CN102358417A

CN102358417A - Annular winglet of civil airliner wing

Info

Publication number: CN102358417A
Application number: CN2011102582836A
Authority: CN
Inventors: 韩天时; 刘沛清; 田云; 屈秋林; 郭昊
Original assignee: Beihang University
Current assignee: Beihang University
Priority date: 2011-09-02
Filing date: 2011-09-02
Publication date: 2012-02-22
Anticipated expiration: 2031-09-02
Also published as: CN102358417B

Abstract

The invention discloses an annular winglet of a civil airliner, which belongs to the field of aviation aerodynamic technology, and comprises an outer ring section, an inner ring section and a transition section; The root of the ring section is connected to the root of the outer ring section and fixed by rivets in the middle of the upper and lower two-layer sheet structures of the transition section, so that the inner ring section and the outer ring section are connected to form an overall ring structure, and the wing tip of the aircraft wing It is also placed in the middle of the upper and lower two-layer sheet structures of the transition section. The ring-shaped winglet of a civil airliner proposed by the present invention is a ring-shaped structure, and the ring-shaped winglet has a greater effective The stretching effect can reduce the induced resistance; the two ends of the ring-shaped winglet are closed into a ring, and the strength and rigidity are greatly improved, so the structural weight can be reduced; the ring-shaped winglet has strong torsion and bending resistance, which is good for aircraft flutter. The speed effect is small.

Description

A kind of wing annular winglet of seating plane

Technical field

The invention belongs to aviation pneumatics field, be specifically related to a kind of wing annular winglet of seating plane.

Background technology

Winglet is a kind of pioneering technology; It with the cost that increases minimal structure weight improve high low speed 1ift-drag ratio with the efficient of cruising, reduce the head that takes off, increase the climb rate; Research shows as long as the local air-flow of the installation direction of the curvature of winglet aerofoil and winglet and wing wing tip matees proper; Can produce inside side force, suppress the wing tip whirlpool of wing, reduce induced drag.For most of transport planes, when cruising flight, induced drag accounts for 40% of total drag, has very big economic value to practicing thrift oil consumption with the operating cost that reduces aircraft.

At present, adopt Wing tip devices such as winglet, wing-tip vortex diffuser and wingtip sail sheet on the aircraft, propose new ideas such as " fusion type winglet ", " spiral winglet " in recent years again, and obtained remarkable result at aspects such as drag reductions.But above-mentioned winglet also has some adverse effects to overcome, and at first, winglet itself can produce induced drag and form resistance; Secondly, the installation of winglet can increase the wing root moment of flexure, influences the structural strength of wing; Once more, best for " spiral winglet " its drag-reduction effect, but structure is too complicated; Inconvenient installation, and install winglet additional airplane flutter speed is reduced, flight safety influenced.

Summary of the invention

To the problem that exists in the prior art; The present invention provides a kind of wing annular winglet of seating plane, and this winglet is used in combination the layout advantage of " ring air foil " through absorbing, merging advanced winglet pneumatic design thought; Can improve the resistance reducing performance of winglet; And can reduce wing wing root moment of flexure, and reduce wing wing tip vortex strength degree, alleviate winglet to the airplane flutter velocity effect.

