CN205738056U - A kind of aerodynamic arrangement of the big aircraft of strategy - Google Patents
A kind of aerodynamic arrangement of the big aircraft of strategy Download PDFInfo
- Publication number
- CN205738056U CN205738056U CN201620708617.3U CN201620708617U CN205738056U CN 205738056 U CN205738056 U CN 205738056U CN 201620708617 U CN201620708617 U CN 201620708617U CN 205738056 U CN205738056 U CN 205738056U
- Authority
- CN
- China
- Prior art keywords
- wing
- aerodynamic arrangement
- aspect ratio
- strategy
- high aspect
- 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.)
- Expired - Fee Related
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
This utility model belongs to technical field of aerospace Flight Vehicle Design direction, mainly solves the problem that the lift-drag ratio of the big aircraft of strategy is relatively low.This utility model relates to the aerodynamic arrangement of the big aircraft of a kind of strategy, aerodynamic arrangement including fuselage, wing, horizontal tail, vertical tail and electromotor, it is characterized in that: the aerodynamic arrangement of expanded letter fuselage, the aerodynamic arrangement of the high aspect ratio wing with winglet, the aerodynamic arrangement of lift horizontal tail, the aerodynamic arrangement of double fins flare, and the aerodynamic arrangement that fanjet installation is under the wings of an airplane.The aerodynamic arrangement of the big aircraft of described strategy makes big aircraft possess, and lift-drag ratio property high, controllable is good and the advantage of good stability.
Description
Technical field
This utility model relates to the aerodynamic arrangement of the big aircraft of a kind of strategy, belongs to technical field of aerospace.
Background technology
The big aircraft of strategy is the support platform of a kind of all-rounder, before having the multiple development such as civilian, military and space flight
Scape.The big aircraft of Muscovite strategy has " Ilyushin-76 ", and the big aircraft of strategy of Ukraine has " amp-124 " and " amp-225 ", the U.S.
The big aircraft of strategy have " C-17 ", " C-5 ", " Boeing-747 " and " Boeing-777 " etc., the strategy aircraft greatly in Europe has " A-
380”.China's aircraft big to world strategy is paid special attention to, the research and development ground zero of the big aircraft of strategy, the same to U.S., Europe, Russia and
The big aircraft of strategy of Ukraine is compared, and technology has certain gap.
At present, the aerodynamic arrangement of the big aircraft of strategy typically belongs to normal configuration.Under current technological conditions, adopt when aircraft
During by positive routine aerodynamic arrangement situation, common pneumatic focus after the center of gravity of airplane, aircraft flat fly trim time, airplane ascensional force
Producing nose-down pitching moment, the negative lift of horizontal tail produces nose-up pitching moment, and both mutually balance, and damping in pitch is big, and the vertical property of aircraft is stable
Property is good.But, so, horizontal tail provides negative lift when aircraft is put down and flown trim, is negative to airplane ascensional force contribution, the liter of aircraft
Power incurs loss, and lift-drag ratio is relatively low.
Utility model content
The purpose of this utility model is to provide the aerodynamic arrangement of the big aircraft of a kind of strategy, this aerodynamic arrangement to make strategy fly greatly
Facility are for outstanding lifting resistance characteristic, navigability and stability.
For achieving the above object, technical solution adopted in the utility model is:
A kind of aerodynamic arrangement of the big aircraft of strategy, including the aerodynamic arrangement of fuselage, wing, horizontal tail, vertical tail and electromotor,
It is characterized in that: the aerodynamic arrangement of expanded letter fuselage, the aerodynamic arrangement of the high aspect ratio wing of band winglet, the gas of lift horizontal tail
Aerodynamic arrangement under the wings of an airplane installed by dynamic layout, the aerodynamic arrangement of double fins flare, and fanjet.
As further improvement of the utility model, the concrete structure of the aerodynamic arrangement of described expanded letter fuselage is: head
(2) trousers hatch door (1) Guan Bi time degree of slipping over, the appearance profile of the cross section of middle fuselage (3) is smooth, afterbody (4)
Smooth excessively reduce to reduce resistance, with landing gear trousers (5) below middle fuselage, head (2), middle fuselage (3), machine
Body afterbody (4) forms described expanded letter fuselage together.
