CN204341388U - A kind of passenger plane connecting wing configuration - Google Patents
A kind of passenger plane connecting wing configuration Download PDFInfo
- Publication number
- CN204341388U CN204341388U CN201420675962.2U CN201420675962U CN204341388U CN 204341388 U CN204341388 U CN 204341388U CN 201420675962 U CN201420675962 U CN 201420675962U CN 204341388 U CN204341388 U CN 204341388U
- Authority
- CN
- China
- Prior art keywords
- wing
- root
- fuselage
- passenger plane
- vertical fin
- 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
- 238000005728 strengthening Methods 0.000 claims description 7
- 230000003068 static effect Effects 0.000 abstract description 2
- 238000012913 prioritisation Methods 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 4
- 239000000969 carrier Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000002131 composite material Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a kind of passenger plane connecting wing configuration, comprise fuselage, the first front wing, the second front wing, the first rear wing, the second rear wing, the first end plate, the second end plate, vertical fin and at least one driving engine, wherein, the root of the first front wing, the second front wing is fixedly connected with the both sides of fuselage respectively; The root of vertical fin is fixedly connected with the back segment of fuselage; The root of the first rear wing, the second rear wing is fixedly connected with vertical fin respectively; The upper end of the first end plate is connected with the wingtip of the first rear wing, and lower end is connected with the wingtip of the first front wing; The upper end of the second end plate is connected with the wingtip of the second rear wing, and lower end is connected with the wingtip of the second front wing; Driving engine is arranged on the back segment of fuselage.The utility model aerodynamic characteristic is better than conventional in layout, has larger Longitudinal static stability, and structural distortion is less than independent wing, structural natural frequencies is higher than independent wing.
Description
Technical field
The utility model relates to airline carriers of passengers configuration, particularly relates to a kind of passenger plane connecting wing configuration.
Background technology
The large percentage of induced drag shared by total drag of the passenger plane of cruising phase, can reach about 35%.In order to reduce induced drag, improving 1ift-drag ratio, often adopt high aspect ratio swept back wing in the design, but such wing configuration rigidity is little, easily causes structural weight to increase.But airline carriers of passengers must strict limiting structure weight.This just brings a contradiction: the high-lift systems of large sweepback, high aspect ratio is good, and critical Mach number is high, and the 1ift-drag ratio that cruises is high, but behavior of structure is poor, and especially rigidity is less, and wingtip distortion is comparatively large, if will improve rigidity, weight is again by overweight.
Therefore, the wing of active service airline carriers of passengers has strict restriction to aspect ratio, can not play the advantage of high aspect ratio completely.
In order to meet day by day harsh environmental protection and the requirement of economy, thus following passenger plane towards efficient, energy saving direction development, will derive all kinds of new configuration that may adapt to these and require.Connection wing configuration is exactly the one in these new configurations.Further, along with the development of composite technology, connection wing configuration has more and more possessed the condition implemented.
Utility model content
Technical problem to be solved in the utility model is for defect involved in background technology, provides a kind of passenger plane connecting wing configuration.
The utility model is for solving the problems of the technologies described above by the following technical solutions:
Connect a passenger plane for wing configuration, comprise fuselage, the first front wing, the second front wing, the first rear wing, the second rear wing, the first end plate, the second end plate, vertical fin and at least one driving engine;
The root of described first front wing, the second front wing is fixedly connected with the both sides of described fuselage respectively;
The root of described vertical fin is fixedly connected with the back segment of described fuselage;
The root of described first rear wing, the second rear wing is fixedly connected with described vertical fin respectively;
The upper end of described first end plate is connected with the wingtip of described first rear wing, and lower end is connected with the wingtip of the first front wing;
The upper end of described second end plate is connected with the wingtip of described second rear wing, and lower end is connected with the wingtip of the second front wing;
Described driving engine is arranged on the back segment of fuselage.
As a kind of further prioritization scheme of passenger plane connecting wing configuration of the utility model, the number of described driving engine is two, and symmetry is arranged on the back segment of described fuselage.
