CN104875873B - A kind of aircraft wing with aerodynamic arrangement and the aircraft using this wing - Google Patents
A kind of aircraft wing with aerodynamic arrangement and the aircraft using this wing Download PDFInfo
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Abstract
The present invention provides a kind of aircraft wing with aerodynamic arrangement and the aircraft using this wing, the upper and lower wing section that aircraft includes fuselage and is connected on fuselage and stretches out along spanwise respectively, the wingtip chordwise dislocation tandem of the wingtip of top wing section and lower wing section is connected and constitutes joint wingtip section so that described upper and lower wing section forms double triangle structure with described fuselage, chordwise is defined as fore-and-aft direction, the trailing edge of the wingtip positioned at front side is connected with the leading edge of the wingtip positioned at rear side.Understood according to modern " nearly coupled wave theory ", wingtip positioned at front side can cause disturbance to the air-flow being born in rear wingtip, reduce flow perturbation to drag effects produced by posterior wingtip, wingtip vortex produced by preceding wingtip is persistently digested by posterior wingtip, wingtip vortex produced by preceding wingtip can play lift effect to posterior wingtip, and then increased the efficient wing span producing lift effect of the connection wing of this triangular structure.
Description
Technical field
The present invention relates to a kind of aircraft wing with novel pneumatic layout and the aircraft using this wing.
Background technology
Light-duty or ultra light aircraft not only " human-oriented ", and has wide application.Due to this kind of aircraft cost relatively
Relatively low, make relatively easy, the lead time again short so that this kind of flivver has an abundant aerodynamic configuration, exquisite structure design,
The technology having more novelties than big aircraft embodies.
In order to obtain larger lift-drag ratio, light aerocraft generally adopts the wing structure of high aspect ratio, this wing area
Generally larger so that the span of single width wing is larger.But the mechanical strength structure efficiency of this excessively elongated wing is relatively low,
It is unfavorable for for airfoil lift being delivered to fuselage, and this very thin high aspect ratio wing must have higher intensity huge to bear
Lift moment of torsion, this makes, and wing manufacture difficulty is very big, and the life-span is not long.The structure of old-fashioned biplane is relatively simple, and it leads to
Cross to obtain compared with lift using the two-layer wing arranged up and down, this biplane lift is larger, and low-altitude performance is stable, low speed
Flight effect is good, easily manipulates, applies more universal in the work such as aerial survey, mine locating, aerophotography, aerial spraying pesticide.But
This biplane generally installs support or pillar additional although increased wing intensity between upper and lower wing, but also greatly increases
Big flight resistance, and a pair of wing having more than monoplane of biplane also adds additional and miscarried by additional wingtip vortex
Raw induced drag.
As shown in Figure 1 to Figure 3, it includes extending along the longitudinal direction the aircaft configuration of existing employing Lian Yi aerodynamic arrangement
Fuselage 300, fuselage 300 is provided with the top wing section 100 extending respectively and lower wing section 200, upper and lower wing section along spanwise
Outer end wingtip be coupled to each other and arranged superposed on vertical up and down, although conventional biplane so can be avoided to be brought
Have more the problem of the double induced drag that a wing leads to occur, but this joint wing has actual asking when using
Topic, because when a wing is less than on vertical and has object in the range of chord length, being bound to disturb the flow field of wing, above-mentioned
The interference being formed between this upper and lower overlapping upper and lower wing section can form the vortex of confusion, this partly chaotic vortex meeting
Balance out the wing section that vortex is surrounded, this part wing section no longer produces useful lift, and then can reduce generation useful lift
Efficient wing span.
A kind of connection wing is disclosed in the Chinese utility model patent application specification for CN2122834U for the Authorization Notice No.