As further improvement of the utility model, the pneumatic cloth of the high aspect ratio wing of described band winglet (8)
The concrete structure of office is: wing root wing (6), middle wing (7), winglet (8) form described high aspect ratio wing, greatly together
Aspect ratio wing is high mounted wing, lower anti-, sweepback；The aspect ratio of high aspect ratio wing is 5.2～6.2, inverted diherdral is 2 °～4 °, peace
Dress angle is 3 °～4 °；Wing root leading edge of a wing angle of sweep is 35 °～45 °, and wing root trailing edge angle of sweep is 0 °；After the middle leading edge of a wing
Sweep angle is 35 °～45 °, and middle trailing edge angle of sweep is 21 °～31 °；Winglet (8) area and high aspect ratio wing area it
Ratio is 11%～15%；High aspect ratio wing trailing edge is with wing flap (9), outer wing flap (10), aileron (11)；Wing flap (9) area with
High aspect ratio wing area ratio is 3%～5%, and outer wing flap (9) area and high aspect ratio wing area ratio are 5%～8%,
Aileron (11) area and high aspect ratio wing area ratio are 10%～12%.
As further improvement of the utility model, the concrete structure of the aerodynamic arrangement of described lift horizontal tail is: lift
Horizontal tail (12) is tapered airfoil, upper anti-, sweepback, and with stagewise elevator (13)；The upper counterangle of lift horizontal tail (12) be 7 °～
10 °, established angle is 3 °～5 °；The leading edge sweep of lift horizontal tail (12) is 40 °～45 °, and trailing sweep is 28 °～32 °；Rise
The aspect ratio of power horizontal tail (12) is 2.8～3.5；Stagewise elevator (13) area and lift horizontal tail (12) area ratio are 18%
～25%.
As further improvement of the utility model, the concrete structure of the aerodynamic arrangement of described double fins flare is: double
Vertical tail camber angle is 15 °～25 °, and vertical tail is divided into upper vertical tail (14) and lower vertical tail (15) two sections by lift horizontal tail, and with segmentation
Linkage rudder (16)；Upper vertical tail (14), lower vertical tail (15) are trapezoidal, and the aerofoil profile of vertical tail is symmetrical airfoil；Segmentation linkage side
It is 20%～25% to rudder (16) area and vertical tail area ratio.
As further improvement of the utility model, the tool of aerodynamic arrangement under the wings of an airplane installed by described fanjet
Body structure is: under left and right high aspect ratio wing, and symmetry respectively hangs 2 fanjets (18), outside fanjet (18)
Wall nacelle (19) is hung by hanger (17) and is forward extended out.
Compared with prior art, the having the beneficial effect that of advantage of the present utility model and acquirement
First, lift-drag ratio is high.Aircraft is flat fly trim time, owing to high aspect ratio wing provides lift, lift horizontal tail provides
Positive lift force, lift does not incur loss, and takes Drag reduction devices due to fuselage again, and resistance is little, so the lift-drag ratio of the big aircraft of strategy
High.
Second, navigability is good.Having stagewise elevator for pitch control, the device for yaw control has segmentation
Linkage rudder, the device for roll guidance has aileron, also has the device for lift-rising to have wing flap, outer wing flap, so aircraft
Maneuverability good.
3rd, good stability.The pneumatic focus of the big aircraft of strategy before the center of gravity of aircraft, the lift pair of high aspect ratio wing
Nose-up pitching moment, the positive lift force of lift horizontal tail that the center of gravity of the big aircraft of strategy produces fight the power of bowing that the center of gravity of bigger aircraft produces
Square reaches balance jointly, and damping in pitch is big, so the longitudinal stability of the big aircraft of strategy is good；Owing to the big aircraft of strategy is upper list
The wing, high aspect ratio, lower instead, so the lateral stability of the big aircraft of strategy is good；Owing to high aspect ratio wing is with winglet, and
Big aircraft has the double fins of flare, so the shipping-direction stability of the big aircraft of strategy is good.
Accompanying drawing explanation
Fig. 1 is axonometric chart of the present utility model.
Fig. 2 is front view of the present utility model.
Fig. 3 is rearview of the present utility model.
Fig. 4 is left view of the present utility model.
Fig. 5 is top view of the present utility model.
Fig. 6 is upward view of the present utility model.
