CN107264774A - A kind of M shape wings high subsonic flight device aerodynamic arrangement of use leading edge braced wing - Google Patents
A kind of M shape wings high subsonic flight device aerodynamic arrangement of use leading edge braced wing Download PDFInfo
- Publication number
- CN107264774A CN107264774A CN201710371758.XA CN201710371758A CN107264774A CN 107264774 A CN107264774 A CN 107264774A CN 201710371758 A CN201710371758 A CN 201710371758A CN 107264774 A CN107264774 A CN 107264774A
- Authority
- CN
- China
- Prior art keywords
- wing
- main wing
- braced
- main
- leading edge
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of high subsonic flight device aerodynamic arrangement of the M shape wings of use leading edge braced wing, belong to aerodynamic configuration of aircraft design field.Described aerodynamic arrangement includes fuselage, main wing and braced wing, and described main wing is divided into main wing inner segment and outer two sections of the section of main wing, is high mounted wing, and main wing inner segment sweepforward, the outer section sweepback of main wing is overlooked in M types；Braced wing one end connects and composes low-wing configuration with belly, and the other end is connected with main wing internal and external section junction；Braced wing also has angle of sweep, and its angle of sweep is more than the angle of main wing inner segment sweepforward.The present invention can significantly reduce the construction weight of wing, make payload and the conevying efficiency lifting of aircraft.From the point of view of pneumatic, the layout can obtain the aspect ratio bigger than normal arrangement under equal material horizontal.The aircraft span being laid out using braced wing is significantly greater than existing civil aircraft.In addition, by the reasonable Arrangement to leading edge braced wing position, the lifting resistance characteristic of wing can be made to be in preferable position, close to the pneumatic efficiency level without braced wing aerodynamic effects.
Description
Technical field
The invention belongs to aerodynamic configuration of aircraft design field, and in particular to a kind of M shapes of use leading edge braced wing
The high subsonic flight device aerodynamic arrangement of the wing.In main wing front lower place, certain distance arrangement braced wing is increased with reducing unfavorable aerodynamic interference
Plus wing intensity and then increase aspect ratio, aircraft is possessed the aerodynamic configuration of aircraft compared with high lift-drag ratio in high subsonic speed.
Background technology
High subsonic speed jet passenger aircraft has become one of main traffic means of transport in the world.Boeing in 2003
Company once carried out prediction to World Airways traffic growth rate, it is believed that carriage of passengers by air average growth rate per annum is 5.1%, shipping year
Equal growth rate is 6.4%.If the pneumatic efficiency of high subsonic speed civil jet can be lifted on the basis of existing, obtain
Economic interests will be huge.But the pneumatic design of modern civil aircraft is frequently not the optimum point in pneumatic design,
But the equalization point in pneumatic design and structural strength.Common wing is usually cantilever beam form, i.e., whole section wing is direct
It is connected in airfoil root and fuselage.This structure arrangement is limited by the strength of materials and rigidity, and the maximum aspect ratio of wing is not
Can be too high, wing otherwise can be made to be influenceed to produce larger dynamic elasticity deformation, i.e. Aeroelastic Problems by aerodynamic loading.It is this existing
As influence flight quality even makes wing fracture.In order to increase structural strength, its wing thickness is generally thicker, adds high infrasound
Fast drag due to shock wave, adds construction weight, and Flight Vehicle Structure efficiency is substantially reduced.
Braced wing layout is a kind of wing configurations for being connected to fuselage somewhere with a braced wing in host wing stage casing.Support
The connection of the wing effectively enhances the structural strength of wing, improves the aeroelasticity feature of wing.1996 to 2001, Fu Ji
Ni Ya Polytechnics has been carried out extensively under NASA subsidy using multidisciplinary design optimization method to transonic speed braced wing layout aircraft
General, system feasibility study.As a result show, braced wing layout allows wing to enter one on the premise of weight and thickness is not increased
Step increase length, reduces induced drag.The rationally distributed structure arrangement of braced wing makes the relatively conventional wing of wing thickness more
It is small, transonic speed drag due to shock wave can be effectively reduced.For air mileage under 325 passengers, cruise Ma=0.85 can be loaded
13890km flight section, braced wing layout aircraft is light than conventional aircraft takeoff gross weight by 9.2%~
17.4%, fuel consumption few 16.2%~19.3%, engine volume reduction 21.5%~31.6%, cost reduction by 3.8%~
7.2%.With the increase of voyage, more advantage of low cost will be highlighted more, it is taken as that the layout is suitably applied long voyage fortune
Defeated machine.