Aircraft, this Connected wing aircraft is the wing tip setting end wing of two pairs of wings in traditional biplane, and by the end wing by two-layer wing
Wingtip is connected and fixed, the wing tip of the upper and lower wing of this Connected wing aircraft arranged superposed, top wing, lower wing, fuselage on vertical
And end plate is integrally formed twoport box-structure.The wingtip of upper and lower wing is staggered certain distance on vertical by the end wing, to reduce
The flow field interference each other of upper and lower wing section, meanwhile, reduces, using the end wing, the induced drag that wingtip vortex produces.But it is this double
The overall resistance of the connection wing layout of mouth box-structure is larger, reduces lift-drag ratio, and lead to the connection wing plays the effective of lift effect
The span is less.And, the vertical end plate in connection wing layout larger face because side has of above-mentioned this twoport box-structure, horizontal
To less stable, when running into larger lateral airflow, side direction perturbation accident easily occurs.
Content of the invention
The present invention provides a kind of aircraft wing, larger with the overall resistance that solves Connected wing aircraft aerodynamic arrangement in prior art
Lead to join the less technical problem of efficient wing span of wing layout；Meanwhile, the present invention also provide a kind of using above-mentioned aircraft wing
Aircraft.
The technical scheme of aircraft wing provided by the present invention is：A kind of aircraft wing, including respectively along spanwise to
The upper and lower wing section of outer extension, the wingtip chordwise dislocation tandem of the described wingtip of top wing section and lower wing section is solid
Even constitute joint wingtip section so that the fuselage of described upper and lower wing Duan Keyu aircraft forms double triangle structure, by wing chord
Direction is defined as fore-and-aft direction, and the trailing edge of the wingtip positioned at front side is connected with the leading edge of the wingtip positioned at rear side.
The outside along spanwise of described joint wingtip section is fixed with swept-back triangle outer wing, swept-back triangle
Chordwise at the wing root of outer wing is consistent with the chordwise of the wingtip of described upper and lower wing section.
The outside along spanwise of described joint wingtip section is fixed with connection end plate, described swept-back triangle outer wing
It is connected with described wingtip section of combining by coupling end plate.
Described top wing section is located at the front of lower wing section, the wing shapes of described upper and lower wing section adopt following its
A kind of middle scheme：
（1）Described upper and lower wing section such as is at the RECTANGULAR WINGS of chord length, and the chord length of upper and lower wing section is equal；
（2）Described upper and lower wing section is the tapered airfoil that wing root chord length is more than wing tip chord length；
（3）Described upper and lower wing section is the tapered airfoil that wing root chord length is less than wingtip chord length.
Described top wing section is located at the front of lower wing section, and top wing section is for being arranged in machine along spanwise insertion
The insertion wing section of body, the two ends wingtip along spanwise arrangement of insertion wing section is the wing of described top wing section
The tip, lower wing section includes being distributed in two split air conditioner wing panels of described fuselage both sides, two splits along described spanwise correspondence
Wing section along spanwise arrangement outer end wingtip be described lower wing section wingtip, two split air conditioner wing panels along span side
Inner wing root to arrangement is used for being fixedly connected in described underbelly.
Described insertion wing section and two split air conditioner wing panels such as are at the RECTANGULAR WINGS of chord length, insertion wing section along wing chord
Spacing with the inner wing root of described two split air conditioner wing panels at the position corresponding with the inner wing root of two split air conditioner wing panels of direction
Chord length more than described insertion wing section.
The technical scheme of the aircraft using above-mentioned wing provided by the present invention is：A kind of aircraft, including fuselage and be connected
Upper and lower wing section, the described wingtip of top wing section and the lower wing section stretching out along spanwise on fuselage and respectively
Wingtip chordwise dislocation tandem be connected constitute joint wingtip section so that described upper and lower wing section is formed with described fuselage
Double triangle structure, chordwise is defined as fore-and-aft direction, the trailing edge of the wingtip positioned at front side and the wingtip positioned at rear side
Leading edge connects.
The outside along spanwise of described joint wingtip section is fixed with swept-back triangle outer wing, swept-back triangle
Chordwise at the wing root of outer wing is consistent with the chordwise of the wingtip of described upper and lower wing section.
