WO1997007020A1 - Aeronef a ailes multiples - Google Patents

Aeronef a ailes multiples Download PDF

Info

Publication number
WO1997007020A1
WO1997007020A1 PCT/CN1996/000071 CN9600071W WO9707020A1 WO 1997007020 A1 WO1997007020 A1 WO 1997007020A1 CN 9600071 W CN9600071 W CN 9600071W WO 9707020 A1 WO9707020 A1 WO 9707020A1
Authority
WO
WIPO (PCT)
Prior art keywords
wing
wings
engine
fuselage
swept
Prior art date
Application number
PCT/CN1996/000071
Other languages
English (en)
Chinese (zh)
Inventor
Fuquan Liang
Original Assignee
Fuquan Liang
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Fuquan Liang filed Critical Fuquan Liang
Priority to AU67316/96A priority Critical patent/AU6731696A/en
Publication of WO1997007020A1 publication Critical patent/WO1997007020A1/fr

Links

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

Definitions

  • the present invention relates to an aircraft, and more particularly to a composite wing aircraft, that is, an aircraft provided with a swept-back wing and a forward-swept wing at the same time.
  • the aircraft adopts single straight wing, double straight wing, swept wing, variable wing, and some countries are currently studying forward swept wing technology.
  • the single-straight wing and double-straight wing have good low-speed performance but poor high-speed performance.
  • the swept wing has good high-speed performance, but low-speed performance is poor, and there is induced drag.
  • people have invented a variable-wing aircraft, but the wing structure of this aircraft is complicated and the weight is increased. Large, reduced strength performance.
  • the forward-swept wing has better aerodynamic characteristics than the backward-swept wing, but its adoption is affected by the problem of aeroelastic divergence. Due to the current development of new materials and technologies, people have a preliminary approach to solve this problem to a certain extent, but it is impossible to adopt this technology on large aircrafts at present.
  • the entire weight of the fuselage affects the intersection of the wing and the fuselage, which has little effect on small aircraft, while large and medium-sized aircraft need to increase the fuselage and wing to meet the strength requirements.
  • carrier-based aircraft Due to the limitation of carrier space, carrier-based aircraft often use foldable wings to increase the amount of aircraft. Compared with non-foldable wings of the same shape, this type of wing has a complicated structure, increased weight, and reduced insurance factor.
  • seaplanes Due to the limitation of the current technical level, seaplanes have low wave resistance and slow flight speed. Because the bottom of the fuselage is designed to take into account the characteristics of the fluid on the water, it is designed into a boat shape, thereby reducing the aerodynamic characteristics therein. Summary of the invention
  • the object of the present invention is to solve the above-mentioned shortcomings of existing aircraft, and provide a new type of aircraft that can satisfy both high and low speed performance, but has a relatively simple structure, a reasonable structure distribution, and a light weight.
  • the invention provides a composite wing aircraft including a fuselage, at least one engine, a vertical tail, a pair of horizontal tails, and a wing device, characterized in that the wing device includes two pairs of wings, a pair They are swept wings at the front of the fuselage. One pair is swept wings at the rear of the fuselage. The two pairs of wings are located above or below the fuselage, not at the same horizontal line. Corresponding wing tips are connected, the wing set under the fuselage of the two pairs of wings is set with an up-tilt, and the wing set above the fuselage is set with a down-tilt.
  • the respective wingtips of the two pairs of wings are connected by an engine, and the engines are located rearward of the wingtips of the swept wing in order to draw the spanwise flow that flows along the wingspan of the swept wings into the engine.
  • This can not only increase the intake pressure of the engine, but also eliminate the induced resistance, thereby better improving the aerodynamic characteristics of the aircraft.
  • the respective wing tips of the two pairs of wings are connected by a multifunctional vertical wing, and the front part of the multifunctional vertical wing is provided with the function of a winglet.
  • the rear part of the multifunctional vertical wing is also used as a vertical tail.
  • the engine may be one of a piston propeller engine, a turboprop engine, a turbofan engine, and a turbojet engine.
  • the forward swept wing and the backward swept wing are used in combination with a duck wing and a side wing.
  • the horizontal tail wing and the forward swept wing may be integrated into a whole.
  • the aircraft is a seaplane including a plurality of floating tanks, the swept-back wings are disposed below the front of the fuselage, and the swept-wings are disposed on the Above the rear of the fuselage, the engines are two engines mounted on the upper part of the tail, and the vertical tails are provided on both sides of the engine in a V shape.
  • the floating tank is provided at one or more of a fuselage, a wing root outside the fuselage, or a wing tip, and a lowermost part of the multifunctional vertical wing.
  • this aircraft Due to the use of this composite wing, this aircraft has good aerodynamic characteristics. Two problems, and compared with single-wing aircraft, the structure distribution of this aircraft is more reasonable. Under the condition of ensuring the strength, it can greatly reduce the weight of the aircraft. Under the condition of ensuring lift or even increasing lift, Wingspan can be reduced. When used in seaplanes, it can increase the wave resistance of seaplanes.
