CN105905277A - Air vehicle aerodynamic configuration with trailing edge supporting wing - Google Patents
Air vehicle aerodynamic configuration with trailing edge supporting wing Download PDFInfo
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- CN105905277A CN105905277A CN201610245406.5A CN201610245406A CN105905277A CN 105905277 A CN105905277 A CN 105905277A CN 201610245406 A CN201610245406 A CN 201610245406A CN 105905277 A CN105905277 A CN 105905277A
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/04—Noseplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/08—Stabilising surfaces mounted on, or supported by, wings
Abstract
The invention discloses an air vehicle aerodynamic configuration with two trailing edge supporting wings. The supporting wings are installed below trailing edges of main wings at the two sides of a fuselage of an air vehicle. Wingtips of the supporting wings are connected to the middle parts of the trailing edges of the wings through connection sections. Wing roots of the supporting wings are connected to the fuselage through connection sections. The relative positions of the supporting wings and the main wings are reasonably designed. In a main wing cross section and a supporting wing cross section which are truncated by air flowing to a vertical plane in wingspans of the support wings upwardly during the flying process, the vertical distance between the centroids is a% of the chord length of the cross section of the main wing, wherein a is a constant value from 10 to 40; and meanwhile, the overlapping length of projections of the chord lines of the main wing cross section and the supporting wing cross section on a horizontal plane is b% of the chord length of the cross section of the main wing, wherein b is a constant value from 0 to 15. The aerodynamic configuration increases the total lift-drag ratio and achieves better aerodynamic performances, and also improves the rigidity of large-span-chord ratio wings and improves the total structural efficiency of the air vehicle.
Description
Technical field
The invention belongs to aerodynamic configuration of aircraft design field, be specifically related to a kind of aircraft gas using the rear edge support wing
Dynamic layout.
Background technology
Pursue one of high lift-drag ratio main target being always aviation aircraft design.Subsonic speed normal arrangement is consolidated
For determining rotor aircraft, owing to wing is its main lift member, thus when design in order to obtain higher liter resistance
Ratio, it will usually use the way increasing wing aspect ratio.The advantage of high aspect ratio wing is: when aircraft flight speed
When spending relatively low, for having the wing of same lift face area, bigger aspect ratio is used to be conducive to reducing luring of wing
Lead resistance, obtain higher lift-drag ratio with this.
But, owing to the length of high aspect ratio wing is much greater compared to wing thickness and chord length, thus may deposit
In exhibition to the problem of rigidity of structure deficiency.In flight course, wing can occur elastic deformation under the effect of aerodynamic force,
This elastic deformation makes the most again aerodynamic force change therewith, forms malformation and the interactive pneumatic bomb of aerodynamic force
Property phenomenon.The maneuverability of aircraft and stability can be made a significant impact by aeroelasticity, can make structural deterioration time serious
Or cause aircraft accident.If directly using the mode strengthening wing internal structure, then can make the construction weight of wing significantly
Increase, reduce payload and the structure efficiency of whole aircraft.
For solving the Rigidity of above-mentioned high aspect ratio wing, NASA is the most green with the subsonic speed that Boeing cooperation is carried out
Aircraft research (SUGAR) proposes a kind of side under the wings of an airplane and adds the layout of sub-truss.This layout comprises
Single-blade, fuselage, couple wing and fuselage, in order to share the main support of wing bending load, and couple wing and
Main support vertical rack.Main support is positioned in the middle part of wing with the tie point of wing, and the position of main support is in wing
Underface.The method of this interpolation sub-truss, compared to the mode of reinforcement wing internal structure, can be substantially reduced machine
The construction weight that the wing is overall, improves payload and the structure efficiency of aircraft.But, the sub-truss of interpolation can be made
The lift-drag ratio becoming aircraft overall reduces, and reduces its pneumatic efficiency.Although wing and sub-truss have passed through the excellent of aerofoil profile
Change design, it is possible to make up certain aerodynamic loss, but according to the experience of double-vane Flight Vehicle Design, immediately below single-blade
Arrange lifting surface, under its pneumatic efficiency is the most relatively low.