Described top wing section is located at the front of lower wing section, and top wing section is for being arranged in machine along spanwise insertion
The insertion wing section of body, the two ends wingtip along spanwise arrangement of insertion wing section is the wing of described top wing section
The tip, lower wing section includes being distributed in two split air conditioner wing panels of described fuselage both sides, two splits along described spanwise correspondence
Wing section along spanwise arrangement outer end wingtip be described lower wing section wingtip, two split air conditioner wing panels along span side
Inner wing root to arrangement is used for being fixedly connected in described underbelly.
Described insertion wing section and two split air conditioner wing panels such as are at RECTANGULAR WINGS, insertion wing section and two splits of chord length
The inner wing root of wing section is more than the chord length of described insertion wing section in the spacing on up and down vertically.
The invention has the beneficial effects as follows：The wingtip of top wing section of aircraft wing provided by the present invention and lower wing section
Wingtip chordwise dislocation tandem is connected and constitutes joint wingtip section, and so, the fuselage of upper and lower wing section and aircraft is formed for pair
Triangular structure, this double triangle structure makes wing stability in the large preferably, and the disturbance of lateral airflow affects on it to reduce,
And, the wingtip chordwise dislocation tandem due to two wing sections is connected, according to " nearly coupled wave theory " it is recognised that being located at front
The wingtip of side can cause favorably to disturb to the air-flow being born in rear wingtip, and wingtip vortex produced by preceding wingtip is posterior
Wingtip continues digestion, and two width wingtips of upper and lower wing section only produce the wingtip vortex of an aileron tip, and then reduces induced drag.
Further, the outside along spanwise in joint wingtip section is fixed with swept-back triangle outer wing, this outer
The wing can effectively absorb wingtip vortex produced by joint wingtip section, reduces induced drag so that this have wingtip cascaded structure
Combine the connection of wingtip section and the wing is superimposed the connection of parallel connection up and down than existing wing tip and the wing increased and produces the effective of lift effect
The span, becomes the high-lift high-strength structure of induced drag very little, and, the wing root chord length of the outer wing of this swept-back triangle
Larger, larger lift contribution can be played.
Further, by coupling end plate, outer wing is fixed together with combining wingtip section, is convenient for assembling and changes.
Further, top wing section is the insertion wing section being arranged in back along spanwise insertion, so permissible
Reduce the impact to wing flow field for the fuselage as far as possible, improve the efficiency that wing produces lift.
Further, the inner wing root of insertion wing section and two split air conditioner wing panels be more than in the spacing on vertical up and down described
The chord length of insertion wing section, by making both at a distance of setting spacing, and then can to reduce insertion wing section be under top wing section
Surface and two split air conditioner wing panels are the aerodynamic interference between the upper surface of lower wing section.
Brief description
Fig. 1 is the structural representation of the aircraft in prior art with joint wing；
Fig. 2 is the top view of aircraft shown in Fig. 1；
Fig. 3 is the side view of aircraft shown in Fig. 1；
Fig. 4 is a kind of structural representation of embodiment of aircraft provided by the present invention；
Fig. 5 is the top view of aircraft shown in Fig. 4；
Fig. 6 is the side view of aircraft shown in Fig. 4；
Fig. 7 is the structural representation of wing in Fig. 4；
Fig. 8 is the top view of wing shown in Fig. 7；
Fig. 9 is the side view of wing shown in Fig. 7；
Figure 10 is the structural representation of the embodiment 2 of wing provided by the present invention；
Figure 11 is the top view of wing shown in Figure 10；
Figure 12 is the side view of wing shown in Figure 10；
Figure 13 is the structural representation of the embodiment 3 of wing provided by the present invention；
Figure 14 is the top view of wing shown in Figure 13；
Figure 15 is the side view of wing shown in Figure 13.
