second screw thread rotation axle 13 is fixedly connected with the rotating shaft of the second rotary-type ultrasound electric machine 14, and the second screw thread bush 12 is connected cooperation by screw thread with the second screw thread rotation axle 13; The other end of the second screw thread bush 12 is connected with revolute pair by sliding pair with winglet rotating beam 11, one end of winglet rotating beam 11 and the second winglet rib 8 are hinged, by moving second rotary-type ultrasound electric machine 14 drive the second screw thread rotation axles 13, in the second screw thread bush 12, rotate, make the total length of the second screw thread rotation axle 13 and the second screw thread bush 12 elongate or shorten, and then drive winglet rotating beam 11 and rotate around hinge-point, finally realize the change at winglet sweepback angle.
In takeoff phase, by moving first rotary-type ultrasound electric machine 16 drive the first screw thread rotation axles 10, in the first screw thread bush 9, rotate, make the total length elongation of the first screw thread rotation axle 10 and the first screw thread bush 9, increase the height of winglet to 0.1 times of the span; By moving second rotary-type ultrasound electric machine 14 drive the second screw thread rotation axles 13, in the second screw thread bush 12, rotate, make the total length elongation of the second screw thread rotation axle 13 and the second screw thread bush 12, and then drive winglet rotating beam 11 around hinge-point to inner rotary, increase the left and right, 45 °, sweepback angle of winglet; By moving rotary-type ultrasound electric machine 3, variant winglet leaning angle support 4 is rotated down around anchor shaft, increase the leaning angle to 90 ° of winglet, winglet and wing are in a plane;
In cruising phase, by moving first rotary-type ultrasound electric machine 16 drive the first screw thread rotation axles 10, in the first screw thread bush 9, rotate, make the total length of the first screw thread rotation axle 10 and the first screw thread bush 9 shorten, the height that reduces winglet is to 0.07 times of the span; By moving second rotary-type ultrasound electric machine 14 drive the second screw thread rotation axles 13, in the second screw thread bush 12, rotate, make the total length of the second screw thread rotation axle 13 and the second screw thread bush 12 shorten, and then drive winglet rotating beam 11 and inwardly rotate around hinge-point, reduce the sweepback angle to 37 ° of winglet; By moving rotary-type ultrasound electric machine 3, variant winglet leaning angle support 4 is rotated up around anchor shaft, reduce the leaning angle to 30 ° of winglet.
In the landing stage, by moving first rotary-type ultrasound electric machine 16 drive the first screw thread rotation axles 10, in the first screw thread bush 9, rotate, make the total length elongation of the first screw thread rotation axle 10 and the first screw thread bush 9, increase the height of winglet to 0.1 times of the span; By moving second rotary-type ultrasound electric machine 14 drive the second screw thread rotation axles 13, in the second screw thread bush 12, rotate, make the total length elongation of the second screw thread rotation axle 13 and the second screw thread bush 12, and then drive winglet rotating beam 11 around hinge-point to inner rotary, increase the sweepback angle to 45 ° of winglet; By moving rotary-type ultrasound electric machine 3, variant winglet leaning angle support 4 is rotated down around anchor shaft, increase the leaning angle to 90 ° of winglet, recover winglet and wing in a plane.
To sum up, taking off and the landing stage of aircraft, increase height, leaning angle and the sweepback angle of winglet, in order to increase wing area, aspect ratio and slope of lift curve.Thereby the increase of the lift of the aircraft produced by wing, promoted take-off weight, climbing speed and the landing safety of aircraft.In the cruising phase of aircraft, reduce the leaning angle of winglet, make winglet play the effect of eddy diffusion device, reduce the induced drag of aircraft.Energy efficient.
Claims (2)
1. the wing that the variant winglet is installed, it is characterized in that: the winglet leaning angle that comprise host wing framework, winglet framework, is installed between host wing framework and winglet framework changes mechanism, and the sweepback angle that also comprise winglet rotating beam (11), is installed between winglet framework and winglet rotating beam (11) changes mechanism;
Above-mentioned host wing framework is connected and is formed by host wing rib (1) and host wing roof beam structure (15);
Above-mentioned winglet framework is by the first winglet rib (5), the second winglet rib (8) and be installed on two height slider tube assemblies between the winglet rib and the first threaded shaft sleeve and electric machine assembly and form; Wherein height slider tube assembly is comprised of height sliding support (6) and height bracket sleeve (7), height sliding support (6) one ends and the first winglet rib (5) are fixing, the other end stretches into an end of height bracket sleeve (7), and the other end of height bracket sleeve (7) and the second winglet rib (8) are fixing; Above-mentioned the first threaded shaft sleeve and electric machine assembly are comprised of the first rotary-type ultrasound electric machine (16), the first screw thread rotation axle (10) and the first screw thread bush (9), the first rotary-type ultrasound electric machine (16) is installed on the first winglet rib (5), its output shaft is connected with an end of the first screw thread rotation axle (10), the other end of the first screw thread rotation axle (10) stretches into an end of the first screw thread bush (9) and is mated, and the other end of the first screw thread bush (9) and the second winglet rib (8) are fixing;
Above-mentioned winglet leaning angle changes mechanism and is comprised of following mode: the host wing framework is provided with a pair of motor mounting rack (2), the winglet framework is provided with a pair of variant winglet leaning angle support (4), a pair of rotary-type ultrasound electric machine (3) is installed on respectively on above-mentioned motor mounting rack, and output shaft connects variant winglet leaning angle support (4);
Above-mentioned winglet rotating beam (11) is installed on above-mentioned the second winglet rib (8) by articulated manner;
Above-mentioned sweepback angle changes mechanism and is comprised of following mode: between the second winglet rib (8) and winglet rotating beam (11), the second threaded shaft sleeve and electric machine assembly also is installed; This second threaded shaft sleeve and electric machine assembly are comprised of the second rotary-type ultrasound electric machine (14), the second screw thread rotation axle (13) and the second screw thread bush (12), the second rotary-type ultrasound electric machine (14) is installed on the second winglet rib (8), its output shaft is connected with an end of the second screw thread rotation axle (13), the other end of the second screw thread rotation axle (13) stretches into an end of the second screw thread bush (12) and is mated, and the other end of the second screw thread bush (12) is connected with revolute pair by sliding pair with winglet rotating beam (11).
2. a kind of mode of operation that the wing of variant winglet is installed according to claim 1 is characterized in that:
In takeoff phase, drive the first screw thread rotation axle (10) and rotate in the first screw thread bush (9) by moving the first rotary-type ultrasound electric machine (16), make the total length elongation of the first screw thread rotation axle (10) and the first screw thread bush (9), increase the height of winglet to 0.08-0.2 times of the span; Drive the second screw thread rotation axle (13) and rotate in the second screw thread bush (12) by moving the second rotary-type ultrasound electric machine (14), make the total length elongation of the second screw thread rotation axle (13) and the second screw thread bush (12), and then drive winglet rotating beam (11) around hinge-point to inner rotary, increase by 45 °-60 °, the sweepback angle of winglet; By moving rotary-type ultrasound electric machine (3), variant winglet leaning angle support (4) is rotated down around anchor shaft, increase the leaning angle to 90 ° of winglet, winglet and wing are in a plane;