Summary of the invention
The present invention can obtain from the angle of pneumatic design, the trailing edge being positioned at top wing according to lower wing in double-vane layout
More preferable aeroperformance, and add sub-truss and can strengthen single-blade exhibition to rigidity, reduce wing structure weight and
Improve the technical experience of aircraft payload, it is proposed that a kind of aerodynamic configuration of aircraft using the rear edge support wing, for
There is the aerodynamic configuration of aircraft of high aspect ratio wing and provide a kind of structural behaviour and the most outstanding skill of aeroperformance
Art scheme.
Aerodynamic configuration of aircraft of the present invention, installs braced wing below the main wing trailing edge of aircraft fuselage both sides.Braced wing
Wing tip is connected with in the middle part of trailing edge by streamlined wing tip linkage section, and the wing root of braced wing is connected by streamlined wing root
Section is connected with fuselage.
Support the most each main wing cross section intercepted along air flow direction vertical guide during aircraft flight of the span with
In support wing section, the main wing cross section chord length that the vertical direction distance between the centre of form is a%, and a is definite value, 10～40
In the range of；Having lap between the leading edge of braced wing and the trailing edge of main wing, design supports the most each edge of the span simultaneously
The main wing cross section that during aircraft flight, air flow direction vertical guide is intercepted and the string of a musical instrument in braced wing cross section are in level
The main wing cross section chord length that overlap length is b% of projection on face, b is definite value, in the range of 0～15.
It is an advantage of the current invention that:
1, the present invention uses the aerodynamic configuration of aircraft of the rear edge support wing, in structural behaviour, it is proposed that a kind of solution
Aerodynamic arrangement's scheme of high aspect ratio wing insufficient rigidity problem, it is possible to reduce the construction weight of wing, promotes aircraft
Overall payload and structure efficiency；
2, the present invention uses the aerodynamic configuration of aircraft of the rear edge support wing, on aeroperformance, the layout side of braced wing
Case can be by braced wing and wing dimension, relative position and the appropriate design of braced wing established angle, making wing whole
The lift-drag ratio when lift coefficient of body and Low Angle Of Attack gets a promotion, and makes it obtain close to the maximum without supporting single-blade layout
Lift-drag ratio, maintains the pneumatic efficiency that aircraft is overall.
3, the present invention uses the aerodynamic configuration of aircraft of the rear edge support wing, it is possible to reach to strengthen high aspect ratio straight wing
The purpose of rigidity, can enable aircraft take into account pneumatic efficiency and structure efficiency simultaneously.
Accompanying drawing explanation
Fig. 1 is aerodynamic configuration of aircraft overall schematic of the present invention；
Fig. 2 is aerodynamic configuration of aircraft entirety schematic top plan view of the present invention；
Fig. 3 is aerodynamic configuration of aircraft entirety schematic side view of the present invention；
Fig. 4 is aerodynamic configuration of aircraft unitary side front elevational schematic of the present invention；
Fig. 5 is to support the span in aerodynamic configuration of aircraft of the present invention upwardly along air flow direction lead during aircraft flight
The main wing that vertical plane is intercepted cut with in braced wing cross section, the vertical direction distance between the centre of form, and main wing cuts with braced wing
Face string of a musical instrument overlap length schematic diagram；
Fig. 6 a is that aerodynamic configuration of aircraft of the present invention contrasts with single-blade layout lift coefficient with angle of attack variation curve map；
Fig. 6 b is that aerodynamic configuration of aircraft of the present invention contrasts with single-blade layout lift-drag ratio with angle of attack variation curve map；
Fig. 7 a be aerodynamic configuration of aircraft of the present invention under two different angles of attack lift coefficient with main wing cross section and braced wing
Cross section established angle difference change curve；
Fig. 7 b for aerodynamic configuration of aircraft of the present invention under two different angles of attack lift-drag ratio with main wing cross section and braced wing
Cross section established angle difference change curve；
In figure:
1-main wing 2-fuselage 3-braced wing
4-wing tip linkage section 5-wing root linkage section
Detailed description of the invention
The present invention will be further described below in conjunction with the accompanying drawings.