As a kind of further prioritization scheme of passenger plane connecting wing configuration of the utility model, the root of described first front wing, the second front wing is fixedly connected with the both sides of described fuselage respectively by No. 1 strengthening rib, and the root of described first rear wing, the second rear wing is fixedly connected with described vertical fin respectively by No. 1 strengthening rib.
As a kind of further prioritization scheme of passenger plane connecting wing configuration of the utility model, the aerofoil profile of described first front wing, the second front wing, the first rear wing, the second rear wing is NACA4415.
As a kind of further prioritization scheme of passenger plane connecting wing configuration of the utility model, the aerofoil profile of described vertical fin is NACA0010.
As a kind of further prioritization scheme of passenger plane connecting wing configuration of the utility model, the length of described first front wing and the second front wing, sharp chord length, root chord length, mean aerodynamic chord, aspect ratio, trapezoidal ratio, mean thickness, leading edge sweep, 1/4 string of a musical instrument sweepback angle, stagger angle, the dihedral angle be respectively 1700mm, 170mm, 282mm, 230mm, 7.64,0.6,0.15,30 °, 28 °, 3 °, 7 °.
As a kind of further prioritization scheme of passenger plane connecting wing configuration of the utility model, the length of described first rear wing, the second rear wing, sharp chord length, root chord length, mean aerodynamic chord, aspect ratio, trapezoidal ratio, mean thickness, leading edge sweep, 1/4 string of a musical instrument sweepback angle, stagger angle, the dihedral angle be respectively 1700mm, 150mm, 150mm, 150mm, 11.33,1,0.15 ,-30 ° ,-30 °, 0 ° ,-7 °.
As a kind of further prioritization scheme of passenger plane connecting wing configuration of the utility model, the length of described vertical fin, sharp chord length, root chord length, mean aerodynamic chord, aspect ratio, trapezoidal ratio, mean thickness, leading edge sweep, 1/4 string of a musical instrument sweepback angle be respectively 237mm, 259mm, 259mm, 259mm, 0.91,1,0.1,30 °, 30 °.
The utility model adopts above technical scheme compared with prior art, has following technique effect:
1. the aerodynamic characteristic of joined-wing configuration is better than normal arrangement, and maximum lift-drag ratio can reach more than 22, and stalling incidence is more than 30 °;
2. due to the nose-down pitching moment that boxlike airplane rear wing lift produces, therefore the aircraft of this layout often has larger Longitudinal static stability;
3. rear portion wing is except providing a part of lift, can also bear the moment of deflection of part wing;
4., when the given span and weight, induced drag can be reduced;
5. lifting surface can carry the radar aerial of various shape, provides the coverage of 360 °;
6., owing to have employed multiple lifting surface, aircraft configuration size can be reduced;
7. when pneumatic equivalence, the structural weight of joined-wing configuration wing is 79.7% ~ 88% of normal arrangement, and the distortion of wing tip vertical direction is only 50% of conventional airfoil;
8. the rear wing of joined-wing configuration has obvious supporting role, and structural distortion is more much smaller than independent wing, and structural natural frequencies is also high than independent wing.
Accompanying drawing explanation
Fig. 1 is the structural representation of connection wing configuration passenger plane.
In figure, 1-fuselage, 2-front wing, 3-rear wing, 4-end plate, 5-vertical fin, 6-driving engine.
Detailed description of the invention
Below in conjunction with accompanying drawing, the technical solution of the utility model is described in further detail:
The utility model discloses a kind of passenger plane connecting wing configuration, the typical configurations of traditional passenger plane " fuselage-wing-horizontal tail-vertical fin " is made into the new-type configuration of " fuselage-front wing-rear wing-vertical fin ", front wing is connected with forebody and rear body respectively with the wing root of rear wing, the wingtip of front wing and rear wing is connected with the lower end of end plate and upper end respectively, defines " the connection wing " configuration that the front and back wing links together.