Specific embodiment
As shown in Fig. 4 to Fig. 9, a kind of embodiment of aircraft, in this embodiment, aircraft includes fuselage 1, and fuselage 1 is provided with machine
The wing, and unlike wing of the prior art：Wing in the present embodiment include having upper and lower wing section joint wing and
It is arranged on the outer wing 4 in the outside along spanwise of joint wing, the top wing section 2 of joint wing and lower wing section 3 are respectively
Stretch out along spanwise, and top wing section 2 is located at the front of lower wing section 3, top wing section 1 is for passing through along spanwise
The logical insertion wing section being arranged in back, the two ends wingtip along spanwise arrangement of insertion wing section is described upper machine
The wingtip of wing panel 2, and lower wing section 3 then includes being distributed in two split air conditioners of described fuselage both sides along described spanwise correspondence
Wing panel, the inner wing root along spanwise arrangement of two split air conditioner wing panels is used for being fixedly connected in described underbelly, two points
The outer end wingtip along spanwise arrangement of body wing section is the wingtip of described lower wing section 3, and in the present embodiment, described is upper
The wingtip chordwise tandem of the wingtip of wing section 2 and lower wing section 3 is connected composition joint wingtip section 5 so that described
The fuselage of upper and lower wing Duan Keyu aircraft forms double triangle structure, chordwise is defined as fore-and-aft direction, positioned at front side
The trailing edge of the wingtip of top wing section 2 is connected with the leading edge of the wingtip of the lower wing section 3 positioned at rear side.
In the present embodiment, outer wing 4 is swept-back triangle outer wing, and outer wing 4 is connected in joint wingtip section 5 by coupling end plate
The outside along spanwise, connection end plate and connected, the wing chord side at the wing root of swept-back triangle outer wing that combines wingtip section 5
To consistent with the chordwise of the wingtip of described upper and lower wing section.And, outer wing 4 i.e. can be in aircraft for folding outer wing
When depositing, outer wing is folded up to reduce the space of aircraft occupancy.
In the present embodiment, insertion wing section as top wing section 2 and equal as two split air conditioner wing panels of lower wing section 3
For etc. chord length RECTANGULAR WINGS, and the chordwise of the insertion wing section position corresponding with the inner wing root of two split air conditioner wing panels
The spacing of the inner wing root of place and described two split air conditioner wing panels is more than the chord length of described insertion wing section.
In order to reduce the aerodynamic interference between the lower surface of top wing section and the upper surface of lower wing section, insertion wing section with
The inner wing root of two split air conditioner wing panels is more than the chord length of described insertion wing section in the spacing on up and down vertically.
In the aircraft that the present embodiment is provided, upper and lower wing section forms connection wing structure, and the wingtip edge of upper and lower wing section
Chordwise dislocation series connection is connected and constitutes joint wingtip section, and the wingtip vortex of the wingtip generation of such top wing section is then by lower wing section
Wingtip intercept and capture comb stream, theoretical according to modern nearly Coupling Design, can be to rear positioned at wingtip vortex produced by the wingtip of front side
Wingtip produces lift upwards, improves the efficient wing span for providing lift of this wing structure.And, in connection wing structure
Wingtip vortex produced by joint wingtip section can be absorbed by the swept-back triangle outer wing set by outside, reduces induced drag,
This connection wing structure with joint wingtip section is made to become the minimum high-lift high-strength structure of induced drag.
Aircraft wing in the present embodiment is the embodiment 1 of wing, introduces flying of two kinds of different wing shapes further below
Machine wing embodiment.
Embodiment 2：
As shown in Figure 10 to Figure 12, the present embodiment provides the enforcement of a kind of aircraft wing, this aircraft wing and above-mentioned aircraft
It is the wing shapes of wing, the first top wing section 21 of the joint wing in the present embodiment, the in place of main difference in example
One lower wing section 31 is the tapered airfoil more than the chord length of wingtip for the chord length of wing root, although the first top wing section 21 is also to pass through herein
Logical wing section, but, the wing root 210 of this first top wing section 21 is located at the middle part of insertion wing section.Now, upper and lower wing section
Outer end wingtip the be connected wing chord of formed joint wingtip section of tandem that misplaces be less than wing root chord length and the lower wing of top wing section
The wing root chord length sum of section, the connection wing structure of this structure mixes less first outer wing 41 of area, suitable transport task again.