In aerodynamic configuration of aircraft of the present invention, aircraft uses the straight main wing 1 of high aspect ratio, conventional cylindrical body fuselage
2, and there is the braced wing 3 at the bigger upper counterangle, as shown in figures 1-4.Wherein, main wing 1 is two, the most right
Claim to be arranged on fuselage 2 left and right sides.Braced wing 3 is two, is symmetrically arranged at fuselage both sides, lays respectively at two
Individual main wing 1 posterior border position, i.e. braced wing 3 are positioned at main wing 1 about the downstream carrying out flow path direction 8.The wing tip of braced wing 3
Being connected in the middle part of wing 1 trailing edge by streamlined wing tip linkage section 4, the wing root of braced wing 3 is by streamlined wing root even
The section of connecing 5 is connected with fuselage 2；And make the braced wing 3 cross section string of a musical instrument be positioned at the lower section of the main wing 1 cross section string of a musical instrument.Above-mentioned two
Main wing 1 is arranged as high mounted wing, and two braced wings 3 are arranged as lower single-blade, can make wing 1 and braced wing 3 and fuselage 2
During connection, it is to avoid fuselage 2 volume and structure are adversely affected.The cross section aerofoil profile of main wing 1 and braced wing 3 can root
According to the demand specific design of pneumatic design, but braced wing 3 open up upwards each along air flow direction during aircraft flight
Main wing 1 cross section that vertical guide is intercepted is with braced wing 3 cross section, and the chord length of braced wing 3 need to be less than the chord length of main wing 1.
Said two braced wing 3 is closely related with aircraft entirety aeroperformance with the concrete relative position of main wing 1, needs
Requirement according to pneumatic design determines, specifically determines that mode is: for the wing 1 of high aspect ratio, owing to its exhibition is to stream
Dynamic can ignore, therefore between main wing 1 with braced wing 3, determination relative to position can be analyzed according to two-dimensional case, leads to
Cross the available aircraft entirety lift-drag ratio of simulation, when lift-drag ratio maximum, be between main wing cross section and braced wing cross section
Excellent relative position.Design braced wing 3 is opened up the most each along air flow direction vertical guide institute during aircraft flight subsequently
In main wing 1 cross section intercepted and braced wing 3 cross section, the main wing 1 cross section string that the vertical direction distance between the centre of form is a%
Grow, and a is definite value, in the range of 10～40.Have overlapping between the leading edge of braced wing 3 with the trailing edge of main wing 1 simultaneously
Part, design braced wing 3 opens up the most each main wing 1 intercepted along air flow direction vertical guide during aircraft flight
The overlap length L that cross section projects in the horizontal plane with the string of a musical instrument in braced wing 3 cross section2For the main wing 1 cross section chord length of b%,
B is definite value, in the range of 0～15.Finally expanding in three-dimensional case, be supported the wing 3 configuration, as shown in Figure 4.
Above-mentioned braced wing 3 may be designed as identical or different with main wing 1 established angle, at braced wing 3 and main wing 1 established angle
Time different so that braced wing 3 has the angle of attack being different from main wing 1 under aircraft flight state, fly in the present invention
Under device aerodynamic arrangement, select suitable braced wing 3 established angle, it is possible in the range of large angles of attack, promote aircraft overall
Aeroperformance.
Embodiment 1: main wing 1 and braced wing 3 all use Clark-Y aerofoil profile；The chord length of main wing 1 is 2m,
The chord length reference length of the support wing 3 is 1m；In the model of braced wing 3 design braced wing 3 open up upwards each along aircraft
Main wing 1 cross section that in flight course, air flow direction vertical guide is intercepted and the vertical side in braced wing 3 cross section, between the centre of form
To the main wing 1 cross section chord length that distance is 10%, and the main wing 1 cross section string of a musical instrument with braced wing 3 cross section string of a musical instrument overlap length is
The main wing 1 cross section string of a musical instrument of 11%.Fig. 6 a, 6b sets forth above-mentioned braced wing 3 layout and in contrast to unsupported single-blade
Layout lift coefficient, lift-drag ratio are with the two-dimension analysis curve of angle of attack variation, and wherein the lift of braced wing layout is both wings liter
Power sum, braced wing 3 is all taken as 1m with the reference length of single-blade.It can be seen that compared to single-blade layout, when this
When in invention, the braced wing 3 of layout is positioned at rational position, the lift coefficient making layout overall is obviously improved, and make its
Lift-drag ratio during Low Angle Of Attack improves, and makes its maximum lift-drag ratio close to unsupported single-blade layout simultaneously.This illustrates this
Bright braced wing layout is obtained in that the pneumatic efficiency more excellent than single-blade layout when appropriate design.
