CN106741947A - A kind of Flying-wing of company structure of flying wing - Google Patents
A kind of Flying-wing of company structure of flying wing Download PDFInfo
- Publication number
- CN106741947A CN106741947A CN201710069004.9A CN201710069004A CN106741947A CN 106741947 A CN106741947 A CN 106741947A CN 201710069004 A CN201710069004 A CN 201710069004A CN 106741947 A CN106741947 A CN 106741947A
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- 230000000368 destabilizing effect Effects 0.000 description 2
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/08—Aircraft not otherwise provided for having multiple wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
- B64C2039/105—All-wing aircraft of blended wing body type
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of Flying-wing of the company structure of flying wing, including front wing, front wing is high aspect ratio swept-back wing, also include the even wing, rear wing, front wing both sides wing tip connects the Lian Yi bottoms of flare, Lian Yi tops connection rear wing both sides wing tip, front wing, Lian Yi, rear wing are end to end to constitute isosceles trapezoid frame structure, and rear wing is located at front wing top；Rear wing includes the straight wing of rear wing of centre and its rear wing buzzard-type wing of symmetrical connection；Front wing rudder face is symmetrical arranged in the elongated surfaces of front wing rear end tails；Rear wing buzzard-type wing rudder face is set in the elongated surfaces of rear wing buzzard-type wing rear end tails, rear wing straight wing rudder face is set in the elongated surfaces of wing rear end tails that rear wing is straight；Even Flying-wing manipulation ability of the invention is strong, static stability is high, mobility good.Solve the control problem of flying wing.
Description
Technical field
The present invention relates to aerodynamic configuration of aircraft field, the Flying-wing of company of more particularly to a kind of flying wing ties
Structure.
Background technology
" all-wing aircraft " is a kind of aerodynamic configuration of aircraft mode for being different from Conventional pneumatic layout.All-wing aircraft is also known as all-wing machine.It is
A kind of major part without empennage and fuselage is hidden in the airborne vehicle in thicker wing.It is only organic for any aircraft
The wing is required, so it is in design feasible theoretically to remove every other unnecessary part.Some all-wing aircraft fuselages
Or retain, but be certainly no empennage.What B-2 bomber was used is Flying-wing.It is this to be laid out briefly just
It is the layout of only airplane wings, it appears that only wing, does not have fuselage, fuselage and wing combines together.Undoubtedly this layout
It is aerodynamic efficiency highest layout, because all airframe structures are all wings, contributes to produce lift, and maximum journey
That spends reduces resistance.But flying wing type layout eliminates conventional vertical fin and horizontal tail, compared to normal layout, stability compared with
Difference, the greatest drawback of Flying-wing is handling extreme difference.
Flying wing type transporter can be larger using area, and the more conventional interior of aircraft space of flying wing type airplane is larger, there is work
It is the advantage of airliner.But its unstable inferior position experiences to passenger with the aviation not high of uncomfortable and degree of safety.
Follow-on long-distance passenger plane is being studied by american lockheed LMT and Boeing, and it uses flying wing type to be laid out, on machine
Complete, system, high-precision avionics system is loaded to coordinate rudder face to realize the state of flight for giving aircraft stabilization differential at any time.But
Used as long-range passenger plane, the tired degree and manufacturing cost of its cost and pilot are also deepened significantly.So final design scheme is slow
Do not shape late.
Shipping-direction stability and longitudinal direction manipulation without vertical fin flying wing aircraft are relatively difficult, so flying wing aircraft is often neutral steady
Determine or quiet unstable design is so as to increase pitch control ability.Therefore the larger challenge that flying wing type layout faces is new
Steerable system and control system.
The content of the invention
It is an object of the invention to provide a kind of Flying-wing of the company structure of flying wing, the present invention is keeping traditional all-wing aircraft
Formula it is original using advantage on the basis of, improve its control ability, by the basis of Flying-wing increase even alar part change
The layout of aircraft, i.e., the method for " becoming all-wing aircraft to connect all-wing aircraft ", solves the control problem of aircraft.