Embodiment 3：
As shown in FIG. 13 to 15, the present embodiment provides the enforcement of a kind of aircraft wing, this aircraft wing and above-mentioned aircraft
It is the wing shapes of wing, the second top wing section 22 of the joint wing in the present embodiment, the in place of main difference in example
Two lower wing sections 32 are the tapered airfoil less than the chord length of wingtip for the chord length of wing root, although the second top wing section 22 is also to pass through herein
Logical wing section, but, the wing root 220 of the second top wing section 22 is located at the middle part of insertion wing section.Now, upper and lower wing section
The wing chord of connected the formed joint wingtip section of outer end wingtip dislocation tandem is more than wing root chord length and the lower wing section of top wing section
Wing root chord length sum, this structure connection wing structure mix the second larger outer wing 42 of area again, be suitable for high motor-driven task.
From above-described embodiment as can be seen that mixing suitable area again by the suitable wing shapes changing upper and lower wing section
Outer wing so that this Connected wing aircraft adapts to different performance requirements.
In above-described embodiment, top wing section is located at the front of lower wing section, in other embodiments it is also possible to by top wing
Section is arranged on the rear of lower wing section, as long as making wingtip chordwise connected formation of dislocation tandem of upper and lower wing section combine
Wingtip section.
In the embodiment of above-mentioned aircraft and wing, outer wing is horizontally disposed, and in other embodiments, outer wing can also upwarp.
In above-described embodiment, it is provided with connection end plate and outer wing outside joint wingtip section, certainly, in other embodiment
In it is also possible to remove outer wing, and only retain joint wingtip section, equally can be using positioned at lift vortex produced by the wingtip in front
The wingtip that stream is pointed to rear produces the useful lift chord that lift effect improves whole connection wing structure.
Claims (8)
1. a kind of aircraft wing, including being respectively used to the upper and lower wing section stretching out along spanwise that is connected on fuselage,
It is characterized in that：The wingtip chordwise dislocation tandem of the wingtip of top wing section and lower wing section is connected and constitutes joint wingtip section
So that the fuselage of described upper and lower wing Duan Keyu aircraft forms double triangle structure, chordwise is defined as front and back
To the trailing edge of the wingtip positioned at front side is connected with the leading edge of the wingtip positioned at rear side；Described joint wingtip section along span side
To outside be fixed with swept-back triangle outer wing, the chordwise at the wing root of swept-back triangle outer wing is upper and lower with described
The chordwise of the wingtip of wing section is consistent.
2. aircraft wing according to claim 1 it is characterised in that：Described joint wingtip section outer along spanwise
Side is fixed with connection end plate, and described swept-back triangle outer wing is passed through connection end plate and is connected with described wingtip section of combining.
3. aircraft wing according to claim 1 and 2 it is characterised in that：Described top wing section is located at lower wing section
Front, the wing shapes of described upper and lower wing section adopt following one of which schemes：
（1）Described upper and lower wing section such as is at the RECTANGULAR WINGS of chord length, and the chord length of upper and lower wing section is equal；
（2）Described upper and lower wing section is the tapered airfoil that wing root chord length is more than wing tip chord length；
（3）Described upper and lower wing section is the tapered airfoil that wing root chord length is less than wingtip chord length.
4. aircraft wing according to claim 1 and 2 it is characterised in that：Described top wing section is located at lower wing section
Front, top wing section is the insertion wing section for being arranged in back along spanwise insertion, insertion wing section along the wing
The two ends wingtip of exhibition direction arrangement is the wingtip of described top wing section, and lower wing section includes distribution corresponding along described spanwise
In two split air conditioner wing panels of described fuselage both sides, the outer end wingtip along spanwise arrangement of two split air conditioner wing panels is institute
State the wingtip of lower wing section, the inner wing root along spanwise arrangement of two split air conditioner wing panels is used for being fixedly connected in described fuselage
Bottom.