The present invention proposes a kind of wing annular winglet of seating plane, comprises outer shroud section, interior ring section and transition phase; This outer shroud section is semi-circular structure, and launching the back is trapezium structure, and trapezoidal upper base is an outer shroud section taper, and trapezoidal going to the bottom is outer shroud section root, and trapezoidal left side is an outer shroud section costa, and trapezoidal right edge is as outer shroud section trailing edge line; The also not semi-circular structure of ring section in described, launching the back is trapezium structure, trapezoidal upper base is as interior ring section taper; Trapezoidal going to the bottom as interior ring section root; Trapezoidal left side is as interior ring section costa, and trapezoidal right edge is as outer shroud section trailing edge line, interior ring section slightly portion and outer shroud section slightly portion's size equate.Described transition phase has two layers of thin chip architecture up and down; The dual-side of two-layer thin slice is connected to each other to integrated formed structure up and down; In described ring section slightly portion and outer shroud section slightly portion be connected and fix; An interior ring section root is connected with outer shroud section root and is fixed in the middle of the chip architecture of two layers of thin up and down of transition phase through rivet; The ring section is connected whole circular ring structure of back formation in making with the outer shroud section; And interior ring section portion and interior ring section root slightly all is positioned at the inside of whole circular ring structure when being connected, and the wing tip of aircraft wing is also placed the centre of the chip architecture of two layers of thin up and down of transition phase, make the centre of the chip architecture of two layers of thin up and down of transition phase rivet in order in the wing tip of ring section, outer shroud section and aircraft wing.

The outer shroud section taper ratio that the present invention proposes a kind of wing annular winglet of seating plane is 0.20～0.30; Outer shroud section sweepback angle be chosen for than wing 1/4 string of a musical instrument sweepback angle big 15 °～20 °; The height of outer shroud section is 10%～12% of a wing semispan length; An interior ring section taper ratio is 0.5～0.6; In ring section sweepback angle than outer shroud section sweepback angle α little 9 °～11 °; Interior ring section height is highly little by 3.5%～4.0% than the outer shroud section; The low brilliance of the central sections of annular winglet is 2 °～3 °; The stagger angle of annular winglet is 0 °～-4 °; The leaning angle of annular winglet is 0 °～4 °.

The advantage that the present invention has is:

1, the present invention proposes a kind of wing annular winglet of seating plane; This winglet and aircraft wing tip chord between adopt the deep camber smooth transition to be connected; It is the fusion type winglet; Guarantee the connecting portion smooth surface, reduce the pneumatic interference between winglet and the wing, improve stressing conditions simultaneously;

2, the present invention proposes a kind of wing annular winglet of seating plane, and winglet is a loop configuration, and annular winglet is under the situation of identical how much long increments of wing exhibition, and more conventional winglet has the bigger long-acting fruit of effective exhibition, can reduce induced drag; The winglet closed at both ends circularizes, and strength and stiffness all significantly improve, so can alleviate structural weight; The annular winglet is antitorque all very strong with resistance to bending, and is little to the influence of airplane flutter speed;

3, the present invention proposes a kind of wing annular winglet of seating plane; The strong concentrated vorticity that the outer shroud section is hauled out the aircraft wing wing tip has good dispersing action, and its intensity under viscous effect is weakened very soon, and its aerofoil profile is a supercritical airfoil; Can postpone winglet separates; Avoid stream field to have a negative impact, and can produce inside side force, extra raising force and thrust forward are provided; Interior ring section can be blocked to flowing inside exhibition; Because interior ring section is symmetrical with the outer shroud section, so the cross section is symmetrical, the interior supercritical airfoil of encircling the section aerofoil profile for counter-rotating produces lateral power, can regulate with the moment of flexure that prevents the winglet generation excessive to the interior side force that the outer shroud section is produced.

Description of drawings

Fig. 1-A: the front view of the wing annular winglet of a kind of seating plane provided by the invention;

Fig. 1-B: the right elevation of the wing annular winglet of a kind of seating plane provided by the invention;

Fig. 1-C: the birds-eye view of the wing annular winglet of a kind of seating plane provided by the invention;

Fig. 2: the wing annular winglet of a kind of seating plane provided by the invention and the scheme drawing that is connected of aircraft wing wing tip;

Fig. 3-A: outer shroud segment structure scheme drawing among the present invention;

Fig. 3-B: ring segment structure scheme drawing among the present invention;

Fig. 4: transition phase outside drawing among the present invention;

Fig. 5: selected wing section lift coefficient is with the change in angle of attack diagram of curves among the present invention.