The present invention is achieved by the following technical solutions：
A kind of Flying-wing of the company structure of flying wing, including front wing 1, described front wing 1 are high aspect ratio swept-back wing,
Also include the even wing 2, rear wing, the even bottom of the wing 2 of the both sides wing tip connection flare of the front wing 1, the even wing 2 top connection institute
Rear wing both sides wing tip is stated, the front wing 1, Lian Yi 2, rear wing are end to end to constitute isosceles trapezoid frame structure in preceding apparent direction,
The rear wing is located at the top of the front wing 1；The rear wing includes the straight wing 4 of rear wing of centre and its rear wing of symmetrical connection
Buzzard-type wing 3；
Front wing rudder face 5 is symmetrical arranged in the elongated surfaces of the rear end tails of the front wing 1；The rear end tails of rear wing buzzard-type wing 3
Elongated surfaces on rear wing buzzard-type wing rudder face 6 is set, the rear wing straight wing is set in the elongated surfaces of the straight rear end tails of the wing 4 of rear wing
Rudder face 7；
Described company's wing 2 is that winglet is trapezoidal shape, 45 ° of flare.
The rear wing buzzard-type wing 3 is parallelogram shape, and described rear wing is straight, and the wing 4 is rectangular shape.
The Plate with web 8 of connected symmetrical dendrimer between the front wing 1 and the straight wing 4 of the rear wing.
Described Plate with web 8 be arranged in parallel for two pieces, and the Plate with web vertically connects the front wing 1 and the straight wing 4 of rear wing
Two ends.
The Plate with web 8 is parallelogram shape, and its base connects the front wing 1, and its top margin connects the rear wing and puts down
One end of the straight wing 4, the parallelogram shape is tilted backwards along air flow.
The front wing 1, Lian Yi 2, rear wing are NACA0012 aerofoil profiles.
Described rudder face uses resistance elevator.
Advantages of the present invention is as follows：
1st, main wing of the invention is that front wing is traditional flying wing type layout, the control of two rudder faces；It is small that company's alar part is divided into flare wing tip
The wing；Rear wing uses one group of buzzard-type wing and a straight wing；Lian Yi is not equipped with rudder face, and rear wing is designed for three rudder faces.Rear wing actually should
The larger material of used time selection structural strength installs supporting plate additional.Even Flying-wing of the invention has control ability strong, quiet steady
The good beneficial effect of qualitative high, mobility.After using even Flying-wing, control efficiency is significantly lifted, and is conducive to being used in
Under more extreme more adverse circumstances, such as troops or goods and materials are delivered to disaster area.
2nd, main wing portion of the invention is based on the Flying-wing of company of traditional flying wing type layout, and main wing (front wing) is high aspect ratio
Swept-back wing, the size of aspect ratio has obvious influence on In-Flight Performance.When aspect ratio increases, the induced drag of wing can drop
It is low, such that it is able to improving the mobility of aircraft and increasing subsonic speed voyage.Main wing portion has one group of steering wheel, and rear wing both sides rudder
The rolling of face co- controlling aircraft.The tumbling action of aircraft is set to have obtained significantly being lifted.Control ability substantially increases.
3rd, alar part is connected：Lian Yi serves as winglet in whole airplane.Aircraft in flight course, wing upper and lower surface
Pressure differential, make the high pressure draught of aircraft lower surface to medial movement, the lateral flow and freedom of the transverse shifting of this air-flow
Stream is combined into wing tip whirlpool.This causes that aircraft produces very big induced drag, and directional instability.Winglet then flies in whole frame
The effect for maintaining vector stability is served in machine.In addition winglet can also make in wing tip downstream dissipation wingtip vortex
The induced velocity and the speed of free flow synthesis for obtaining the generation of wing upper and lower surface gas flow sideways are produced to side thrust i.e. " winglet
Lift ".In addition after adding winglet in even wing aircraft, the aspect ratio of aircraft can also further be increased.If removed, aircraft
Course will be very unstable.
4th, rear alar part：Rear wing has three rudder faces.Rudder face on two rudder faces assistance main wings of wing or so is carried out to aircraft
Rolling is controlled, and middle rudder face can then carry out the control in terms of pitching.Rudder face and traditional flying wing type airplane rudder on rear wing
Face is compared, and its control arm of force is longer, and pitch control ability is stronger.When necessary, all of wing can be carried out to aircraft simultaneously
Pitch control, is obviously improved the control efficiency of aircraft.Improve mobility, stability and the quiet anti-interference energy of aircraft
Power.