  • FIG. 1 to 3 show a first embodiment of the composite wing aircraft of the present invention, wherein FIG. 1 is a front view, FIG. 2 is a top view, and FIG. 3 is a side view, which shows a pair of forward swept wings and a pair of The wingtips of the swept wings are connected by an engine, respectively;
  • FIG. 4 to 6 show a modification of the first embodiment of the composite wing aircraft of the present invention, wherein FIG. 3 is a front view, FIG. 4 is a top view, and FIG. 5 is a side view, which shows a pair of front The wing tips of a swept wing and a pair of swept wing are connected by a multifunctional vertical wing respectively;
  • FIG. 7 to 9 show a second embodiment of the composite wing aircraft of the present invention, which is used for a seaplane, wherein FIG. 7 is a front view, FIG. 8 is a top view, and FIG. 9 is a side view. Best Mode of the Invention
  • FIG. 1 to 3 show a first embodiment of a composite wing aircraft of the present invention.
  • This is a general military or civilian aircraft, which includes a fuselage 1, at least one engine 3, a pair of swept wings 2, A pair of swept wing flaps 5, a pair of forward swept wings 6,-a forward swept wing flap 7, a pair of horizontal tail fins 8, 8, (which can be connected to the forward swept wing as shown by the solid line in Fig. 1
  • the integrated horizontal tail wing 8 ′ or the separated horizontal tail wing 8), a vertical tail wing 9, a plurality of front wheels 10, and a plurality of rear wheels 11, are shown as dashed lines.
  • the invention is characterized in that a forward swept wing and a backward swept wing 2 are simultaneously provided on one aircraft.
  • the swept-back wings are disposed below the front of the fuselage, and the swept-wings 6 are disposed above the rear of the fuselage.
  • the swept-back wing 2 can also be set above the fuselage, and the forward-swept wing 6 can be set below the fuselage.
  • the two pairs of wings are above and above the fuselage, and not on a horizontal line.
  • the corresponding wing tips of the two pairs of wings are connected by an engine 3.
  • the corresponding wing tips of the two pairs of wings can also be connected by a multifunctional vertical wing 4 respectively.
  • the engine 3 may be arranged at the rear of the wing tip of the swept wing, so as to draw the spanwise flow that flows along the wing span of the swept wing into the engine. In order to eliminate the induced resistance, the aerodynamic characteristics of the aircraft can be improved.
  • the engine is installed at the wing root of the forward-swept wing of the aircraft, and the spanwise flow along the forward-swept wing spanwise direction can be drawn into the engine, thereby increasing the engine intake pressure.
  • the wing or engine makes the aeroelastic divergence phenomenon of the forward swept wing and the aeroelastic convergence phenomenon of the back swept wing eliminated.
  • the wing at the upper part of the fuselage can be designed with a certain downward tilt, and the wing at the lower part of the fuselage can be designed with a certain upward tilt.
  • the front part of the multifunctional vertical wing is designed according to the winglet winglet function, and the rear part of the multifunctional vertical wing can be placed here when necessary, so that the multifunctional vertical wing has a wingtip at the same time Winglets; vertical tails; strengthened forward and swept wing structure; balance the comprehensive functions of aeroelastic divergence and aeroelastic convergence of the forward and swept wings respectively.
  • the engine of the aircraft of the present invention may be a piston propeller engine, or a turboprop engine, a turbofan engine, or a jet engine.
  • the engine can be installed at the root of the wing (when using a jet engine) or at the tip of the wing. It can be installed on the forward or backward swept wings, or on both sides of the tail or on the upper part of the tail.
  • the forward and backward swept wings can also be combined with duck wings and side wings to improve the aerodynamic characteristics of the aircraft.
  • Figures 7-9 show a second embodiment of the composite wing aircraft of the present invention, which is a water-based composite wing aircraft.
  • a pair of swept wings 2 is provided below the front of the fuselage, and a pair of swept wings 6 is provided above the rear of the fuselage.
  • the two engines 3 are mounted on the upper part of the tail, and there is an engine air inlet 14 in front of the engine, and V-shaped tail fins 13 are arranged on both sides of the engine.
  • the two engines share an air inlet, so that after entering the air inlet, the air will be biased to both sides. This structure has a great advantage in preventing bird collisions.
  • the pontoon 12 may be provided at the wing root or at an appropriate position at the wing tip.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un aéronef à ailes multiples qui, selon l'invention, est équipé de deux paires d'ailes. Une paire d'ailes à flèche positive (2) est disposée dans une partie avant du fuselage. Une paire d'ailes à flèche négative (6) est disposée dans une partie arrière du fuselage. La première paire et la deuxième paire d'ailes susmentionnées sont respectivement disposées dans des parties supérieure et inférieure du fuselage, mais pas dans le même plan horizontal. L'extrémité des ailes à flèche négative et celle des ailes à flèche positive sont reliées par des ailettes verticales dotées de plusieurs fonctions ou moteurs.
PCT/CN1996/000071 1995-08-18 1996-08-19 Aeronef a ailes multiples WO1997007020A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU67316/96A AU6731696A (en) 1995-08-18 1996-08-19 A multi-winged aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN 95109756 CN1143589A (zh) 1995-08-18 1995-08-18 复合翼飞机
CN95109756.3 1995-08-18