Fig. 7 is lift coefficient characteristic curve of the present utility model.
Fig. 8 is resistance coefficient characteristic curve of the present utility model.
Fig. 9 is lift-drag ratio characteristic curve of the present utility model.
In the accompanying drawings, 1 is trousers hatch door；2 is head；3 is middle fuselage；4 is afterbody；5 is landing gear trousers；
6 is wing root wing；7 is middle wing；8 is winglet；9 is wing flap；10 is outer wing flap；11 is aileron；12 is lift horizontal tail；13
For stagewise elevator；14 is upper vertical tail；15 is lower vertical tail；16 is segmentation linkage rudder；17 is hanger；18 start for turbofan
Machine；19 is outer wall nacelle.
Detailed description of the invention
Below in conjunction with accompanying drawing 1～9 and embodiment this utility model is further elaborated.
The embodiment of the aerodynamic arrangement of the big aircraft of a kind of strategy, including fuselage, wing, horizontal tail, vertical tail and electromotor
Aerodynamic arrangement, it is characterised in that: the aerodynamic arrangement of expanded letter fuselage, the aerodynamic arrangement of the high aspect ratio wing of band winglet, rise
Aerodynamic arrangement under the wings of an airplane installed by the aerodynamic arrangement of power horizontal tail, the aerodynamic arrangement of double fins flare, and fanjet；War
The captain of bigger aircraft is 84.8m, a height of 18.3m of machine, and the span is 88.4m.
As the further improvement of this utility model embodiment, the aerodynamic arrangement of described expanded letter fuselage is: head (2)
Trousers hatch door (1) Guan Bi time degree of slipping over, the appearance profile of the cross section of middle fuselage (3) is smooth, and afterbody (4) is in order to subtract
Slight drag and smooth excessively reduce, with landing gear trousers (5) below middle fuselage, head (2), middle fuselage (3), afterbody
(4) described expanded letter fuselage is formed together.
As the further improvement of this utility model embodiment, the high aspect ratio wing of described band winglet (8)
Aerodynamic arrangement is: wing root wing (6), middle wing (7), winglet (8) form described high aspect ratio wing, great Zhan string together
It is high mounted wing, lower anti-, sweepback than wing；The aspect ratio of high aspect ratio wing is 5.2, inverted diherdral is 2 °, established angle is 3 °；Wing root
Leading edge of a wing angle of sweep is 35 °, and wing root trailing edge angle of sweep is 0 °；Middle leading edge of a wing angle of sweep is 35 °, after middle trailing edge
Sweep angle is 21 °；Winglet (8) area and high aspect ratio wing area ratio are 11%；High aspect ratio wing trailing edge is with the flap
The wing (9), outer wing flap (10), aileron (11)；Wing flap (9) area and high aspect ratio wing area ratio are 3%, outer wing flap (9) face
Long-pending is 5% with high aspect ratio wing area ratio, and aileron (11) area and high aspect ratio wing area ratio are 10%；Great Zhan string
21.2m more a length of than the wing root chord of wing, in the wing, chord length is 13.638m, a length of 3.6m of tip chord, and winglet chord length is 1.5m；
High aspect ratio wing aerofoil profile is AH-21.
As the further improvement of this utility model embodiment, the aerodynamic arrangement of described lift horizontal tail is: lift horizontal tail
(12) it is tapered airfoil, upper anti-, sweepback, and with stagewise elevator (13)；The upper counterangle of lift horizontal tail (12) is 7 °, established angle
It it is 3 °；The leading edge sweep of lift horizontal tail (12) is 40 °, and trailing sweep is 28 °；The aspect ratio of lift horizontal tail (12) is 2.8；
Stagewise elevator (13) area and lift horizontal tail (12) area ratio are 18%；The a length of 11.2m of lift horizontal tail wing root chord, lift
The a length of 6.2m of horizontal tail tip chord；Lift horizontal tail aerofoil profile is AG10.
As the further improvement of this utility model embodiment, the aerodynamic arrangement of described double fins flare is: double fins
Camber angle is 15 °, and vertical tail is divided into upper vertical tail (14) and lower vertical tail (15) two sections by lift horizontal tail, and with segmentation linkage rudder
(16)；Upper vertical tail (14), lower vertical tail (15) are trapezoidal, and the aerofoil profile of vertical tail is symmetrical airfoil；Segmentation linkage rudder (16) face
Long-pending is 20% with vertical tail area ratio；The a length of 3.816m of vertical tail upper chord, in vertical tail, chord-length is 9m, and under vertical tail, chord-length is
3.28m；Vertical tail aerofoil profile is NA006T.