5th, the present invention is using the NACA0012 aerofoil profiles that stall is difficult in big generator rotor angle.Buzzard-type wing technology can make aircraft in subsonics
There is extraordinary aeroperformance big-elevation stall performance during fast flight, it is motor-driven under the state of the elevation angle so as to greatly improve it
Property.Why buzzard-type wing has good High Angle of Attack performance, be because its wing root lateral margin whirlpool and wing tip leading vortex interact,
Upper suction is produced to wing, vortex lift is brought and is enhanced the control ability flowed to aerofoil surface.
6th, even the rear wing of Flying-wing is bigger than the tailplane area of conventional airplane, therefore control efficiency is high, trim resistance
It is small.If envisioning the company's of addition wing design on B2 bombers, multiple rudder faces are controlled it jointly, are mixed using the front and rear wing and controlled
The method of system, is effectively reduced the cost and precision of avionics system, in long-range flight, it is possible to reduce pilot is absorbed in behaviour for a long time
The pressure of work, effective guarantee flight reappearance.When air blast or other destabilizing factors are met with, the rear wing of sweepforward also can fully be sent out
The mobility under its big-elevation is waved, aircraft safety coefficient and stability is improve.
Brief description of the drawings：
Fig. 1 is dimensional structure diagram of the invention,
Fig. 2 is schematic top plan view of the invention,
Fig. 3 is front-view schematic diagram of the invention,
Fig. 4 is schematic side view of the invention,
Fig. 5 is the schematic top plan view for showing each rudder face of the invention；
Each component names and numbering in figure：1st, front wing (be main wing) 2, Lian Yi 3, rear wing buzzard-type wing 4, rear wing the is straight wing
5th, front wing rudder face 6, rear wing buzzard-type wing rudder face 7, rear wing is straight wing rudder face 8, Plate with web
Specific embodiment
Embodiment 1：
Referring to shown in Fig. 1,2, a kind of Flying-wing of the company structure of flying wing, including front wing 1, described front wing 1 is
High aspect ratio swept-back wing, also including the even wing 2, rear wing, the even bottom of the wing 2 of the both sides wing tip connection flare of the front wing 1 is described
Even the top of the wing 2 connects rear wing both sides wing tip, the end to end composition etc. in preceding apparent direction of the front wing 1, Lian Yi 2, rear wing
Referring to Fig. 3, the rear wing is located at the top of the front wing 1 to waist ladder-shaped frame structure；The rear wing includes the middle straight wing 4 of rear wing
And its rear wing buzzard-type wing 3 of symmetrical connection；
Front wing rudder face 5 is symmetrical arranged in the elongated surfaces of the rear end tails of the front wing 1；The rear end tails of rear wing buzzard-type wing 3
Elongated surfaces on rear wing buzzard-type wing rudder face 6 is set, the rear wing straight wing is set in the elongated surfaces of the straight rear end tails of the wing 4 of rear wing
Rudder face 7；Referring to Fig. 5
Described company's wing 2 is that winglet is trapezoidal shape, 45 ° of flare.
The rear wing buzzard-type wing 3 is parallelogram shape, and described rear wing is straight, and the wing 4 is rectangular shape.
The Plate with web 8 of connected symmetrical dendrimer between the front wing 1 and the straight wing 4 of the rear wing.
Described Plate with web 8 be arranged in parallel for two pieces, and the Plate with web vertically connects the front wing 1 and the straight wing 4 of rear wing
Two ends.
The Plate with web 8 is parallelogram shape, and its base connects the front wing 1, and its top margin connects the rear wing and puts down
One end of the straight wing 4, the parallelogram shape is tilted backwards referring to Fig. 4 along air flow.
The front wing 1, Lian Yi 2, rear wing are NACA0012 aerofoil profiles.
Described rudder face uses resistance elevator.
Structure of the present invention is described further below：
Main wing of the invention is that front wing is traditional flying wing type layout, the control of two rudder faces；Even alar part is divided into flare winglet；
Rear wing uses one group of buzzard-type wing and a straight wing；Lian Yi is not equipped with rudder face, and rear wing is designed for three rudder faces.Rear wing is in practical application
The larger material of selection structural strength installs Plate with web additional.Even Flying-wing of the invention has that control ability is strong, static stability
The good beneficial effect of high, mobility.Main wing portion of the invention is based on traditional flying wing type layout, and main wing (front wing) is great Zhan strings
Than swept-back wing, the size of aspect ratio has obvious influence on In-Flight Performance.When aspect ratio increases, the induced drag meeting of wing
Reduce, such that it is able to improving the mobility of aircraft and increasing subsonic speed voyage.Main wing portion has one group of steering wheel, and rear wing both sides
The rolling of rudder face co- controlling aircraft.The tumbling action of aircraft is set to have obtained significantly being lifted.Control ability substantially increases.
Connect alar part：Lian Yi serves as winglet in whole airplane.Aircraft in flight course, wing upper and lower surface
Pressure differential, makes the high pressure draught of aircraft lower surface to medial movement, the lateral flow and free flow of the transverse shifting of this air-flow
It is combined into wing tip whirlpool.This causes that aircraft produces very big induced drag, and directional instability.Winglet is then in whole airplane
In serve maintain vector stability effect.In addition winglet can also be in wing tip downstream dissipation wingtip vortex so that
The induced velocity that wing upper and lower surface gas flow sideways are produced is produced to side thrust i.e. " winglet liter with the speed of free flow synthesis
Power ".In addition after adding winglet in even wing aircraft, the aspect ratio of aircraft can also further be increased.If removed, the boat of aircraft
To will be very unstable.
Alar part afterwards：Rear wing has three rudder faces.Two rudder faces of wing or so assist the rudder face on main wing to roll aircraft
Turn control, middle rudder face can then carry out the control in terms of pitching.Rudder face and traditional flying wing type airplane rudder face on rear wing
Compare, its control arm of force is longer, and pitch control ability is stronger.When necessary, all of wing can bow to aircraft simultaneously
Control is faced upward, the control efficiency of aircraft is obviously improved.Improve mobility, stability and the quiet anti-interference energy of aircraft
Power.
The present invention is using the NACA0012 aerofoil profiles that stall is difficult in big generator rotor angle.Buzzard-type wing technology can make aircraft in subsonic speed
There is extraordinary aeroperformance big-elevation stall performance, so as to greatly improve its mobility under the state of the elevation angle during flight.
Why buzzard-type wing has good High Angle of Attack performance, be because its wing root lateral margin whirlpool and wing tip leading vortex interact, it is right
Wing produces upper suction, brings vortex lift and enhances the control ability flowed to aerofoil surface.
The rear wing that the present invention connects Flying-wing is bigger than the tailplane area of conventional airplane, therefore control efficiency is high, trim
Resistance is small.If envisioning the company's of addition wing design on B2 bombers, multiple rudder faces are controlled it jointly, mixed using the front and rear wing
The method for closing control, is effectively reduced the cost and precision of avionics system, in long-range flight, it is possible to reduce pilot is special for a long time
Note the pressure of operation, effective guarantee flight reappearance.When air blast or other destabilizing factors are met with, the rear wing of sweepforward can also fill
The mobility under its big-elevation is waved in distribution, improves aircraft safety coefficient and stability.
Flare connects the wing can be improved according to the condition of work difference of aircraft, and the present invention is using 45 ° of designs of flare, trapezoidal knot
Structure.Rear wing buzzard-type wing uses parallelogram aerofoil profile, and rear wing is straight, and the wing is rectangular design.Rudder face uses resistance elevator.This
The full machine of invention aircraft uses NACA0012 aerofoil profiles.Actual design can be right in the case of selection even Flying-wing according to actual conditions
Aircraft parameter is adjusted.Several different rudder faces mix joint control system using many rudder faces, in practical flight according to flight condition
Etc. the rudder surface control system that factor Programming is adapted to this flight.Front wing, rear wing buzzard-type wing rudder face can control aircraft rolling,
All rudder faces can control aircraft pitch.Flare connects the wing and winglet effect is played in aircraft, increases vector stability,
Increase aspect ratio, rudder face is not equipped with thereon.The aircraft is applied to design direction of the subsonic speed to Stealth no requirement (NR).