But new problem occurs therewith, braced wing can also produce aerodynamic lift and resistance, and its interference to air-flow also can be right
The lifting resistance characteristic of host wing is impacted.Existing braced wing placement scheme is general as shown in figure 8, braced wing and main wing are from top view
Direction is looked overlapping larger, is occurred the air between strong unfavorable interference, upper lower aerofoil between both wings and is formd local two dimension spray
Pipe flows, and air-flow easily forms intense shock wave at area minimum, reduces airplane ascensional force, adds resistance, noise, makes aircraft
Lift-drag ratio is greatly reduced.The braced wing distribution form of this underface support has larger defect.
Therefore, explore a kind of rational, efficient braced wing layout is for improving high subsonic flight device pneumatic efficiency
It is highly important.
The content of the invention
The present invention is from pneumatic design angle, it is proposed that a kind of high subsonic flight of the M shape wings of use leading edge braced wing
Device aerodynamic arrangement.The layout by rationally designing the relative position of leading edge braced wing and main wing and the sweepback arrangement form of main wing,
The overall lift-drag ratio of layout can be lifted, preferable aeroperformance is obtained；Enhancing wing rigidity is realized simultaneously, increase wing exhibition
String than purpose, the design of braced wing improves Flight Vehicle Structure efficiency；Present invention layout for high subsonic speed civil transport and
Passenger plane provides a kind of structure efficiency and pneumatic efficiency very outstanding solution.
Present invention layout takes traditional cylinderical fuselage.Main wing employs larger aspect ratio, and uses shoulder-wing configuration.
Main wing is divided into inside and outside two sections, main wing inner segment sweepforward, and the outer section of main wing is with the sweepforward angle sweepback more than main wing inner segment, therefore from vertical view
Figure direction sees that M shapes are presented in main wing.The sweepforward of the main wing and sweepback angle can play a part of improving critical Mach number, reduction
The high velocity of sound, transonic speed when flight resistance.The specific size of front/rear sweep angle is determined that cruise Mach by aircraft cruise Mach number
Number is bigger, and front/rear sweep angle is bigger, and the sweepforward angle and sweepback angular region typically chosen are no more than 45 °.Swept-back wing wing it is pneumatic
Elastic performance is better than buzzard-type wing, but its wingtip air-flow is first separated, and is lost effectiveness of aileron, is reduced maximum lift coefficient.And
Buzzard-type wing is that wing root air-flow is first separated, it is ensured that the available lift of aircraft.Buzzard-type wing can also reduce the induced drag of aircraft, carry
High aircraft slope of lift curve.The shortcoming of buzzard-type wing is that aeroelastic divergence problem occurs in wing.Aircraft layout branch of the present invention
The connection of the support wing avoids the Aeroelastic Problems of buzzard-type wing, and the outer section sweepback of main wing fully combines both preceding swept-back wings in gas
The dynamic, advantage of construction applications simultaneously avoids inferior position.
Braced wing has the upper counterangle, and one end connects and composes low-wing configuration, the other end and main wing internal and external section with belly
Junction is connected.Above connected mode is constrained support wing dihedral angle, and its concrete numerical value will be by fuselage upper-lower height, branch
The length of the support wing is together decided on.Braced wing also has angle of sweep, and its angle of sweep degree is more than the main wing inner segment sweepforward angle of design code
Degree.The overlapping region of braced wing and main wing is less as viewed from top view direction, only braced wing and leading edge of a wing junction have compared with
It is few overlapping.
The advantage of the invention is that：
The present invention proposes a kind of topology layout for solving the problems, such as wing insufficient rigidity and aerodynamic arrangement's scheme.Program energy
The construction weight of wing is enough significantly reduced, makes payload and the conevying efficiency lifting of aircraft.From the point of view of pneumatic, the cloth
Office can obtain the aspect ratio bigger than normal arrangement under equal material horizontal.The aircraft span being laid out using braced wing
Significantly greater than existing civil aircraft.In addition, it by the reasonable Arrangement to leading edge braced wing position, can hinder the liter of wing
Characteristic is in preferable position, close to the pneumatic efficiency level without braced wing aerodynamic effects.