Among the figure: 1-outer shroud section; Ring section in the 2-; The 3-transition phase; 4-aircraft wing wing tip;

101-outer shroud section taper; 102-outer shroud section root; 103-outer shroud section costa; 104-outer shroud section trailing edge line;

Ring section taper in the 201-; Ring section root in the 202-; Ring section costa in the 203-; Ring section trailing edge line in the 204-.

The specific embodiment

To combine accompanying drawing and embodiment that the present invention is done further detailed description below.

The wing annular winglet of a kind of seating plane provided by the invention like Fig. 1-A, 1-B, 1-C and shown in Figure 2, comprises outer shroud section 1,

interior ring section

2 and 3 three parts of transition phase.Shown in Fig. 3-A, described outer shroud section 1 is semi-circular structure, and launching the back is trapezium structure; Trapezoidal upper base is as outer shroud section taper 101; Trapezoidal going to the bottom as outer shroud section root 102, trapezoidal left side are as outer shroud section costa 103, and trapezoidal right edge is as outer shroud section trailing edge line 104; Outer shroud section taper ratio is outer shroud section taper 101 length and outer shroud section root 102 length ratios; Value is 0.20～0.30; Outer shroud section sweepback angle α is the angle between outer shroud section costa 103 and the outer shroud section root 102, this outer shroud section sweepback angle α be chosen for than wing setting big 15 °～20 °.The diameter length that this trapezium structure is rolled the semi-circular outer shroud section of back formation is outer shroud section height H.

Shown in Fig. 3-B, described interior ring section 2 also not semi-circular structures, launching the back is trapezium structure; Trapezoidal upper base is as interior ring section taper 201; Trapezoidal going to the bottom as interior ring section root 202, trapezoidal left side is as interior ring section costa 203, and trapezoidal right edge is as outer shroud section trailing edge line 204; An interior ring section taper ratio is interior ring section taper 201 length and interior ring section root 202 length ratios, and value is 0.5～0.6.In a ring section sweepback angle β be chosen for than outer shroud section sweepback angle α little 9 °～11 °.The semi-circular interior diameter length of encircling section that forms after this trapezium structure is rolled is as interior ring section height h, and preferably interior ring section height is highly little by 3.5%～4.0% than the outer shroud section.

As shown in Figure 4; Described transition phase 3 has two layers of thin chip architecture up and down; The surface has some riveted holes that are used to rivet; The dual-side of two-layer thin slice is connected to each other to integrated formed structure up and down, described in ring section slightly portion 201 and outer shroud section slightly portion 101 is connected and fixes, an interior ring section root 202 is connected with outer shroud section root 102 and is fixed in the middle of the chip architecture of two layers of thin up and down of transition phase 3 through rivet; Guarantee that interior ring section 2 is connected the back with outer shroud section 1 and forms a whole circular ring structure; And interior ring section portion 201 and interior ring section root 202 slightly all is positioned at the inside of whole circular ring structure when being connected, and aircraft wing wing tip 4 is also placed the centre of the chip architecture of two layers of thin up and down of transition phase 3, makes that the centre of the chip architecture of two layers of thin up and down of transition phase 3 encircles sections 2 in riveting in order, the wing tip 4 of outer shroud section 1 and aircraft wing.

The wing of a kind of seating plane provided by the invention annular winglet has 2 °～3 ° the low brilliance γ of central sections, the low brilliance of described central sections be the outer shroud section slightly portion 102 and interior ring section slightly relative ground, portion 201 junctions horizon towards the leaning angle of outer shroud section costa 103 with interior ring section costa 203.Shape winglet provided by the invention has the winglet stagger angle ε of 0 °～-4 ° (being preferably-2 °); Described winglet stagger angle ε is that aircraft wing wing tip 4 is when being connected with annular winglet; When aircraft wing wing tip 4 is connected with outer shroud section root 102, interior ring section root 202; Outer shroud section root 102, the interior angle that encircles section root 202 with respect to aircraft wing wing tip 4 planes; Wherein being positive-angle, be negative angle with angle away from the direction on aircraft wing wing tip 4 planes near aircraft wing wing tip 4 in-plane angles.Shape winglet provided by the invention has the winglet leaning angle δ of 0 °～4 ° (being preferably 4 °); Described winglet leaning angle δ is outer shroud section root 201, an interior ring section root 202 when being connected with aircraft wing wing tip 4, the leaning angle outside with respect to the horizontal surface of aircraft wing.