Optimization technique parameter of the present invention is as follows, based on traditional flying wing type layout forewing sweep control 20 ° to 45 ° it
Between to ensure that it is high aspect ratio, 45 ° of 2 flares of Lian Yi, the end positions of the wing 4 that rear wing is straight at 1/2nd of front wing 1, rear wing
Buzzard-type wing sweepforward angle is 45 °, and front wing rear wing interval height is controlled 2/3rds of designed winglet (Lian Yi) length
It is interior.
The present inventor has made checking model machine by the technical scheme of embodiment 1, verifies the specific ginseng of each technical characteristic of model machine
Number is as follows：Forewing sweep control based on traditional flying wing type layout at 45 °, 45 ° of 2 flares of Lian Yi, rear wing the is straight two ends of the wing 4 position
It is set at 1/2nd of front wing 1, rear wing buzzard-type wing sweepforward angle is 45 °, and front wing rear wing interval height is controlled in the designed wing
2/3rds of sharp winglet length.Tests prove that：The checking model machine has foregoing handling, and it has and is substantially better than biography
Rolling, the pitch control performance of system flying wing type airplane.Its radius of turn is about 2/3rds of conventional flying wing, tool
There is excellent minor-circle turn characteristic.Model machine successfully flies to 70 meters of high-altitudes, directional instability does not occur, and the present inventor is by being somebody's turn to do
Checking model machine demonstrates the feasibility of Flying-wing of the company structure of flying wing of the present invention.
The invention of the present inventor is it is important that be Flying-wing of the company structure of this flying wing, those skilled in the art
Even Flying-wing of the invention, with reference to the specific requirement in actual design, the conventional selection using prior art completely may be used
Adjust or select with the particular technique parameter of the aircraft to this layout.
Claims (8)
1. a kind of Flying-wing of the company structure of flying wing, including front wing (1), described front wing (1) is high aspect ratio sweepback
The wing, it is characterised in that also including the even wing (2), rear wing, the described even wing (2) bottom of front wing (1) both sides wing tip connection flare
Portion, the even wing (2) the top connection rear wing both sides wing tip, the front wing (1), Lian Yi (2), rear wing are end to end in forward sight
Isosceles trapezoid frame structure is constituted on direction, the rear wing is located at the front wing (1) top；The rear wing includes middle rear wing
The straight wing (4) and its rear wing buzzard-type wing (3) of symmetrical connection；
Front wing rudder face (5) is symmetrical arranged in the elongated surfaces of front wing (1) rear end tails；Rear wing buzzard-type wing (3) rear end tail
Rear wing buzzard-type wing rudder face (6) is set in the elongated surfaces in portion, rear wing is set in the elongated surfaces of the straight wing of rear wing (4) rear end tails
Straight wing rudder face (7).
2. a kind of Flying-wing of the company structure of flying wing according to claim 1, it is characterised in that described company's wing
(2) for winglet is trapezoidal shape, 45 ° of flare.
3. Flying-wing of the company structure of a kind of flying wing according to claim 1, it is characterised in that before the rear wing
It is parallelogram shape to plunder the wing (3), and described rear wing is straight, and the wing (4) is rectangular shape.
4. a kind of Flying-wing of the company structure of flying wing according to claim 1, it is characterised in that the front wing
(1) between the straight wing of the rear wing (4) connected symmetrical dendrimer Plate with web (8).
5. a kind of Flying-wing of the company structure of flying wing according to claim 4, it is characterised in that described company's muscle
Plate (8) be arranged in parallel for two pieces, and the Plate with web vertically connects the two ends of the front wing (1) and the straight wing of rear wing (4).
6. a kind of Flying-wing of the company structure of flying wing according to claim 4, it is characterised in that the Plate with web
(8) it is parallelogram shape, its base connects the front wing (1), its top margin connects one end of the straight wing of rear wing (4),
The parallelogram shape is tilted backwards along air flow.