Brief description of the drawings
Fig. 1 a, Fig. 1 b, Fig. 1 c, Fig. 1 d are respectively to be laid out axonometric drawing using the M shapes rotor aircraft of leading edge braced wing, overlook
Figure, side view, front view；
Fig. 2 is braced wing and host wing relative position diagrammatic cross-section.
Fig. 3 is braced wing and host wing relative rotation diagrammatic cross-section.
Fig. 4 is braced wing of the present invention layout and traditional civil aircraft (MD-80) overlapping contrast's top view.
Fig. 5 be in embodiment 1 with length without braced wing and having the overall lift-drag ratio of braced wing with braced wing and main wing water
The change curve of flat distance (s).
Fig. 6 is the overall lift-drag ratio of braced wing of varying level distance in embodiment 2 with the vertical height of braced wing and main wing
(g) change curve.
Fig. 7 is that the overall lift-drag ratio of braced wing of varying level distance in embodiment 3 is installed with the wing of braced wing and main wing
The change curve of the difference at angle (d).
Fig. 8 is upward view, top view and the front view that the traditional support wing is laid out.
In figure：
1. fuselage；2. main wing inner segment；3. the outer section of main wing；4. braced wing；5. engine；6. vertical tail；7. tailplane.
Embodiment
The present invention is further described below in conjunction with the accompanying drawings.
The high subsonic flight device layout of the leading edge braced wing M shape wings that the present invention is provided, with reference to Fig. 1 a, Fig. 1 b, Fig. 1 c and figure
1d, main fuselage 1, main wing, braced wing 4, vertical tail 6 and the tailplane 7 for including conventional in layout, described main wing is divided into small
The main wing inner segment 2 of angle sweepforward and outer 3 two sections of the section of the main wing of low-angle sweepback, wherein, sweepback angle is more than sweepforward angle.It is described
Braced wing 4 is connected to main wing inner segment 2 and outer section 3 of intersection.Described braced wing 4, main wing inner segment 2 and main wing outer section 3 is cutd open
Face is aerofoil profile, and its respective aerofoil profile can be individually determined or design as needed.In the layout, main wing inner segment 2 and the outer section 3 of main wing
For high mounted wing, braced wing 4 is lower single-blade.This arrangement can avoid having a negative impact to the volume of fuselage 1 and structure.Institute
State the leading edge that braced wing 4 is connected to main wing inner segment 2, rather than traditional be connected in the middle part of main wing chord length.
The braced wing of the present invention has the upper counterangle, and one end connects and composes low-wing configuration, the other end and master with belly
Wing internal and external section junction is connected.Braced wing also has angle of sweep, and its angle of sweep degree is more than the main wing inner segment sweepforward angle of design code
Degree.As shown in figure 4, the overlapping region of braced wing and main wing is less as viewed from top view direction, only in braced wing and the leading edge of a wing
Junction has less overlapping, and M shapes layout is presented in top view direction for main wing.
Numerical result shows, under the conditions of high subsonic speed, when braced wing 4 is outside main wing inner segment 2 and main wing before section 3
Side, and the slave span to section see that the leading edge of braced wing 4 and the leading edge horizontal range of main wing inner segment 2 are more than or equal to main wing inner segment 2
During 1.0 times of chord lengths or so, unfavorable aerodynamic interference is weak between double-vane (braced wing and main wing), lift-drag ratio close to it is noiseless when liter
Resistance ratio.Also preferable in the structural strength of this horizontal range lower wing integral layout, pneumatic efficiency and structure efficiency reach
Preferable level.If further increase wing opens up the leading edge level of braced wing 4 and main wing inner segment 2 into section on this basis
Distance, then lift-drag ratio is by lift-drag ratio when more leveling off to noiseless.The horizontal range being laid out due to braced wing is from braced wing
Root is to gradually become 0 by a particular value to taper, should increase by 1.0 times of strings that horizontal range is more than or equal to main wing inner segment 2
The proportion of long part, reducing both wings intersection as far as possible, (i.e. horizontal range is less than 1.0 times of chord lengths of main wing inner segment 2
Part) proportion.Result of the test is shown, under high subsonic speed environment, if by the strong point on the fuselage 1 of braced wing 4 or
Tie point is arranged in the rear portion of main wing inner segment 2, forms rear edge support layout, then the leading edge of braced wing 4 and the leading edge of main wing inner segment 2
Distance to reach that five times of chord lengths of main wing inner segment 2 can be only achieved the effect of leading edge braced wing, now Fabric utilization and structure are strong
Degree is not as leading edge braced wing layout.