The outer shroud section of the conventional winglet of large-scale seating plane highly accounts for 5.00%～10.08% of wing semispan length; The outer shroud section 1 of winglet highly increases can make induced drag reduce; And because ring section 2 is carried out the moment trim in having; Can significantly not increase the wing root moment of deflection, so outer shroud section 1 highly is 10%～12% of a wing semispan length among the present invention.For making annular winglet reach desirable exhibition to distribution; Make it have maximum air efficient; The annular winglet should have bigger outer shroud section taper ratio, and general span is 0.300～0.545, effectively opens up because of ring air foil and grows up; Therefore can reduce ratio, choosing outer shroud section taper ratio among the present invention is 0.20～0.30.Outer shroud section sweepback angle is approximate identical with the sweepback angle of wing or bigger slightly than the sweepback angle of wing; Because of ring air foil structural strength, good rigidity; For delaying the stall of outer shroud section winglet; Strengthen outer shroud section sweepback angle, thus among the present invention outer shroud section sweepback angle choose than wing 1/4 string of a musical instrument sweepback angle big 15 °～20 °.Ring section 2 height are highly little by 3.5%～4.0% than outer shroud section 1 among the present invention, and are inner to avoid itself and top airfoil contact position, influence high-lift systems.Be to encircle the big interference of the mobile generation of 202 pairs of upper surface of the airfoils of section root in preventing among the present invention, under the situation that guarantees structural requirement, reduce the root chord length as far as possible, an interior ring section taper ratio of the present invention is 0.5～0.6; For preventing annular winglet than the first stall of wing tip, the low brilliance of central sections is selected 2 °～3 °, delays burbling among the present invention; The stagger angle that annular winglet stagger angle general leading edge outwards promptly becomes to bear with the tip chord plane; Can reduce the burbling of annular winglet root upper surface; Because aircraft wing wing tip 4 upper surfaces have sizable incoming flow angle; Wind tunnel test proof winglet stagger angle is 0 °～-4 °, is preferably-2 °.For making winglet can reduce induced drag effectively, and it is little that aircraft wing wing tip 4 and annular winglet root intersection are disturbed in the supercriticality air current flow, prevents to separate, and annular winglet leaning angle is 0 °～-4 °.

To select for use with the supercritical airfoil be that (outer shroud section aerofoil profile is a supercritical airfoil on the basis to the aerofoil profile (cross sectional shape) of wing annular winglet among the present invention; Interior ring section aerofoil profile is the supercritical airfoil of counter-rotating); And reduce leading-edge radius, increase camber, reduce relative thickness, after move the maximum ga(u)ge position; So that it has low speed lift efficiency preferably; Also have overcritical preferably characteristic and stalling characteristics, among the present invention the wing section lift coefficient that adopts as shown in Figure 5 with the change in angle of attack curve, Mach number (ratio of local speed and local velocity of sound) Ma=0.75, Reynolds number (describing the parameter of air viscosity) Re=4*10 wherein ⁷Annular winglet aerofoil profile stalling incidence is 6 ° under the state, and original aerofoil profile of the prior art relatively is about 4 °, and stalling characteristics improve a lot.