As shown in Figure 1, the utility model comprises fuselage, front wing, rear wing, vertical fin, end plate, driving engine totally 6 parts, wherein, front wing root is connected with fuselage by No. 1 strengthening rib, and rear wing root is connected with vertical fin by No. 1 strengthening rib, and vertical fin root is connected with aft body, front wing and rear wing pass through end plate connection at wingtip, front wing wingtip is connected to end plate lower end, and rear wing wingtip is connected to end plate upper end, and 2 driving engines are arranged on rear body both sides.Wherein wing parameter is in table 1.
Front wing integral structure adopts two-beam type, and twin beams runs through whole front wing, and after transferring with fuselage junction, run through the central wing box under fuselage floor, the front wing of the left and right sides docks with fuselage in this way.Rear wing also adopts two-beam type, and twin beams is run through rear wing and docked by bolt with the strengthening rib on vertical fin in the region of docking with vertical fin, and such rear wing is also connected with vertical fin.The connection of front wing and end plate is by fixing connecting bolt, and rear wing also adopts identical method and end plate connection.The connection of vertical fin and fuselage adopts fusion type, namely the beam of vertical fin and afterbody bulkhead as a whole, design together, process, such vertical fin becomes a part for fuselage.Install the bulkhead of driving engine and the composition entirety of fuselage bulkhead, such driving engine bulkhead is also connected with fuselage.Linked together by the major part of such mode aircraft.
Claims (8)
1. connect a passenger plane for wing configuration, it is characterized in that, comprise fuselage, the first front wing, the second front wing, the first rear wing, the second rear wing, the first end plate, the second end plate, vertical fin and at least one driving engine;
The root of described first front wing, the second front wing is fixedly connected with the both sides of described fuselage respectively;
The root of described vertical fin is fixedly connected with the back segment of described fuselage;
The root of described first rear wing, the second rear wing is fixedly connected with described vertical fin respectively;
The upper end of described first end plate is connected with the wingtip of described first rear wing, and lower end is connected with the wingtip of the first front wing;
The upper end of described second end plate is connected with the wingtip of described second rear wing, and lower end is connected with the wingtip of the second front wing;
Described driving engine is arranged on the back segment of fuselage.
2. the passenger plane of connection wing configuration according to claim 1, is characterized in that, the number of described driving engine is two, and symmetry is arranged on the back segment of described fuselage.
3. the passenger plane of connection wing configuration according to claim 1, it is characterized in that, the root of described first front wing, the second front wing is fixedly connected with the both sides of described fuselage respectively by No. 1 strengthening rib, and the root of described first rear wing, the second rear wing is fixedly connected with described vertical fin respectively by No. 1 strengthening rib.
4. the passenger plane of connection wing configuration according to claim 1, is characterized in that, the aerofoil profile of described first front wing, the second front wing, the first rear wing, the second rear wing is NACA4415.
5. the passenger plane of connection wing configuration according to claim 4, is characterized in that, the aerofoil profile of described vertical fin is NACA0010.
6. the passenger plane of connection wing configuration according to claim 5, it is characterized in that, the length of described first front wing and the second front wing, sharp chord length, root chord length, mean aerodynamic chord, aspect ratio, trapezoidal ratio, mean thickness, leading edge sweep, 1/4 string of a musical instrument sweepback angle, stagger angle, the dihedral angle be respectively 1700mm, 170mm, 282mm, 230mm, 7.64,0.6,0.15,30 °, 28 °, 3 °, 7 °.
7. the passenger plane of connection wing configuration according to claim 6, it is characterized in that, the length of described first rear wing, the second rear wing, sharp chord length, root chord length, mean aerodynamic chord, aspect ratio, trapezoidal ratio, mean thickness, leading edge sweep, 1/4 string of a musical instrument sweepback angle, stagger angle, the dihedral angle be respectively 1700mm, 150mm, 150mm, 150mm, 11.33,1,0.15 ,-30 ° ,-30 °, 0 ° ,-7 °.