As shown in Figure 1 b, the link position of braced wing 4 on the fuselage 1 is located at main wing inner segment 2 in the layout that the present invention is provided
To flow front.For high aspect ratio wing, air current flow can regard two-dimensional flow as.Therefore from the point of view of two dimensional cross-section,
The relative position control parameter of braced wing 4 and main wing inner segment 2 can be defined as two, i.e. horizontal range s and vertical range g.Such as
Shown in Fig. 2, define horizontal range s be along wing open up to section in both aerofoil profile leading edges horizontal direction distance, vertical range g
For along wing open up to section in both aerofoil profile leading edges vertical direction distance.Horizontal range s is not therewith yet in different sections
Together.Beyond a small number of join domains for removing braced wing 4 and main wing inner segment 2, more than the part master of 80% main wing inner segment span-wise length
The wing-braced wing is extended should be greater than being equal to 1.0 times of chord lengths of main wing inner segment 2 to the horizontal range s of section.Vertical range g is high by fuselage 1
Degree determines that vertical range g influences very micro- to lifting resistance characteristic in the case where horizontal range s is more than 1.0 times of chord lengths of main wing inner segment 2
It is weak.Therefore, preferable aeroperformance can be kept on the basis of this geometrical relationship.
The M shape rotor aircrafts aerodynamic arrangement of described use leading edge braced wing, with reference to Fig. 3, braced wing 4 may be designed as and master
The wing has the difference that d in different established angles, Fig. 3 is braced wing established angle and main wing inner segment established angle, referred to as decalage.Its mesh
Be braced wing 4 is had the angle of attack different from section 3 outside main wing inner segment 2 and main wing under state of flight.The layout is from conjunction
During suitable decalage d, the overall aeroperformance of aircraft can be lifted.For different aerofoil profiles, different braced wing arrangement ginsengs
For number, decalage d optimal solution be all it is different, should be according to actual conditions specific design.
Embodiment 1：The aerofoil profile of main wing and braced wing is RAE2822, and free stream Mach number takes 0.75, based on main wing chord length Reynolds
Number 1.66 × 107.The vertical range (g) in main wing section and support wing section in leading edge support wing model is respectively 0.2 times,
0.65 times, 1.0 times of main wing chord lengths.Shown in lift-drag ratio curve map 5, no braced wing is that the lift-drag ratio curve of single-wing is carried with the present invention
The lift-drag ratio curve of the braced wing of confession is compared, when the horizontal range of braced wing and main wing inner segment is 1.0 times of main wing inner segment chord lengths, branch
The lift-drag ratio of support wing layout has been significantly closer to single-wing, and then lift-drag ratio is decreased obviously less than 1.0 times main wing inner segment chord lengths.
Embodiment 2：The aerofoil profile of main wing and braced wing is RAE2822, and free stream Mach number takes 0.75, based on main wing chord length Reynolds
Number 1.66 × 107.Lift-drag ratio curve is with the change of vertical range (g) as shown in fig. 6, dotted line is 1.5 times of main wing inner segment chord length water
The leading edge braced wing of flat distance (s) is laid out, and solid line is the rear edge support wing layout of 0.8 times of main wing inner segment chord length horizontal range (s).
The chord length of leading edge braced wing is the 10% of main wing inner segment chord length, and rear edge support chord-length is the 30% of main wing inner segment chord length.By Fig. 6
It can be seen that, leading edge braced wing is in the case of 1.5 times of horizontal ranges, and vertical range (g) influences on the lift-drag ratio of leading edge braced wing
Less.And trailing edge braced wing layout not only changes with the change of vertical range, its lift-drag ratio is also not so good as leading edge support arrangement.
Embodiment 3：The aerofoil profile of main wing and braced wing is RAE2822, and free stream Mach number takes 0.75, based on main wing chord length Reynolds
Number 1.66 × 107.Lift-drag ratio curve is with the change of decalage (decalage) as shown in fig. 7, dotted line is 1.5 times of main wing chord length water
The leading edge braced wing of flat distance (s) is laid out, and solid line is the rear edge support wing layout of 0.8 times of main wing chord length horizontal range (s).Leading edge
The chord length of braced wing is the 10% of main wing chord length, and vertical range (g) is 0.3 times of main wing chord length, below main wing；The rear edge support wing
Chord length is the 30% of main wing, and vertical range (g) is 0.2 times of main wing chord length, below main wing.As seen from Figure 7, leading edge braced wing
In the case of 1.5 times of horizontal ranges, lift-drag ratio is changed significantly with the change of decalage.Reality for particular case should
With, should be with reference to selected aerofoil profile, chord length, horizontal vertical distance considers and calculated, to determine the peace of suitable braced wing
Fill angle.