With certain 300 base main-line-aircraft is example, the long 30m of this aircraft exhibition, and 30 ° at 1/4 chord length sweepback angle, confirm its outer shroud section height: the winglet height accounts for 10% of wing semispan, is 30 (m) * 10%=3 (m); Outer shroud section sweepback angle is bigger 10 ° than wing setting, is 30 °+15 °=45 °; Outer shroud section taper ratio 0.20; In ring section height: interior ring section is highly little by 3.5% than the outer shroud section, and is inner to avoid itself and top airfoil contact position, influences high-lift systems, is 30 (m) * (1-3.5%)=28.95 (m); Interior ring section sweepback angle is little 9 ° than outer shroud section sweepback angle, is 45 °-9 °=36 °; An interior ring section taper ratio is 0.50; The low brilliance of central sections is got-2 °; Stagger angle is got-2 °; Camber angle is got 4 °.

The present invention has taken into account the advantage of various configurations, and full machine induced drag reduces 30%, practices thrift fuel oil 6%.

Claims

1. A wing ring-shaped winglet of a civil airliner is characterized in that: it comprises an outer ring section, an inner ring section and a transition section; the outer ring section is a semi-circular structure, which is a trapezoidal structure after deployment, and the trapezoidal upper bottom is The tip of the outer ring section, the lower bottom of the trapezoid is the root of the outer ring section, the left side of the trapezoid is the front edge line of the outer ring section, and the right side of the trapezoid is the trailing edge line of the outer ring section; the inner ring section is not semi-circular. , after unfolding, it becomes a trapezoidal structure, the upper bottom of the trapezoid is used as the tip of the inner ring segment, the lower bottom of the trapezoid is used as the root of the inner ring segment, the left side of the trapezoid is used as the leading edge line of the inner ring segment, and the right side of the trapezoid is used as the trailing edge line of the outer ring segment; The transition section has an upper and lower two-layer thin sheet structure, and the two sides of the upper and lower two-layer thin sheets are connected to each other to form an integral structure. The root of the ring section is connected and fixed in the middle of the upper and lower two-layer sheet structures of the transition section by riveting, so that the inner ring section and the outer ring section are connected to form a whole ring structure, and the inner ring section and the root of the inner ring section are connected The time is located inside the overall ring structure, and the wing tip of the aircraft wing is also placed in the middle of the upper and lower two-layer sheet structures of the transition section, so that the middle of the upper and lower two-layer sheet structures of the transition section is sequentially riveted with an inner ring section , the outer ring segment and the wingtip of the aircraft wing.

2 . The annular winglet of a civil passenger aircraft according to claim 1 , wherein the tip-to-root ratio of the outer ring section is 0.20-0.30. 3 .

3. The annular winglet of a kind of civil airliner according to claim 1, characterized in that: the sweep angle of the outer ring section is selected to be 15% larger than the sweep angle of the 1/4 chord line of the wing. °～20°.

4. The annular winglet of a civil passenger aircraft according to claim 1, wherein the height of the outer ring section is 10% to 12% of the half-span length of the wing.

5 . The annular winglet of a civil passenger aircraft according to claim 1 , wherein the tip-to-root ratio of the inner ring section is 0.5-0.6. 5 .

6. The ring-shaped winglet of a civil passenger aircraft according to claim 1 or 3, wherein the sweep angle of the inner ring section is 9°-11° smaller than the sweep angle α of the outer ring section. °.

7. The annular winglet of a civil passenger aircraft according to claim 1 or 4, wherein the height of the inner ring section is 3.5%-4.0% smaller than the height of the outer ring section.

8 . The ring-shaped winglet of a civil airliner according to claim 1 , wherein the nose-down angle of the central section of the ring-shaped winglet is 2° to 3°.

9 . The ring-shaped winglet of a civil airliner according to claim 1 , wherein the installation angle of the ring-shaped winglet is 0°˜-4°.

10. The ring-shaped winglet of a civil airliner according to claim 1, wherein the inclination angle of the ring-shaped winglet is 0°-4°.