8. the passenger plane of connection wing configuration according to claim 7, it is characterized in that, the length of described vertical fin, sharp chord length, root chord length, mean aerodynamic chord, aspect ratio, trapezoidal ratio, mean thickness, leading edge sweep, 1/4 string of a musical instrument sweepback angle be respectively 237mm, 259mm, 259mm, 259mm, 0.91,1,0.1,30 °, 30 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420675962.2U CN204341388U (en) | 2014-11-13 | 2014-11-13 | A kind of passenger plane connecting wing configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420675962.2U CN204341388U (en) | 2014-11-13 | 2014-11-13 | A kind of passenger plane connecting wing configuration |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204341388U true CN204341388U (en) | 2015-05-20 |
Family
ID=53224678
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420675962.2U Expired - Fee Related CN204341388U (en) | 2014-11-13 | 2014-11-13 | A kind of passenger plane connecting wing configuration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204341388U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111315655A (en) * | 2017-11-02 | 2020-06-19 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for air, water, land or space vehicles |
| CN111572773A (en) * | 2020-05-22 | 2020-08-25 | 中国民用航空飞行学院 | Medium-sized tactical transporter |
| CN112265631A (en) * | 2020-10-16 | 2021-01-26 | 中国空气动力研究与发展中心 | Box-type folding wing unmanned aerial vehicle layout capable of realizing modular assembly with variable aspect ratio |
-
2014
- 2014-11-13 CN CN201420675962.2U patent/CN204341388U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111315655A (en) * | 2017-11-02 | 2020-06-19 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for air, water, land or space vehicles |
| CN111315655B (en) * | 2017-11-02 | 2023-10-27 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for an air, water, land or space vehicle |
| CN111572773A (en) * | 2020-05-22 | 2020-08-25 | 中国民用航空飞行学院 | Medium-sized tactical transporter |
| CN112265631A (en) * | 2020-10-16 | 2021-01-26 | 中国空气动力研究与发展中心 | Box-type folding wing unmanned aerial vehicle layout capable of realizing modular assembly with variable aspect ratio |
| CN112265631B (en) * | 2020-10-16 | 2022-07-12 | 中国空气动力研究与发展中心 | Box-type folding wing unmanned aerial vehicle layout capable of realizing modular assembly with variable aspect ratio |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9637226B2 (en) | Split winglet system | |
| US7300021B2 (en) | Aerospace vehicle fairing systems and associated methods | |
| US7980515B2 (en) | Aircraft wing modification and related methods | |
| US20090084904A1 (en) | Wingtip Feathers, Including Paired, Fixed Feathers, and Associated Systems and Methods | |
| US20040262451A1 (en) | Efficient wing tip devices and methods for incorporating such devices into existing wing designs | |
| CN205633014U (en) | Folding wing vertical take -off and landing aircraft | |
| CN202320772U (en) | High lift device of double-aisle large-type passenger plane | |
| CN102826216A (en) | Aerodynamic configuration of aircraft | |
| CN103171766A (en) | Short distance rising and landing unmanned all-wing aircraft | |
| CN104443344A (en) | Passenger plane with joined-wing configuration | |
| CN110104160B (en) | Middle-distance coupling folding double-wing aircraft | |
| CN103231795A (en) | Corporate aircraft engine upper placement and front swept wing duck type layout | |
| CN113232832B (en) | Amphibious aircraft | |
| CN204341388U (en) | A kind of passenger plane connecting wing configuration | |
| CN105416587A (en) | Aerodynamic layout of aircraft with blended wing body | |
| CN107264774B (en) | A kind of M shape wing high subsonic flight device aerodynamic arrangement using leading edge braced wing | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| US8740139B1 (en) | Leading edge snag for exposed propeller engine installation | |
| US11584506B2 (en) | Aircraft wing assemblies | |
| CN108502138A (en) | A kind of buzzard-type wing expanded letter high subsonic flight device aerodynamic arrangement using leading edge braced wing | |
| CN104192294A (en) | A wing structure and an airplane | |
| US10981645B2 (en) | Drag reduction systems for aircraft | |
| CN111017190A (en) | Large-scale civil passenger plane of integration overall arrangement | |
| CN204750551U (en) | Transportation class aircraft of all -wing aircraft overall arrangement | |
| CN202541831U (en) | Aircraft winglet |
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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150520 Termination date: 20161113 |