In summary, the present invention can make aircraft overall in high infrasound while high aspect ratio wing rigidity is strengthened
Speed obtains preferably aeroperformance.The present invention provides one for the high subsonic flight device aerodynamic arrangement with high aspect ratio wing
Plant the technical scheme of excellent performance.In above-described embodiment, opened up in aircraft layout more than 80% main wing inner segment into part main wing
The horizontal range of Duan Qianyuan and support nose of wing is more than 1.0 times of main wing inner segment chord lengths, and decalage d is 0 °, main wing inner segment sweepforward
10 °, outer 15 ° of the section sweepback of main wing, 15 ° of braced wing sweepback.Result of the test illustrates that vertical range influences smaller, Ying Gen to aircraft
Determined according to the structural requirement of aircraft other parts.Studied above just for embodiment example.For other design conditions,
It should be made a concrete analysis of and determine braced wing design parameter again, but overall anterior-posterior horizontal distance of obeying is more than 1.0 times of main wing chord lengths
Design rule.
As known by the technical knowledge, the present invention can pass through other embodiment party for not departing from its theoretical essence or essential feature
Case is realized.Therefore, above-mentioned all embodiments are all merely illustrative, and are not only.Each component in the present invention
Size, cross sectional shape and relative position are determined according to design requirement, and the aerodynamic arrangement of the aircraft suitable for any size
Design, it is all within the scope of the invention as claimed or the change that is equal in protection scope of the present invention is sent out by this
It is bright to include.
Claims (5)
1. a kind of high subsonic flight device aerodynamic arrangement of the M shape wings of use leading edge braced wing, including fuselage, main wing and braced wing,
It is characterized in that：Described main wing is divided into outer two sections of the section of main wing inner segment and main wing, is high mounted wing, main wing inner segment sweepforward, outside main wing
Section sweepback, the layout of M shapes is presented from main wing in terms of top view direction；Braced wing one end connects and composes lower single-blade cloth with belly
Office, the other end is connected with main wing internal and external section junction；Braced wing also has angle of sweep, and its angle of sweep is more than main wing inner segment sweepforward
Angle.
2. a kind of high subsonic flight device aerodynamic arrangement of use leading edge braced wing according to claim 1, its feature exists
In：The scope of the angle of described sweepforward and the angle of sweepback is no more than 45 °.
3. a kind of high subsonic flight device aerodynamic arrangement of use leading edge braced wing according to claim 1, its feature exists
In：Under the conditions of high subsonic speed, the front of braced wing section outside main wing inner segment and main wing, and the slave span to section see, prop up
Part of the nose of wing with main wing inner segment leading edge horizontal range more than or equal to 1.0 times of chord lengths of main wing inner segment is supportted more than 80%.
4. a kind of high subsonic flight device aerodynamic arrangement of use leading edge braced wing according to claim 1, its feature exists
In：The angle of main wing back segment sweepback is more than the angle of the sweepforward of main wing inner segment.
