CN110027698A

CN110027698A - A kind of adjustable angle of attack winglet and wing wingtip

Info

Publication number: CN110027698A
Application number: CN201910382188.3A
Authority: CN
Inventors: 王宁郅
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-05-08
Filing date: 2019-05-08
Publication date: 2019-07-19

Abstract

The present invention relates to a kind of adjustable angle of attack winglet and wing wingtips, belong to wing structure field.The existing winglet low mach raising and lowering section angle of attack is not big enough and the low speed segment that rises and falls reaches critical angle of attack stall.Winglet is constituted by 1 or 2, it is placed on wing wingtip end curved surface, shaft is on 1/4 string of winglet or slightly before, shaft is horizontal or close to level, and equal sweepback, shaft is by the insertion of wing wingtip end curved surface, it is supported on bearing, with the motor deceleration driving in wingtip, the adjustable angle of attack is deflected automatically, and small wing incidence value is made to reach the larger of flight each stage.Winglet driving torque is small, and the airplane ascensional force durection component of aerodynamic force is big.In addition, winglet wing tip adds a piece of open up to sweepback fixed shear wingtip.The present invention is used to further decrease wing induced drag.

Description

A kind of adjustable angle of attack winglet and wing wingtip

Technical field

The present invention relates to a kind of aeroplane wing tip winglet and wing wingtip, especially a kind of adjustable angle of attack winglet and wingtip Interior driving mechanism and wingtip structure is suitable for subsonic aircraft.

Background technique

The complementary angle of helical angle of the wing wing-tip vortex at radius r is the linear function of wing angle of attack α, is k α.A wing Tip winglet is placed in wing wingtip flow field, it is assumed that its chord length is infinitely small, and stream field influences very little under the different angles of attack, with convenient Following discussion.If horizontal or vertical winglet root chord is α with respect to the interior drift angle of wing wing tip chord or the elevation angle₀, then vertical winglet The angle of attack are as follows: α_y=k α+α₀, the angle of attack of horizontal winglet are as follows: α_z=k α+α+α₀.When the wing angle of attack changes Δ α, vertical small wing incidence It changes are as follows: Δ α_y=k Δ α, horizontal small wing incidence change are as follows: Δ α_z=(1+k) Δ α.The difference of the two: Δ α_z-Δα_y=Δ α, i.e., Horizontal small wing incidence change value wing angle of attack change value bigger than vertically small wing incidence change value.Practical small chord-length is not infinite Small, its stream field has an impact, and shows: different small wing incidences reduce k value in various degree；The wingtip vortex of winglet itself is in winglet The negative increment that wing wing-tip vortex helical angle complementary angle is generated within the scope of length, also reduces k value in various degree.It indicates to patrol with subscript 1 Boat, subscript 2 indicate take-off climb, then