5. aircraft wing according to claim 4 it is characterised in that：Described insertion wing section and two split wings
The RECTANGULAR WINGS of the chord lengths such as Duan Junwei, insertion wing section is more than in the spacing on up and down vertically with the inner wing root of two split air conditioner wing panels
The chord length of described insertion wing section.
6. a kind of aircraft, including fuselage with the upper and lower wing section that is connected on fuselage and stretches out along spanwise respectively, its
It is characterised by：The wingtip of top wing section and lower wing section wingtip chordwise dislocation tandem be connected constitute joint wingtip section with
Make described upper and lower wing section form double triangle structure with described fuselage, chordwise is defined as fore-and-aft direction, positioned at front
The trailing edge of the wingtip of side is connected with the leading edge of the wingtip positioned at rear side；The outside along spanwise of described joint wingtip section is solid
It is connected with swept-back triangle outer wing, the wing of the chordwise at the wing root of swept-back triangle outer wing and described upper and lower wing section
The chordwise of the tip is consistent.
7. aircraft according to claim 6 it is characterised in that：Described top wing section is located at the front of lower wing section, on
Wing section is the insertion wing section for being arranged in back along spanwise insertion, insertion wing section along spanwise cloth
The two ends wingtip put is the wingtip of described top wing section, and lower wing section includes being distributed in described machine along described spanwise correspondence
Two split air conditioner wing panels of body both sides, the outer end wingtip along spanwise arrangement of two split air conditioner wing panels is described lower wing
The wingtip of section, the inner wing root along spanwise arrangement of two split air conditioner wing panels is used for being fixedly connected in described underbelly.
8. aircraft according to claim 7 it is characterised in that：Described insertion wing section and two split air conditioner wing panels are
Etc. the RECTANGULAR WINGS of chord length, at the chordwise of the insertion wing section position corresponding with the inner wing root of two split air conditioner wing panels with
The spacing of the inner wing root of described two split air conditioner wing panels is more than the chord length of described insertion wing section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510225888.3A CN104875873B (en) | 2015-05-06 | 2015-05-06 | A kind of aircraft wing with aerodynamic arrangement and the aircraft using this wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510225888.3A CN104875873B (en) | 2015-05-06 | 2015-05-06 | A kind of aircraft wing with aerodynamic arrangement and the aircraft using this wing |
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| CN104875873A CN104875873A (en) | 2015-09-02 |
| CN104875873B true CN104875873B (en) | 2017-03-01 |
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| CN201510225888.3A Active CN104875873B (en) | 2015-05-06 | 2015-05-06 | A kind of aircraft wing with aerodynamic arrangement and the aircraft using this wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108725750B (en) * | 2018-04-28 | 2020-07-14 | 昆明鞘翼科技有限公司 | Method for improving vertical take-off and landing and flight control of aircraft by using slightly smaller wings |
| CN112455699B (en) * | 2020-11-13 | 2024-01-02 | 中国航空工业集团公司沈阳飞机设计研究所 | High-fusion aircraft rear body |
| CN112607025A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | High-aspect-ratio and high-strength double-layer wing solar unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US6886778B2 (en) * | 2003-06-30 | 2005-05-03 | The Boeing Company | Efficient wing tip devices and methods for incorporating such devices into existing wing designs |
| CN101254753A (en) * | 2007-02-28 | 2008-09-03 | 西北工业大学 | A solar powered drone |
| DE102007059455A1 (en) * | 2007-12-10 | 2009-06-25 | Airbus Deutschland Gmbh | Wingtip extension to reduce wake turbulences on airplanes |
| ES2377637B1 (en) * | 2009-04-07 | 2013-02-28 | Airbus Operations, S.L. | PLANE WITH ALAR CONFIGURATION IN LAMBDA BOX. |
| DE102010048139A1 (en) * | 2010-10-11 | 2012-04-12 | Eads Deutschland Gmbh | Aircraft with variable geometry |
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