5. a kind of high subsonic flight device aerodynamic arrangement of use leading edge braced wing according to claim 1, its feature exists
In：Described braced wing is connected to the leading edge of main wing inner segment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710371758.XA CN107264774B (en) | 2017-05-24 | 2017-05-24 | A kind of M shape wing high subsonic flight device aerodynamic arrangement using leading edge braced wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710371758.XA CN107264774B (en) | 2017-05-24 | 2017-05-24 | A kind of M shape wing high subsonic flight device aerodynamic arrangement using leading edge braced wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107264774A true CN107264774A (en) | 2017-10-20 |
| CN107264774B CN107264774B (en) | 2019-10-25 |
Family
ID=60065551
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710371758.XA Active CN107264774B (en) | 2017-05-24 | 2017-05-24 | A kind of M shape wing high subsonic flight device aerodynamic arrangement using leading edge braced wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107264774B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN110481771A (en) * | 2019-09-26 | 2019-11-22 | 成都纵横大鹏无人机科技有限公司 | Can VTOL Fixed Wing AirVehicle and UAV system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5899410A (en) * | 1996-12-13 | 1999-05-04 | Mcdonnell Douglas Corporation | Aerodynamic body having coplanar joined wings |
| RU2165867C2 (en) * | 1996-07-23 | 2001-04-27 | Безруков Юрий Иванович | Vertical take-off and landing aircraft |
| US8141815B1 (en) * | 2009-05-19 | 2012-03-27 | The Boeing Company | Wing strut trailing edge device |
| CN102458988A (en) * | 2009-04-07 | 2012-05-16 | 空中客车西班牙运营有限责任公司 | Aircraft having a lambda-box wing configuration |
| CN203698650U (en) * | 2014-01-20 | 2014-07-09 | 谭大刚 | Flexible skin M-shaped aerofoil capable of being quickly unfolded and folded |
| CN105905277A (en) * | 2016-04-19 | 2016-08-31 | 北京航空航天大学 | Air vehicle aerodynamic configuration with trailing edge supporting wing |
-
2017
- 2017-05-24 CN CN201710371758.XA patent/CN107264774B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2165867C2 (en) * | 1996-07-23 | 2001-04-27 | Безруков Юрий Иванович | Vertical take-off and landing aircraft |
| US5899410A (en) * | 1996-12-13 | 1999-05-04 | Mcdonnell Douglas Corporation | Aerodynamic body having coplanar joined wings |
| CN102458988A (en) * | 2009-04-07 | 2012-05-16 | 空中客车西班牙运营有限责任公司 | Aircraft having a lambda-box wing configuration |
| US8141815B1 (en) * | 2009-05-19 | 2012-03-27 | The Boeing Company | Wing strut trailing edge device |
| CN203698650U (en) * | 2014-01-20 | 2014-07-09 | 谭大刚 | Flexible skin M-shaped aerofoil capable of being quickly unfolded and folded |
| CN105905277A (en) * | 2016-04-19 | 2016-08-31 | 北京航空航天大学 | Air vehicle aerodynamic configuration with trailing edge supporting wing |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN110481771A (en) * | 2019-09-26 | 2019-11-22 | 成都纵横大鹏无人机科技有限公司 | Can VTOL Fixed Wing AirVehicle and UAV system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107264774B (en) | 2019-10-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8936219B2 (en) | Performance-enhancing winglet system and method | |
| CN101687542B (en) | Engine nacelle of an aircraft comprising a vortex generator arrangement | |
| WO2009045694A2 (en) | Wingtip feathers, including paired, fixed feathers, and associated systems and methods | |
| CN105129090A (en) | Low resistance and low sonic boom layout supersonic aircraft | |
| CN109131833A (en) | A kind of high aspect ratio wing of high lift-rising | |
| US11718386B2 (en) | Cupola fairing for an aircraft and method for fabricating the same | |
| CN202609085U (en) | Aircraft aerodynamic configuration with blended wing body | |
| CN108733914A (en) | Transonic airfoil Natural Laminar Flow delay based on artificial neural network turns to twist design method | |
| CN107521695A (en) | A kind of blended wing-body connects wing aircraft | |
| CN105857579A (en) | Propeller airplane | |
| CN106828876B (en) | A kind of sweepforward natural laminar flow wing suitable for medium or short range high speed civil aircraft | |
| CN106828933B (en) | A kind of high altitude long time tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference | |
| CN107264774B (en) | A kind of M shape wing high subsonic flight device aerodynamic arrangement using leading edge braced wing | |
| Metkowski et al. | Winglet and strut configuration study for a slotted, natural-laminar-flow strut-braced transport aircraft | |
| CN108502138A (en) | A kind of buzzard-type wing expanded letter high subsonic flight device aerodynamic arrangement using leading edge braced wing | |
| CN111017185B (en) | Laminar flow technology verification machine | |
| CN106828872B (en) | Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage | |
| CN113148105A (en) | Double-head wing body fusion low-detectable layout | |
| CN209008845U (en) | A kind of high aspect ratio wing of high lift-rising | |
| Andrews et al. | Parametric study of box-wing aerodynamics for minimum drag under stability and maneuverability constraints | |
| CN104192294A (en) | A wing structure and an airplane | |
| CN207902734U (en) | A kind of unmanned plane of aerodynamic arrangement | |
| CN109263856A (en) | High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement | |
| CN102358417B (en) | Annular winglet of civil airliner wing | |
| CN109484622A (en) | A kind of high subsonic speed sweep wing aircraft aerodynamic arrangement using leading edge braced wing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |