CN1143589A - Combined wing aircraft - Google Patents
Combined wing aircraft Download PDFInfo
- Publication number
- CN1143589A CN1143589A CN 95109756 CN95109756A CN1143589A CN 1143589 A CN1143589 A CN 1143589A CN 95109756 CN95109756 CN 95109756 CN 95109756 A CN95109756 A CN 95109756A CN 1143589 A CN1143589 A CN 1143589A
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- CN
- China
- Prior art keywords
- wing
- combined
- aircraft
- driving engine
- wing aircraft
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
- B64C39/068—Aircraft not otherwise provided for having disc- or ring-shaped wings having multiple wings joined at the tips
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
An airplane with composite wing features use of double wings design, that is, a pair of swept-back wings is attached to front half of fuselage, a pair of swept-forward wings is attached to back half of fuselage, and they are not in a same horizontal plane. The ends of said swept-back and swept-forward wings are connected via a multifunctional vertical wing or engine.
Description
The present invention establishes and a kind of combined wing aircraft.
At present, the wing of aircraft employing has Dan Zhiyi, two straight wing, swept wing, adjustable wing, some countries at present also in research buzzard-type wing technology.In these wings, the low-speed performance of Dan Zhiyi, two straight wings is fine, but high speed performance is very poor.Swept wing then high speed performance is fine, but low-speed performance is very poor.For aircraft is taken into account at a high speed and low-speed performance, people have invented adjustable wing plane, but the wing structure complexity of this aircraft, weight strengthen, strength character descends.Buzzard-type wing has been compared aerodynamic characteristic preferably with swept wing, but has influenced its employing because existing this problem of aeroelastic divergence.Because the development of new material, up-to-date technology at present makes people know about the certainly preliminary way of this problem to a certain extent, but adopts this technology also not accomplish from present on large aircraft at all.
Next century, being in great demand of skymaster.USA and Europe producer is all developing this type unexpectedly mutually.In the development of this project, mainly contain two kinds of technical schemes at present: the one, development wing body association aircraft; The one, the size and the span that strengthen conventional airplane.The implementation phase that preceding a kind of scheme not entering at present as yet, then a kind of scheme is subjected to the restriction of airport installation up till now again, can not strengthen arbitrarily.
Aircraft awing, the whole weight of fuselage has all affacted wing and fuselage intersects part, this is little to the blimp influence, the increase fuselage that big-and-middle-sized aircraft then will be bigger in order to satisfy requirement of strength and the application of the strength materials on the wing, thereby the weight of bigger increase aircraft.
Ship-board aircraft often adopts folding wing owing to be subjected to the restriction in aircraft carrier space, to increase the carrier aircraft amount.And this wing is compared with the not folding wing of phase homotype shape, and then complex structure, weight increasing, conservative factor descend.
Hydroairplane is subjected to the restriction of state-of-the art, and storm resistance is low, and flying speed is slow.The needs of considering fluid behaviour waterborne owing to fuselage bottom are designed to ship shape, thereby its aerial aerodynamic characteristic is descended.
Purpose of the present invention is exactly will be according to the deficiency of above said various aircrafts existence, adopt a kind of combined wing aircraft of novelty, design respectively high, low speed performance tool good, simple comparatively speaking, the structure distribution of structure reasonably, low weight, aircraft small span, that outstanding behaviour at sea is arranged series come, thereby overcome the deficiency that above said various aircrafts exist.
The object of the present invention is achieved like this: this series aircraft is made of body, driving engine, wing, vertical tail, tailplane etc.It is characterized in that: this aircraft series adopts the design of the two-shipper wing, in the front portion of fuselage one swept wing is set, and at the rear portion of fuselage one buzzard-type wing is set.Two wings divide other below that is in fuselage and top and are not on the horizon.The wing tip place of two wings couples together by a multi-functional normal limb.The wing tip place of two wings also can connect by a driving engine.Design driving engine and the swept wing position of this moment, to suck driving engine to flow air stream along the bentwing span, promptly can increase engine charge pressure, can eliminate the accumulation of boundary-layer again, thereby can improve the aerodynamic characteristic of aircraft preferably at the wing tip place.Driving engine is contained in the wing root place of aircraft buzzard-type wing, also can sucks driving engine to flow air stream, thereby increase engine charge pressure along the exhibition of buzzard-type wing wing.For the intensity of the wing that increases the intensity of wing, especially hydroairplane, the wing of back can be designed to certain dihedral that has a down dip, and the wing of underbelly can be designed to certain updip dihedral.The multi-functional normal limb at wing tip place or driving engine be arranged so that the aeroelasticity convergence phenomenon that aeroelastic divergence phenomenon that buzzard-type wing exists and swept wing exist is eliminated at this.Wing winglet function design is slightly pressed in the front portion of this multi-functional normal limb, vertical tail can be positioned on here when the rear portion needs, and makes this multi-functional normal limb that wing winglet slightly be arranged; Vertical tail; The forward and backward wing structure of plunderring is strengthened; Balance is forward and backward plunders comprehensive functions such as aeroelastic divergence that the wing exists respectively and aeroelasticity convergence.The driving engine of this series aircraft promptly can adopt the piston type airscrew engine, also can adopt propeller turbine, turbofan engine, turbojet.Driving engine promptly can be positioned on wing root place (jet-propelled), also can be positioned on the wing tip place, promptly can be positioned on forward and backward plunderring on the wing, also can be positioned on the top of tail both sides or tail.The forward and backward wing of plunderring also can combine design with canard, strake wing, to improve the aerodynamic characteristic of aircraft.
Owing to adopted the wing of this combined type, make this aircraft compare with the aircraft that adopts single-wing, structure distribution is more reasonable, under the situation of proof strength, can alleviate the weight of aircraft largely.Guaranteeing lift even increasing under the situation of lift, can dwindle the span.And the behaviour at sea of increase hydroairplane.
The present invention is described further below in conjunction with drawings and Examples:
Fig. 1 is common three scheme drawings of combined wing aircraft.
Fig. 2 is three scheme drawings of a float-plane version combined wing aircraft.
Body 1, swept wing 2, driving engine 3, wing flap 4, buzzard-type wing 5, buzzard-type wing wing flap or tailplane 6, tailplane 7, vertical tail 8, preceding wheel 9, back wheel 10, buoyancy tank 11, fuel tank 12 among the figure.
Fig. 1 is a common combined wing aircraft scheme drawing.One swept wing 2 is set below forebody, a buzzard-type wing 5 is set above fuselage afterbody.Two wings divide other below that is in fuselage and top and are not on the horizon.The wing tip place of two wings couples together by a driving engine, and the office of another kind of portion of this aircraft can adopt a swept wing 2 is set above forebody, and a buzzard-type wing 5 is set below fuselage afterbody.The wing tip place of two wings also can couple together by a multi-functional normal limb.Select the area of suitable buzzard-type wing wing flap 6 just this buzzard-type wing wing flap can be used as tailplane, thus cancellation tailplane 7.
Fig. 2 is a float-plane version combined wing aircraft scheme drawing.One swept wing 2 is set below forebody, a buzzard-type wing 5 is set above fuselage afterbody.Driving engine 3 is positioned on the top of tail, and the both sides of driving engine are provided with the U type tail, and fuel tank 12 promptly can be arranged on the wing root place, also can be arranged on the appropriate location at wing tip place.
Claims (7)
1, a kind of combined wing aircraft is made of body, driving engine, wing, vertical tail, tailplane etc.It is characterized in that: this aircraft adopts the design of the two-shipper wing, one swept wing 2 is set in the front portion of fuselage, one buzzard-type wing 5 is set at the rear portion of fuselage, two wings divide other below that is in fuselage and top and are not on the horizon, the wing tip place of two wings couples together by a multi-functional normal limb, and the wing tip place of two wings also can connect by a driving engine.Design driving engine 3 and the swept wing position of 2 this moments, to suck driving engine to flow air stream along the bentwing span, promptly can increase engine charge pressure, can eliminate the accumulation of boundary-layer again at the wing tip place, thereby can improve the aerodynamic characteristic of aircraft preferably, the wing of back is designed to certain dihedral that has a down dip, and the wing of underbelly is designed to certain updip dihedral.Wing winglet function design is slightly pressed in the front portion of the multi-functional normal limb at wing tip place, vertical tail can be positioned on here when the rear portion needs, and makes this multi-functional normal limb that wing winglet slightly be arranged; Vertical tail; The forward and backward wing structure of plunderring is strengthened; Balance is forward and backward plunders comprehensive functions such as aeroelastic divergence that the wing exists respectively and aeroelasticity convergence.
2, combined wing aircraft according to claim 1 is characterized in that: the driving engine of this combined wing aircraft promptly can adopt the piston type airscrew engine, also can adopt propeller turbine, turbofan engine, turbojet.
3, according to claim 1,2, described combined wing aircraft, it is characterized in that: this combined wing aircraft driving engine 3 promptly can be positioned on wing root place (jet-propelled); Also can be positioned on the wing tip place; Or be positioned on forward and backward plunderring on the wing; Or be positioned on the tail both sides; Or be positioned on tail top.
4, combined wing aircraft according to claim 1 is characterized in that: the forward and backward wing of plunderring of this combined wing aircraft is used in combination with canard, strake wing.
5, combined wing aircraft according to claim 1 is characterized in that: the tailplane 7 of this combined wing aircraft promptly can be combined into an integral body with buzzard-type wing 5, also can be provided with separately.
6, combined wing aircraft according to claim 1 is characterized in that: when this combined wing aircraft is a float-plane version, a swept wing 2 is set below forebody, a buzzard-type wing 5 is set above fuselage afterbody.Driving engine 3 is positioned on the top of tail, and the both sides of driving engine are provided with the U type tail.
7, combined wing aircraft according to claim 1 is characterized in that: the fuel tank 12 of this combined wing aircraft is arranged in the body; Or be arranged on extra-organismal wing root place; Or be arranged on the below of the multi-functional normal limb 4 at wing tip place; Or these several places are provided with simultaneously.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 95109756 CN1143589A (en) | 1995-08-18 | 1995-08-18 | Combined wing aircraft |
| PCT/CN1996/000071 WO1997007020A1 (en) | 1995-08-18 | 1996-08-19 | A multi-winged aircraft |
| AU67316/96A AU6731696A (en) | 1995-08-18 | 1996-08-19 | A multi-winged aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 95109756 CN1143589A (en) | 1995-08-18 | 1995-08-18 | Combined wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1143589A true CN1143589A (en) | 1997-02-26 |
Family
ID=5077339
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 95109756 Pending CN1143589A (en) | 1995-08-18 | 1995-08-18 | Combined wing aircraft |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN1143589A (en) |
| AU (1) | AU6731696A (en) |
| WO (1) | WO1997007020A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101830280A (en) * | 2010-05-06 | 2010-09-15 | 张伟 | Aerodynamic configuration of aircraft |
| CN101549754B (en) * | 2009-04-29 | 2012-05-23 | 北京航空航天大学 | Rotary fixed wing composite aircraft and design method thereof |
| CN104684803A (en) * | 2011-12-30 | 2015-06-03 | 航空集团联合控股公司 | Agile aircraft |
| CN105564633A (en) * | 2015-10-22 | 2016-05-11 | 龙川 | Wing flap lift enhancement type joined-wing airplane with approximately horizontal rotation propellers |
| CN116252944A (en) * | 2023-05-11 | 2023-06-13 | 北京航空航天大学 | High lift-drag ratio tight coupling double-wing pneumatic layout of medium-low Reynolds number micro aircraft |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2936490B1 (en) * | 2008-09-30 | 2011-05-20 | Airbus France | AIRCRAFT HAS AT LEAST TWO MOTORS |
| CN107097952A (en) * | 2017-05-10 | 2017-08-29 | 郑州航空工业管理学院 | A kind of novel and multifunctional boxlike connection wing aquatic unmanned aerial vehicle |
| US10640212B1 (en) * | 2018-11-18 | 2020-05-05 | Faruk Dizdarevic | Double wing aircraft |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1803132A1 (en) * | 1968-10-15 | 1970-04-16 | Hamburger Flugzeugbau Gmbh | Aircraft with several wings arranged one behind the other and having different spans |
| GB1262419A (en) * | 1970-07-09 | 1972-02-02 | Rolls Royce | Aircraft engine mountings |
| US3834654A (en) * | 1973-03-19 | 1974-09-10 | Lockheed Aircraft Corp | Boxplane wing and aircraft |
| US4053125A (en) * | 1973-08-30 | 1977-10-11 | Alexander Ratony | Staggered channel wing-type aircraft |
| DE2641468C2 (en) * | 1976-09-15 | 1985-06-13 | Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn | Airplane with engines arranged above the wings |
| US4146199A (en) * | 1977-08-01 | 1979-03-27 | Phoenixbird, Inc. | Multi-winged lifting body aircraft |
| US4365773A (en) * | 1979-04-11 | 1982-12-28 | Julian Wolkovitch | Joined wing aircraft |
| US4336913A (en) * | 1979-10-02 | 1982-06-29 | Hall Eric B | Compound wing aircraft |
| US5415365A (en) * | 1993-11-08 | 1995-05-16 | Ratliff; Paul D. | High performance amphibious aircraft |
-
1995
- 1995-08-18 CN CN 95109756 patent/CN1143589A/en active Pending
-
1996
- 1996-08-19 WO PCT/CN1996/000071 patent/WO1997007020A1/en active Application Filing
- 1996-08-19 AU AU67316/96A patent/AU6731696A/en not_active Abandoned
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101549754B (en) * | 2009-04-29 | 2012-05-23 | 北京航空航天大学 | Rotary fixed wing composite aircraft and design method thereof |
| CN101830280A (en) * | 2010-05-06 | 2010-09-15 | 张伟 | Aerodynamic configuration of aircraft |
| CN104684803A (en) * | 2011-12-30 | 2015-06-03 | 航空集团联合控股公司 | Agile aircraft |
| CN105564633A (en) * | 2015-10-22 | 2016-05-11 | 龙川 | Wing flap lift enhancement type joined-wing airplane with approximately horizontal rotation propellers |
| CN116252944A (en) * | 2023-05-11 | 2023-06-13 | 北京航空航天大学 | High lift-drag ratio tight coupling double-wing pneumatic layout of medium-low Reynolds number micro aircraft |
| CN116252944B (en) * | 2023-05-11 | 2023-08-11 | 北京航空航天大学 | High lift-drag ratio tight coupling double-wing pneumatic layout of medium-low Reynolds number micro aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| AU6731696A (en) | 1997-03-12 |
| WO1997007020A1 (en) | 1997-02-27 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C06 | Publication | ||
| PB01 | Publication | ||
| C01 | Deemed withdrawal of patent application (patent law 1993) | ||
| WD01 | Invention patent application deemed withdrawn after publication |