Publications (1)

Publication Number Publication Date
WO1997007020A1 true WO1997007020A1 (fr) 1997-02-27

Family

ID=5077339

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN1996/000071 WO1997007020A1 (fr) 1995-08-18 1996-08-19 Aeronef a ailes multiples

Country Status (3)

Country Link
CN (1) CN1143589A (fr)
AU (1) AU6731696A (fr)
WO (1) WO1997007020A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2936490A1 (fr) * 2008-09-30 2010-04-02 Airbus France Avion a au moins deux moteurs
CN107097952A (zh) * 2017-05-10 2017-08-29 郑州航空工业管理学院 一种新型多功能盒式联翼水上无人机
EP3880555A4 (fr) * 2018-11-18 2022-07-20 Faruk Dizdarevic Aéronef à deux ailes

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101549754B (zh) * 2009-04-29 2012-05-23 北京航空航天大学 一种旋定翼复合式飞行器及其设计的方法
CN101830280B (zh) * 2010-05-06 2012-10-10 张伟 一种飞行器气动布局
RU2503584C2 (ru) * 2011-12-30 2014-01-10 Открытое Акционерное Общество "Авиационная Холдинговая Компания "Сухой" Маневренный самолет
CN105564633A (zh) * 2015-10-22 2016-05-11 龙川 近似水平转动推进器襟翼增升连接翼飞机
CN116252944B (zh) * 2023-05-11 2023-08-11 北京航空航天大学 中低雷诺数微小型飞行器的高升阻比紧耦合双翼气动布局

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1803132A1 (de) * 1968-10-15 1970-04-16 Hamburger Flugzeugbau Gmbh Luftfahrzeug mit mehreren hintereinander angeordneten,verschiedene Spannweiten aufweisenden Tragfluegeln
US3735946A (en) * 1970-07-09 1973-05-29 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
US4146199A (en) * 1977-08-01 1979-03-27 Phoenixbird, Inc. Multi-winged lifting body aircraft
US4171786A (en) * 1976-09-15 1979-10-23 Vereinigte Flugtechnische Werke-Fokker Gmbh Aircraft wing with engine mount
US4336913A (en) * 1979-10-02 1982-06-29 Hall Eric B Compound wing aircraft
US4365773A (en) * 1979-04-11 1982-12-28 Julian Wolkovitch Joined wing aircraft
US5415365A (en) * 1993-11-08 1995-05-16 Ratliff; Paul D. High performance amphibious aircraft

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1803132A1 (de) * 1968-10-15 1970-04-16 Hamburger Flugzeugbau Gmbh Luftfahrzeug mit mehreren hintereinander angeordneten,verschiedene Spannweiten aufweisenden Tragfluegeln
US3735946A (en) * 1970-07-09 1973-05-29 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
US4171786A (en) * 1976-09-15 1979-10-23 Vereinigte Flugtechnische Werke-Fokker Gmbh Aircraft wing with engine mount
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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2936490A1 (fr) * 2008-09-30 2010-04-02 Airbus France Avion a au moins deux moteurs
CN107097952A (zh) * 2017-05-10 2017-08-29 郑州航空工业管理学院 一种新型多功能盒式联翼水上无人机
EP3880555A4 (fr) * 2018-11-18 2022-07-20 Faruk Dizdarevic Aéronef à deux ailes

Also Published As

Publication number Publication date
AU6731696A (en) 1997-03-12
CN1143589A (zh) 1997-02-26

Similar Documents

Publication Publication Date Title
CN102826215B (zh) 一种可短距起降的轻小型飞翼载人机
US4030688A (en) Aircraft structures
CN106347663A (zh) 一种翼身融合飞翼布局的无人机
CN210235305U (zh) 一种可变机翼外翼后掠角和可倾斜小翼的飞翼式飞机
CN207860452U (zh) 一种可垂直起降的联翼无人机
CN108639339A (zh) 一种无人机气动布局
EP3880555A1 (fr) Aéronef à deux ailes
CN111516871A (zh) 一种气动隐身一体化设计的超音速隐身无人机
CN103231795A (zh) 一种公务机的发动机上置及前掠翼鸭式布局
CN103171766A (zh) 短距起降无人飞翼
WO2024060633A1 (fr) Aile d'aéronef avec ventilateur canalisé distribué intégré, et aéronef électrique
CN105416587A (zh) 一种翼身融合飞行器气动布局
CN112896499A (zh) 一种倾转涵道与固定螺旋桨组合布局的垂直起降飞行器
CN115571323A (zh) 一种亚声速扁平融合体布局飞行器
WO1997007020A1 (fr) Aeronef a ailes multiples
CN110816806A (zh) 一种集群式仿生太阳能无人机
US20200324871A1 (en) Aircraft wing
CN108502138A (zh) 一种采用前缘支撑翼的前掠翼宽体高亚声速飞行器气动布局
CN113148105A (zh) 一种双机头翼身融合低可探测布局
CN111017190A (zh) 一种融合体布局大型民用客机
CN111532426A (zh) 一种v型尾翼多旋翼垂直起降布局的飞行器
CN208647149U (zh) 一种无人机气动布局
CN115924059A (zh) 一种单后掠飞翼平尾融合气动布局飞机
CN215043673U (zh) 一种倾转涵道与固定螺旋桨组合布局的垂直起降飞行器
CN112027080B (zh) 一种使用双模态动力舱的混电推进垂直起降无人机

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AL AM AT AU AZ BB BG BR BY CA CH CZ DE DK EE ES FI GB GE HU IL IS JP KE KG KP KR KZ LK LR LS LT LU LV MD MG MK MN MW MX NO NZ PL PT RO RU SD SE SG SI SK TJ TM TR TT UA UG US UZ VN AM AZ BY KG KZ MD RU TJ TM

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): KE LS MW SD SZ UG AT BE CH DE DK ES FI FR GB GR IE IT LU MC NL PT SE BF BJ CF CG CI CM GA GN

DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
121 Ep: the epo has been informed by wipo that ep was designated in this application
REG Reference to national code

Ref country code: DE

Ref legal event code: 8642

122 Ep: pct application non-entry in european phase
NENP Non-entry into the national phase

Ref country code: CA