Embodiment 2: main wing and braced wing all use Clark-Y aerofoil profile；The chord length of main wing is 2m, the string of braced wing
A length of 1m；The model of braced wing 3 designs braced wing 3 open up upwards each along air flow direction during aircraft flight
In main wing 1 cross section that vertical guide is intercepted and braced wing 3 cross section, the main wing that vertical direction distance is 40% between the centre of form
1 cross section chord length, and the main wing 1 cross section string of a musical instrument that the main wing 1 cross section string of a musical instrument and braced wing 3 cross section string of a musical instrument overlap length are 0%,
The most overlapping；Main wing 1 cross section established angle is φ1=0 °, braced wing 3 cross section established angle is φ2, then main wing
1 with braced wing 3 cross section install angular difference be Δ φ=φ2-φ1.Fig. 7 a, 7b sets forth above-mentioned braced wing 3 layout
The embodiment two-dimension analysis curve that its lift coefficient, lift-drag ratio change with Δ φ under two different angles of attack, wherein lift
The definition of coefficient is with embodiment 1.The angle of attack of layout entirety is respectively 0 ° and 8 °.It can be seen that when layout is overall
When the angle of attack is 0 °, lift coefficient and lift-drag ratio monotone increasing therewith in the range of sizable Δ φ；When the angle of attack is 8 °
Time, lift-drag ratio not change to Δ φ has monotonicity.This explanation can consider according to design requirement, with really
Determine the established angle of braced wing 3, make rear edge support wing layout overall obtain at bigger range of angles of attack more satisfactory pneumatic
Performance.
In sum, the present invention increases braced wing 3 by posterior border position below main wing 1, and to braced wing 3 with main
The relative position of the wing 1 carries out appropriate design, while strengthening high aspect ratio main wing 1 rigidity, it is possible to promote layout whole
The lift-drag ratio of body, it is thus achieved that preferably aeroperformance；Can reach to strengthen the purpose of the rigidity of high aspect ratio wing simultaneously,
Promote the structure efficiency that aircraft is overall.
Claims (6)
1. the aerodynamic configuration of aircraft using the rear edge support wing, it is characterised in that: aircraft fuselage both sides master
Braced wing is installed below wing trailing edge.
A kind of aerodynamic configuration of aircraft using the rear edge support wing the most as claimed in claim 1, it is characterised in that: main
The wing is arranged as high mounted wing, and braced wing is arranged as lower single-blade.
A kind of aerodynamic configuration of aircraft using the rear edge support wing the most as claimed in claim 1, it is characterised in that:
The wing tip of the support wing is connected with in the middle part of trailing edge by streamlined wing tip linkage section, and the wing root of braced wing passes through the streamlined wing
Root linkage section is connected with fuselage.
A kind of aerodynamic configuration of aircraft using the rear edge support wing the most as claimed in claim 1, it is characterised in that:
The support span upwards each main wing cross section intercepted along air flow direction vertical guide during aircraft flight is cut with braced wing
In face, the chord length of braced wing need to be less than the chord length of main wing.
A kind of aerodynamic configuration of aircraft using the rear edge support wing the most as claimed in claim 1, it is characterised in that:
The most each main wing cross section intercepted along air flow direction vertical guide during aircraft flight of the support span is cut with braced wing
In face, the main wing cross section chord length that the vertical direction distance between the centre of form is a%, and a is definite value, in the range of 10～40；
Having lap between the leading edge of braced wing and the trailing edge of main wing, design supports that the span is the most each to fly along aircraft simultaneously
The main wing cross section that during row, air flow direction vertical guide is intercepted projects in the horizontal plane with the string of a musical instrument in braced wing cross section
The main wing cross section chord length that overlap length is b%, b is definite value, in the range of 0～15.
A kind of aerodynamic configuration of aircraft using the rear edge support wing the most as claimed in claim 1, it is characterised in that:
The support wing has the established angle being different from main wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610245406.5A CN105905277B (en) | 2016-04-19 | 2016-04-19 | A kind of aerodynamic configuration of aircraft using the rear edge support wing |
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| CN201610245406.5A CN105905277B (en) | 2016-04-19 | 2016-04-19 | A kind of aerodynamic configuration of aircraft using the rear edge support wing |
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| CN105905277A true CN105905277A (en) | 2016-08-31 |
| CN105905277B CN105905277B (en) | 2018-08-24 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107264774A (en) * | 2017-05-24 | 2017-10-20 | 北京航空航天大学 | A kind of M shape wings high subsonic flight device aerodynamic arrangement of use leading edge braced wing |
| CN107862128A (en) * | 2017-11-03 | 2018-03-30 | 张家港江苏科技大学产业技术研究院 | A kind of three dwell aircushion vehicle true angle of incidence degree acquisition methods |
| CN108502138A (en) * | 2018-03-26 | 2018-09-07 | 北京航空航天大学 | A kind of buzzard-type wing expanded letter high subsonic flight device aerodynamic arrangement using leading edge braced wing |
| CN109263856A (en) * | 2018-09-28 | 2019-01-25 | 北京航空航天大学 | High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement |
| CN109263855A (en) * | 2018-09-28 | 2019-01-25 | 北京航空航天大学 | A kind of super large aspect ratio aerodynamic configuration of aircraft using the rear edge support wing |
| CN109484622A (en) * | 2018-11-27 | 2019-03-19 | 北京航空航天大学 | A kind of high subsonic speed sweep wing aircraft aerodynamic arrangement using leading edge braced wing |
| CN113682469A (en) * | 2021-09-30 | 2021-11-23 | 北京航空航天大学 | Overall layout of small long-endurance unmanned aerial vehicle |
| JP2022016568A (en) * | 2020-02-27 | 2022-01-21 | 義郎 中松 | Wing rotation vertical takeoff/landing long distance aircraft |
| WO2023109154A1 (en) * | 2021-12-15 | 2023-06-22 | 北京航空航天大学宁波创新研究院 | Wing and method for improving control efficiency of two-dimensional airfoil rudder surface |
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| DE626386C (en) * | 1936-02-25 | Fritz Huth Dr | Aircraft tailplane | |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107264774B (en) * | 2017-05-24 | 2019-10-25 | 北京航空航天大学 | A kind of M shape wing high subsonic flight device aerodynamic arrangement using leading edge braced wing |
| CN107264774A (en) * | 2017-05-24 | 2017-10-20 | 北京航空航天大学 | A kind of M shape wings high subsonic flight device aerodynamic arrangement of use leading edge braced wing |
| CN107862128A (en) * | 2017-11-03 | 2018-03-30 | 张家港江苏科技大学产业技术研究院 | A kind of three dwell aircushion vehicle true angle of incidence degree acquisition methods |
| CN108502138A (en) * | 2018-03-26 | 2018-09-07 | 北京航空航天大学 | A kind of buzzard-type wing expanded letter high subsonic flight device aerodynamic arrangement using leading edge braced wing |
| CN109263856A (en) * | 2018-09-28 | 2019-01-25 | 北京航空航天大学 | High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement |
| CN109263855A (en) * | 2018-09-28 | 2019-01-25 | 北京航空航天大学 | A kind of super large aspect ratio aerodynamic configuration of aircraft using the rear edge support wing |
| CN109263856B (en) * | 2018-09-28 | 2020-07-03 | 北京航空航天大学 | Pneumatic layout of multipurpose carrier aircraft with large aspect ratio support wings and double aircraft bodies |
| CN109263855B (en) * | 2018-09-28 | 2020-12-29 | 北京航空航天大学 | Pneumatic layout of ultra-large aspect ratio aircraft adopting trailing edge supporting wings |
| CN109484622A (en) * | 2018-11-27 | 2019-03-19 | 北京航空航天大学 | A kind of high subsonic speed sweep wing aircraft aerodynamic arrangement using leading edge braced wing |
| JP2022016568A (en) * | 2020-02-27 | 2022-01-21 | 義郎 中松 | Wing rotation vertical takeoff/landing long distance aircraft |
| CN113682469A (en) * | 2021-09-30 | 2021-11-23 | 北京航空航天大学 | Overall layout of small long-endurance unmanned aerial vehicle |
| CN113682469B (en) * | 2021-09-30 | 2023-03-10 | 北京航空航天大学 | Overall layout of small long-endurance unmanned aerial vehicle |
| WO2023109154A1 (en) * | 2021-12-15 | 2023-06-22 | 北京航空航天大学宁波创新研究院 | Wing and method for improving control efficiency of two-dimensional airfoil rudder surface |
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