As the further improvement of this utility model embodiment, pneumatic cloth under the wings of an airplane installed by described fanjet
Office is: under left and right high aspect ratio wing, symmetry respectively hangs 2 fanjets (18), and the outer wall of fanjet (18) is short
Cabin (19) is hung by hanger (17) and is forward extended out.
As shown in Figure 7, Figure 8 and Figure 9, utilize CFD software for calculation to calculate it and there is under high reynolds number good pneumatic spy
Property, in the range of low incidence, lift-drag ratio is big, and its maximum lift-drag ratio is 18.95, and stalling angle is relatively big, when the angle of attack is 12 ° still without
Stall event occurs.
The above embodiment is only preferred embodiment of the present utility model, and the not feasible enforcement of this utility model
Exhaustive.For one of ordinary skill in the art, to its institute on the premise of without departing substantially from this utility model principle and spirit
Any obvious change made, within all should being contemplated as falling with claims of the present utility model.
Therefore, protection domain of the present utility model should be as the criterion with described scope of the claims.
Claims (6)
1. an aerodynamic arrangement for the big aircraft of strategy, including the aerodynamic arrangement of fuselage, wing, horizontal tail, vertical tail and electromotor, its
It is characterised by: the aerodynamic arrangement of expanded letter fuselage, the aerodynamic arrangement of the high aspect ratio wing of band winglet, lift horizontal tail pneumatic
Aerodynamic arrangement under the wings of an airplane installed by layout, the aerodynamic arrangement of double fins flare, and fanjet.
The aerodynamic arrangement of the big aircraft of a kind of strategy the most according to claim 1, it is characterised in that the gas of described expanded letter fuselage
The concrete structure of dynamic layout is: trousers hatch door (1) the Guan Bi time degree of slipping over of head (2), outside the cross section of middle fuselage (3)
Shape contour smoothing, afterbody (4) smooth excessively reduces, with landing gear trousers below middle fuselage to reduce resistance
(5), head (2), middle fuselage (3), afterbody (4) form described expanded letter fuselage together.
The aerodynamic arrangement of the big aircraft of a kind of strategy the most according to claim 1, it is characterised in that described band winglet
(8) concrete structure of high aspect ratio wing aerodynamic arrangement is: wing root wing (6), middle wing (7), winglet (8) group together
High aspect ratio wing described in one-tenth, high aspect ratio wing is high mounted wing, lower anti-, sweepback；The aspect ratio of high aspect ratio wing is 5.2
～6.2, inverted diherdral be 2 °～4 °, established angle be 3 °～4 °；Wing root leading edge of a wing angle of sweep is 35 °～45 °, wing root trailing edge
Angle of sweep is 0 °；Middle leading edge of a wing angle of sweep is 35 °～45 °, and middle trailing edge angle of sweep is 21 °～31 °；Winglet (8)
Area and high aspect ratio wing area ratio are 11%～15%；High aspect ratio wing trailing edge is with wing flap (9), outer wing flap
(10), aileron (11)；Wing flap (9) area and high aspect ratio wing area ratio are 3%～5%, outer wing flap (9) area and great Zhan
String is 5%～8% than the ratio of wing area, and aileron (11) area and high aspect ratio wing area ratio are 10%～12%.
The aerodynamic arrangement of the big aircraft of a kind of strategy the most according to claim 1, it is characterised in that described lift horizontal tail
The concrete structure of aerodynamic arrangement is: lift horizontal tail (12) is tapered airfoil, upper anti-, sweepback, and with stagewise elevator (13)；Rise
The upper counterangle of power horizontal tail (12) is 7 °～10 °, and established angle is 3 °～5 °；The leading edge sweep of lift horizontal tail (12) be 40 °～
45 °, trailing sweep is 28 °～32 °；The aspect ratio of lift horizontal tail (12) is 2.8～3.5；Stagewise elevator (13) area
It is 18%～25% with lift horizontal tail (12) area ratio.