Δα_z-Δα_y=α₂-α₁+(k_z2-k_y2)α₂-(k_z1-k_y1)α₁≈Δα

The angle of attack is cruised close to the wing cruise angle of attack for winglet, and the low speed segment angle of attack that rises and falls is more than the situation of the critical angle of attack, k value Reduce, k_z1And k_y1Reduce slightly more, k_z2And k_y2Reduce less slightly, but above formula is still set up.The existing winglet of the big aircraft of civil aviaton is close vertical, Winglet cruises normal force coefficient close to wing cruise lift coefficient, allows its low speed segment angle of attack that rises and falls to increase to the critical angle of attack and reaches mistake Speed, to improve the cruise efficiency of winglet as far as possible, during this, the angle of attack change value of vertical winglet is approximately equal to wing and rises and falls low speed segment most Daying angle value.By above formula, angle of attack change value is certainly bigger between horizontal winglet cruise and the low speed segment that rises and falls, and leads to the low speed segment that rises and falls Remote overcritical angle of attack advanced stall makes because the low speed segment wing angle of attack that rises and falls contains wing flap and retreats the ingredient for putting down rear decline The horizontal practical angle of attack variation of winglet is more smaller than the value calculated by above formula, but advanced stall conclusion is constant, and it is difficult that here it is horizontal winglets The reason of to obtain application.Due to 1/4 of the angle of attack less than the low mach critical angle of attack of existing winglet cruise, although having been approached high horse The conspicuous number shake angle of attack, but the low mach rise and fall section angle of attack is too small, has and quite mentions effect space greatly and be not utilized, and it is low to rise and fall The failure of fast section winglet, can only as the resistance element of wing wing-tip vortex, so existing winglet be not suitable for frequently rising and falling in it is short The big aircraft of journey, in addition, its aerodynamic force is no or seldom generates airplane ascensional force durection component.In wing wing tip chord lateral outer side, Wing-tip vortex is unobstructed, and above wing wing tip chord, since wing-tip vortex is stopped by wing, vortex energy shunts forwards, backwards, false If horizontal and vertical small wing incidence is all variable, keep identical larger, then the horizontal winglet in wing-tip vortex mainstream weakens wingtip The efficiency in whirlpool is higher than vertical winglet.The difficulty that fixed small wing incidence adapts to, promotes the invention of adjustable angle of attack winglet.Patent 1.CN109178296A, the shaft of winglet are parallel to wing wing tip chord, and front end is slightly outside, the camber angle of when rotation is adjustable winglet, Allow winglet from level change to vertical, whens low mach rise and fall, is horizontal, rise and fall low speed segment when it is vertical, when cruise, occupies In, the angle of attack is adjusted by changing camber angle.Patent 2.CN105480404A, the shaft of vertical winglet is perpendicular to wing, upper end Slightly outward, the peace corner of when rotation adjustable winglet, whens low mach rise and fall, small nose of wing was biased inwardly, rise and fall low speed segment when to Outside partially, placed in the middle when cruise, the angle of attack is adjusted by changing established angle.Patent 1. has a disadvantage that, aerodynamic force when (1) winglet is vertical Airplane ascensional force durection component it is small, (2) winglet aerodynamic center is remote from shaft, winglet rotate when need larger driving torque.Patent 2. having a disadvantage that, the airplane ascensional force durection component of (1) aerodynamic force is small, and the efficiency that (2) vertical winglet weakens tip whirlpool is smaller than horizontal The wing is low, and (3) have interference drag.In addition, patent 1. is risen and fallen, low speed segment winglet is vertical, and 2. winglet of patent is vertical, in addition to there is longitudinal force Outside moment vector, when rise and fall low speed segment crosswind winglet stall when, winglet causes to add wing box and short shaft to patent 1., or to patent The torque transverse direction vector at the long end of 2.L shape curved beam, because aerodynamic center radius is big, torque is larger, and structural strength rigidity is low, unreasonable. In addition, existing adjustable angle of attack winglet cannot improve drag reduction capability using multi-disc winglet in tandem as hawk.It is existing Fixed vertical winglet multi-disc is 2 vertical types and 2 run-in indexs, because of piece after influencing when 2 front and back formula anter stall.

Summary of the invention

The task of the present invention is provide a kind of adjustable angle of attack winglet and wing wingtip, winglet shaft is horizontal or close Level, transverse belt sweepback, it automatically controls winglet rotation, makes small wing incidence under the motor deceleration driving in wing wingtip The larger of each stage that fly is kept, it is not big enough and rise for solving the existing fixed vertical winglet low mach rise and fall section angle of attack Fall the problem of low speed segment reaches critical angle of attack stall, and for solving existing adjustable angle of attack winglet otherwise driving torque is excessive, Otherwise the too small problem of the airplane ascensional force durection component of aerodynamic force, in addition, can be subtracted using 2 winglets in tandem to improve The efficiency of weak wing wing-tip vortex, and in the wing tip of winglet, add a piece of open up to sweepback fixed shear wingtip, solution winglet itself The problem of wing tip vortex strength.

The present invention completes as follows: adjustable angle of attack winglet has 1 or 2 winglets, and the bar axis of winglet is Its shaft, on 1/4 string of winglet or slightly before, the winglet of 1 winglet scheme is placed on wing wingtip end curved surface shaft axis, Or the winglet of 2 winglet schemes is placed on end curved surface with spaced apart, equal sweepback, it is bent that shaft axis passes through wing wingtip end Face, 1 low-angle that space allows in shaft is horizontal or the winglet front and rear panel of 2 winglet schemes is staggered up and down wingtip, small wing bar Axis insertion wingtip is supported on 2 bearings, can rotate relative to wing, have sector bevel gear between 2 bearings on bar axis, with Conical gear engagement, then, the direct-connected harmonic speed reducer of the conical gear of 1 winglet scheme and motor；Or 2 winglet schemes Anter winglet conical gear by roller gear to after engagement together with the conical gear of rear winglet, connect harmonic reduction Device and motor.When motor drives harmonic speed reducer rotation, 1 winglet scheme directly arrives conical gear or 2 winglet schemes 1 tunnel directly another 1 tunnel, to 2 conical gears, drives sector bevel gear to rotate the bar axis of winglet, to adjust through roller gear Save the angle of attack of winglet.Band rotary angle transmitter on the bar axis of winglet, is calculated with the wing angle of attack and the complementary angle of wing wing-tip vortex helical angle Value and Mach 2 ship parameter, when changing the wing angle of attack to automatically control, small wing incidence keeps the larger of each stage that fly.For The wingtip vortex for weakening winglet itself, adds a piece of shearing wingtip in winglet wing tip, opens up and be fixed on winglet wing tip to sweepback.For Reduce the gas leakage of rotation winglet root and wing wingtip junction, the winglet root before and after small wing bar axis, respectively with wing Wingtip is gone forward sector bevel face and the sliding contact of rear sector bevel face, rear sector bevel face be higher than wingtip upper surface part be divided into it is small Wing fence in type is divided into small-sized lower wing fence lower than wingtip lower surface portion.In 2 winglet schemes, in order to allow winglet to occupy upcurrent The part of field is wider, and reduces the interference of front and rear panel winglet, improves the efficiency of 2 winglets, front and rear panel winglet can be allowed with level Face is starting point, around aircraft longitudinal axis, 1 low-angle that space allows in the wingtip that is staggered up and down, in this way, the small wing bar axis of anter is in wing Outlet port on wingtip end curved surface moves up, and anter small wing bar axis inner end rotates decline in wingtip.

It is solid to have the advantages that (1) present invention is solved with the adjustable angle of attack compared with existing winglet by the present invention Fixed horizontal small wing incidence adapts to problem, and winglet can be horizontal or close to horizontal setting；(2) since the angle of attack is adjustable, on low mach Rising the small wing incidence of descending branch may operate in more than 2 times of the small wing incidence value of fixed vertical, is gradually reduced, utilizes with Mach number rising Its is unserviceable to mention effect space, and the low speed segment that avoids rising and falling fixed vertical winglet some occurs and reaches critical angle of attack mistake Speed solves the problems, such as the low speed segment decrease wing wing-tip vortex that rises and falls by the way；(3) horizontal or close to horizontal setting winglet, pneumatically The airplane ascensional force durection component of power is big；(4) horizontal or close to horizontal setting winglet weakens the efficiency of wing wing-tip vortex than vertical Winglet is high；(5) horizontal or close to horizontal setting winglet, interference drag are small；(6) horizontal or close to horizontal setting winglet, no It can be because of crosswind winglet stall；(7) on 1/4 string or slightly before, driving torque is small, less than the 1/ of patent 1. for winglet shaft of the present invention 50, little motor and transmission mechanism together, are arranged in wing wingtip in which can be convenient；(8) the small wing bar axis axis of the present invention It is big to hold spacing, wing wingtip and winglet junction stress are small, and do not have axial moment vector, unlike patent 1. and 2. has transverse direction Moment vector；(9) present invention solves the problems, such as winglet stall with the adjustable angle of attack, and winglet can be changed with 2 in tandem, further be cut Weak wing-tip vortex；(10) since winglet wing tip adds a piece of shearing wingtip, the wingtip vortex of winglet itself is reduced.

Detailed description of the invention

Fig. 1 is 1 winglet scenario-frame schematic top view of the invention, and winglet can move forward some placements；Fig. 2 is this Invent 2 winglet scenario-frame schematic top views；Fig. 3 is 1 winglet scheme of the invention and 2 winglet scheme winglet wing tips Shearing wingtip structure schematic top view；Fig. 4 is the winglet root front and back sector bevel face structure of 1 winglet scheme of the present invention Schematic diagram is the wingtip rear portion left view that winglet is removed outside wing wingtip.

Specific embodiment

It is described in further detail below in conjunction with 2 embodiments of attached drawing of the invention to 2 schemes of the invention.Figure 1. Fig. 2,00 is wing, and 01 is winglet, and winglet angle of sweep is equal to or more than wing setting, for 1 winglet, due to Winglet root chord length closer to wing wingtip chord length, effect just closer to the wing span of only increase winglet length, Especially horizontal winglet, so the winglet of 1 winglet scheme of the invention should not be using larger wing root chord length and wing wingtip chord length Ratio.02 is the bar axis of winglet, and bar is pivotally supported on 2 bearings 03, is tapered roller bearing, has sector bevel gear on bar axis 04, the part other than work meshing segment is removed, to reduce height and weight.Sector bevel gear 04 and conical gear 05 Engagement, conical gear 05 to sector bevel gear 04 is deceleration transmission.Then, in the 1st embodiment of 1 winglet scheme, circular cone The direct-connected harmonic speed reducer 08 of gear 05 and motor 09；Or in the 2nd embodiment of 2 winglet schemes, the circular cone tooth of anter winglet Wheel 05 by roller gear to after 06 and 07 engagement with the conical gear 05 of rear winglet together, connect harmonic speed reducer 08 and electricity Motivation 09.Harmonic speed reducer 08 uses big retarding ratio.Angled sensor 10 on the bar axis 02 of winglet.Fig. 3 is 01 wing tip of winglet Shearing wingtip 11, open up on the wing tip that sweepback is fixed on winglet 01.Fig. 4 is sector bevel face 13 before 1 winglet scheme with after Sector bevel face 12, to make the upper and lower small wing fence in rear sector bevel face along aircraft portrait, can allow winglet root back segment slightly inwards Partially.Bar axis 02 and winglet 01 and shearing 11 three parts of wingtip are integrally made of carbon fibre composite.

Claims

1. a kind of adjustable angle of attack winglet and wing wingtip, characterized in that winglet is made of 1 or 2, and the bar axis of winglet is Its shaft, on 1/4 string of winglet or slightly before, the winglet of 1 winglet scheme is placed on wing wingtip end curved surface shaft axis, Or the winglet of 2 winglet schemes is placed on end curved surface with spaced apart, shaft axis passes through wing wingtip end curved surface, shaft water Flat or 2 winglet schemes winglet front and rear panel is staggered the low-angle that space in wingtip allows up and down, equal sweepback, and bar axis is inserted Enter wingtip to be supported on 2 bearings, can be rotated relative to wing, is driven by the motor deceleration in wingtip, made to automatically control The angle of attack of winglet is adjustable.

2. according to adjustable angle of attack winglet as defined in claim 1. and wing wingtip, characterized in that the wing tip of winglet has one Piece is opened up to sweepback fixed shear wingtip.

3. according to adjustable angle of attack winglet as defined in claim 2. and wing wingtip, characterized in that and small in wing wingtip , there are rear sector bevel face and preceding sector bevel face in thriving root front and rear part contact position, it and rotation winglet root sliding contact, rear to fan Shape circular conical surface be higher than wing wingtip upper surface part be divided into small-sized upper wing fence, lower than wing wingtip lower surface portion be divided into it is small-sized under Wing fence.

4. according to adjustable angle of attack winglet as defined in claim 3. and wing wingtip, characterized in that 2 on the bar axis of winglet There is sector bevel gear between a bearing, is engaged with conical gear.

5. according to adjustable angle of attack winglet as defined in claim 4. and wing wingtip, the conical gear of 1 winglet scheme is straight Even harmonic speed reducer；Or the conical gear of the anter winglet of 2 winglet schemes by roller gear to after engagement with rear piece winglet Conical gear together, connect harmonic speed reducer.

6. according to adjustable angle of attack winglet as defined in claim 5. and wing wingtip, characterized in that harmonic speed reducer connection Motor.