In cruising phase, drive the first screw thread rotation axle (10) and rotate in the first screw thread bush (9) by moving the first rotary-type ultrasound electric machine (16), make the total length of the first screw thread rotation axle (10) and the first screw thread bush (9) shorten, the height that reduces winglet is to 0.05-0.1 times of the span; Drive the second screw thread rotation axle (13) and rotate in the second screw thread bush (12) by moving the second rotary-type ultrasound electric machine (14), make the total length of the second screw thread rotation axle (13) and the second screw thread bush (12) shorten, and then drive winglet rotating beam (11) and inwardly rotate around hinge-point, reduce the sweepback angle to 35 °-45 ° of winglet; By moving rotary-type ultrasound electric machine (3), variant winglet leaning angle support (4) is rotated up around anchor shaft, reduce the leaning angle to 30 °-40 ° of winglet;
In the landing stage, drive the first screw thread rotation axle (10) and rotate in the first screw thread bush (9) by moving the first rotary-type ultrasound electric machine (16), make the total length elongation of the first screw thread rotation axle (10) and the first screw thread bush (9), increase the height of winglet to 0.08-0.2 times of the span; Drive the second screw thread rotation axle (13) and rotate in the second screw thread bush (12) by moving the second rotary-type ultrasound electric machine (14), make the total length elongation of the second screw thread rotation axle (13) and the second screw thread bush (12), and then drive winglet rotating beam (11) around hinge-point to inner rotary, increase the sweepback angle to 45 °-60 ° of winglet; By moving rotary-type ultrasound electric machine (3), variant winglet leaning angle support (4) is rotated down around anchor shaft, increase the leaning angle to 90 ° of winglet, recover winglet and wing in a plane.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011103176666A CN102407938B (en) | 2011-10-19 | 2011-10-19 | Wing installed with variant wingtip winglet and working mode thereof |
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| CN2011103176666A CN102407938B (en) | 2011-10-19 | 2011-10-19 | Wing installed with variant wingtip winglet and working mode thereof |
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| CN102407938A CN102407938A (en) | 2012-04-11 |
| CN102407938B true CN102407938B (en) | 2013-12-04 |
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| CN105438443B (en) * | 2015-12-08 | 2017-11-21 | 中国航空工业集团公司成都飞机设计研究所 | A kind of conformal folding wings |
| CN106516083A (en) * | 2016-08-01 | 2017-03-22 | 西北农林科技大学 | Winglet rotation device of minitype fixed wing unmanned aerial vehicle |
| CN109178296A (en) * | 2018-10-24 | 2019-01-11 | 东汉太阳能无人机技术有限公司 | Winglet and aerofoil system |
| CN109606627A (en) * | 2018-12-10 | 2019-04-12 | 彩虹无人机科技有限公司 | A kind of aviation aircraft winglet attachment device |
| CN110182353A (en) * | 2019-05-22 | 2019-08-30 | 厦门大学 | A kind of flying wing of variable geometry outboard wing sweep and tiltable winglet |
| CN110329490A (en) * | 2019-06-17 | 2019-10-15 | 南京航空航天大学 | A kind of deflector vane separated flow control apparatus and method |
| CN112389631B (en) * | 2020-10-15 | 2022-05-03 | 南京航空航天大学 | Analysis method for morphing wing and morphing wing driven by shaft disc type transmission mechanism |
| CN113320712A (en) * | 2021-06-17 | 2021-08-31 | 陕西飞机工业有限责任公司 | Installation method of airplane conduit bracket |
| CN114313215B (en) * | 2022-01-28 | 2023-11-14 | 天津大学 | Wing tip structure with variable dip angle and height |
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| US3730459A (en) * | 1969-09-18 | 1973-05-01 | D Zuck | Airplane with floating wing and reverse propeller thrust |
| RU2286287C1 (en) * | 2005-03-18 | 2006-10-27 | Казанский государственный технический университет им. А.Н. Туполева | Double-deck horizontal takeoff and landing aircraft with tiltable wings |
| CN202345909U (en) * | 2011-10-19 | 2012-07-25 | 南京航空航天大学 | Wing assembled with variant winglet |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH02227398A (en) * | 1989-03-01 | 1990-09-10 | Mitsubishi Heavy Ind Ltd | Main wing device for aircraft |
| US8083185B2 (en) * | 2007-11-07 | 2011-12-27 | The Boeing Company | Aircraft wing tip having a variable incidence angle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3730459A (en) * | 1969-09-18 | 1973-05-01 | D Zuck | Airplane with floating wing and reverse propeller thrust |
| RU2286287C1 (en) * | 2005-03-18 | 2006-10-27 | Казанский государственный технический университет им. А.Н. Туполева | Double-deck horizontal takeoff and landing aircraft with tiltable wings |
| CN202345909U (en) * | 2011-10-19 | 2012-07-25 | 南京航空航天大学 | Wing assembled with variant winglet |
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| JP平2-227398A 1990.09.10 |
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