7. a kind of Flying-wing of the company structure of flying wing according to claim 1, it is characterised in that the front wing
(1), Lian Yi (2), rear wing are NACA0012 aerofoil profiles.
8. a kind of Flying-wing of the company structure of flying wing according to claim 1, it is characterised in that described rudder face
Use resistance elevator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710069004.9A CN106741947A (en) | 2017-02-08 | 2017-02-08 | A kind of Flying-wing of company structure of flying wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710069004.9A CN106741947A (en) | 2017-02-08 | 2017-02-08 | A kind of Flying-wing of company structure of flying wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106741947A true CN106741947A (en) | 2017-05-31 |
Family
ID=58956217
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710069004.9A Pending CN106741947A (en) | 2017-02-08 | 2017-02-08 | A kind of Flying-wing of company structure of flying wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106741947A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109543250A (en) * | 2018-11-02 | 2019-03-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of vertical fin and horizontal tail configuration designing method of flare twin-finned layout |
| CN113859514A (en) * | 2021-11-11 | 2021-12-31 | 沈阳航空航天大学 | Split type all-wing aircraft |
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| ITFI20030043A1 (en) * | 2003-02-19 | 2004-08-20 | Aldo Frediani | TWO-LEVEL WINGS AIRCRAFT WITH HIGH STATIC STABILITY |
| WO2009029796A2 (en) * | 2007-08-29 | 2009-03-05 | Advanced Product Development, Llc | Oblique blended wing body aircraft |
| CA2758220A1 (en) * | 2009-04-07 | 2010-10-14 | Airbus Operations, S.L. | Aircraft having a lambda-box wing configuration |
| CN103171766A (en) * | 2011-12-20 | 2013-06-26 | 北京航空航天大学 | Short distance rising and landing unmanned all-wing aircraft |
| CN203283375U (en) * | 2013-04-16 | 2013-11-13 | 赵嘉珩 | Aircraft wing layout structure |
| CN103552682A (en) * | 2013-10-30 | 2014-02-05 | 北京航空航天大学 | Airplane with combined-wing layout of flying wing and forward-swept wings |
| CN105416587A (en) * | 2015-12-02 | 2016-03-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aerodynamic layout of aircraft with blended wing body |
| CN206446796U (en) * | 2017-02-08 | 2017-08-29 | 杨宇腾 | A kind of Flying-wing of company structure of flying wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ITFI20030043A1 (en) * | 2003-02-19 | 2004-08-20 | Aldo Frediani | TWO-LEVEL WINGS AIRCRAFT WITH HIGH STATIC STABILITY |
| WO2009029796A2 (en) * | 2007-08-29 | 2009-03-05 | Advanced Product Development, Llc | Oblique blended wing body aircraft |
| CA2758220A1 (en) * | 2009-04-07 | 2010-10-14 | Airbus Operations, S.L. | Aircraft having a lambda-box wing configuration |
| CN103171766A (en) * | 2011-12-20 | 2013-06-26 | 北京航空航天大学 | Short distance rising and landing unmanned all-wing aircraft |
| CN203283375U (en) * | 2013-04-16 | 2013-11-13 | 赵嘉珩 | Aircraft wing layout structure |
| CN103552682A (en) * | 2013-10-30 | 2014-02-05 | 北京航空航天大学 | Airplane with combined-wing layout of flying wing and forward-swept wings |
| CN105416587A (en) * | 2015-12-02 | 2016-03-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aerodynamic layout of aircraft with blended wing body |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109543250A (en) * | 2018-11-02 | 2019-03-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of vertical fin and horizontal tail configuration designing method of flare twin-finned layout |
| CN109543250B (en) * | 2018-11-02 | 2023-02-10 | 中国航空工业集团公司西安飞机设计研究所 | Vertical tail and horizontal tail configuration design method for camber double-vertical-tail layout |
| CN113859514A (en) * | 2021-11-11 | 2021-12-31 | 沈阳航空航天大学 | Split type all-wing aircraft |
| CN113859514B (en) * | 2021-11-11 | 2024-04-02 | 沈阳航空航天大学 | Split type allies oneself with wing overall arrangement aircraft |
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Application publication date: 20170531 |