The aerodynamic arrangement of the big aircraft of a kind of strategy the most according to claim 1, it is characterised in that described double fins flare
The concrete structure of aerodynamic arrangement be: double fins camber angle is 15 °～25 °, vertical tail by lift horizontal tail be divided into upper vertical tail (14) and
Lower vertical tail (15) two sections, and with segmentation linkage rudder (16)；Upper vertical tail (14), lower vertical tail (15) are trapezoidal, vertical tail
Aerofoil profile is symmetrical airfoil；Segmentation linkage rudder (16) area is 20%～25% with vertical tail area ratio.
The aerodynamic arrangement of the big aircraft of a kind of strategy the most according to claim 1, it is characterised in that described fanjet
The concrete structure installing aerodynamic arrangement under the wings of an airplane is: under left and right high aspect ratio wing, symmetry respectively hangs 2 turbofans and sends out
Motivation (18), the outer wall nacelle (19) of fanjet (18) is hung by hanger (17) and is forward extended out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620708617.3U CN205738056U (en) | 2016-07-06 | 2016-07-06 | A kind of aerodynamic arrangement of the big aircraft of strategy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620708617.3U CN205738056U (en) | 2016-07-06 | 2016-07-06 | A kind of aerodynamic arrangement of the big aircraft of strategy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205738056U true CN205738056U (en) | 2016-11-30 |
Family
ID=57377908
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620708617.3U Expired - Fee Related CN205738056U (en) | 2016-07-06 | 2016-07-06 | A kind of aerodynamic arrangement of the big aircraft of strategy |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205738056U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110046448A (en) * | 2019-04-23 | 2019-07-23 | 中国人民解放军海军航空大学 | A kind of carrier landing course line side clocking method |
| CN111017190A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Large-scale civil passenger plane of integration overall arrangement |
-
2016
- 2016-07-06 CN CN201620708617.3U patent/CN205738056U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110046448A (en) * | 2019-04-23 | 2019-07-23 | 中国人民解放军海军航空大学 | A kind of carrier landing course line side clocking method |
| CN111017190A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Large-scale civil passenger plane of integration overall arrangement |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103552682B (en) | A kind of all-wing aircraft and buzzard-type wing connection wing airplane | |
| CN203666966U (en) | Canard wing configuration aircraft provided with movable strakes | |
| CN106005366A (en) | Pneumatic layout of dual flying wings of UAV (Unmanned Aerial Vehicle) | |
| CN106043668B (en) | A kind of aerodynamic arrangement of three-control aircraft | |
| CN108639339B (en) | Pneumatic layout of unmanned aerial vehicle | |
| CN107187599B (en) | High-altitude long-endurance aircraft pneumatic layout adopting double-height rear wing three-wing surface | |
| CN204399465U (en) | A kind of anury all-wing aircraft many controlsurfaces unmanned plane | |
| CN103171766A (en) | Short distance rising and landing unmanned all-wing aircraft | |
| CN103231795A (en) | Corporate aircraft engine upper placement and front swept wing duck type layout | |
| CN110254720A (en) | A kind of Flying-wing's solar energy unmanned plane | |
| CN205738058U (en) | A kind of aerodynamic arrangement of three-control aircraft | |
| CN109050918A (en) | A kind of low speed target drone aerodynamic arrangement | |
| CN208412143U (en) | A kind of aerodynamic arrangement being coupled wing unmanned plane | |
| CN205738056U (en) | A kind of aerodynamic arrangement of the big aircraft of strategy | |
| CN101774429A (en) | Small UAV aerodynamic layout for vertical rope-type recovery | |
| CN209176908U (en) | A kind of rotor fixed-wing unmanned plane of composite drive | |
| CN106828933A (en) | A kind of HAE tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference | |
| CN106828872B (en) | Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage | |
| CN206719524U (en) | It is a kind of to reduce wing structure of the winglet to wing root bending moment | |
| CN206749416U (en) | A kind of VTOL flight automobile pneumatic layout structure | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN208647149U (en) | A kind of UAV aerodynamic layout | |
| CN206679269U (en) | A kind of double hair unmanned planes | |
| CN207902734U (en) | A kind of unmanned plane of aerodynamic arrangement | |
| CN107215462B (en) | Landing method and landing device for vertical take-off and landing fixed wing unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161130 Termination date: 20190706 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |