CN103072691A - Front-rear-rudder multiple-power-wing airplane - Google Patents
Front-rear-rudder multiple-power-wing airplane Download PDFInfo
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- CN103072691A CN103072691A CN2013100502874A CN201310050287A CN103072691A CN 103072691 A CN103072691 A CN 103072691A CN 2013100502874 A CN2013100502874 A CN 2013100502874A CN 201310050287 A CN201310050287 A CN 201310050287A CN 103072691 A CN103072691 A CN 103072691A
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Abstract
The invention relates to a front-rear-rudder multiple-power-wing airplane. The front-rear-rudder multiple-power-wing airplane comprises a front wing (A) and a rear wing (B) which are symmetrically arranged at the two sides of a fuselage, wherein the rear side of the front wing (A) is provided with a flap (A5) and an aileron (A2), the lower side of the wing (A) is provided with a group of engines (A1), the upper side of the wing (A) is provided with a direction wing (A3), the direction wing is provided with a rudder (A4), the rear side of the rear wing (B) is provided with a flap (B5) and an aileron (B2), the lower side of the wing (B) is provided with a group of engines (B1), the upper side of the wing (B) is provided with a direction wing (B3), and the direction wing is provided with a rudder (B4). Due to the adoption of the technical scheme, the front-rear-rudder multiple-power-wing airplane provided by the invention has the advantages of large takeoff weight, good equilibrium of flight, small turning radius, quick direction change, short gliding distance in takeoff and landing, and the like.
Description
Technical field:
The present invention relates to a kind of aircraft, particularly a kind of many power wings of fore-and-aft direction rudder aircraft.
Background technology:
The take-off weight of aircraft and the size of wing and power have direct relation, owing to be subject to the restriction of material and technology, wing can not unconfinedly strengthen; The design of big-block engine and processing all have a very high technology content, and manufacturing cost and service expenditure height and weight, size, noise are all larger.Because now large aircraft adopts an assembly that the wing of big-block engine is arranged, so maximum take-off weight just is subject to certain restriction; Aircraft now only has afterbody to be provided with yaw rudder, and turning to balance of aircraft also had certain restriction, and again because the gross area of the aileron on the wing and wing flap is less, and takeoff speed and the landing speed of aircraft are higher, it is longer with the landing and sliding distance to take off.
Summary of the invention:
Purpose of the present invention is exactly in order to solve the deficiency of existing aircraft, design a kind of many power wing, multi-aspect rudder, many wing flaps aircraft, be exactly specifically front and rear at fuselage and be provided with wing more than two groups or two groups, wing is provided with wing flap, aileron, yaw rudder and organizes put-put more, to overcome the now above-mentioned shortcoming of large aircraft.
To achieve these goals, the present invention has adopted following technical scheme:
Many power wings of fore-and-aft direction rudder aircraft, it comprises the fuselage of aircraft, it is characterized in that: the front and rear bilateral symmetry of fuselage is provided with front wing, rear wing; Front wing rear side is provided with wing flap, aileron, and the downside of front wing is provided with one group of driving engine, and the upside of front wing is provided with the direction wing, and the direction wing is provided with yaw rudder; Rear wing rear side is provided with wing flap, aileron, and the downside of rear wing is provided with one group of driving engine, and the upside of rear wing is provided with the direction wing, and the direction wing is provided with yaw rudder.The quantity N of driving engine can determine according to the aircraft size more than or equal to 1 on the forward and backward wing.
On the basis of technique scheme, also have following further technical scheme:
Be arranged with the front slave wing on the fuselage of front wing below, front slave wing rear side is provided with wing flap, aileron, and the downside of the front slave wing is provided with one group of driving engine; The quantity N of front slave wing engine can determine according to the aircraft size more than or equal to 1;
Be arranged with the rear slave wing on the fuselage of rear wing below, rear slave wing rear side is provided with wing flap, aileron, and the downside of the rear slave wing is provided with one group of driving engine, and the quantity N of rear slave wing engine can determine according to the aircraft size more than or equal to 1.
Since adopted technique scheme, so that the present invention has the following advantages:
(1), increase power wing quantity, can improve the load carrying ability of aircraft;
(2), increase the quantity of aileron, wing flap, namely increase their gross area, can improve rising or falling speed and decelerating power at any time;
(3), increase the quantity of yaw rudder, namely increase their gross area, thereby improve turning velocity.
For more detailed explanation the present invention, following accompanying drawing provides three most preferred embodiments.
Description of drawings:
Fig. 1 is double dynamical wing aircraft block diagram of the present invention;
Fig. 2 is three engine wing aircraft block diagrams of the present invention:
Fig. 3 is four engine wing aircraft block diagrams of the present invention.
The specific embodiment:
Embodiment one,
Fig. 1 is a kind of many power wings of fore-and-aft direction rudder aircraft provided by the invention, it comprises: forebody is provided with front wing A, and front wing A rear side is provided with wing flap A5, aileron A2, and the downside of front wing is provided with one group of driving engine A1, the upside of front wing is provided with direction wing A3, and the direction wing is provided with yaw rudder A4; Fuselage afterbody is provided with rear wing B, and rear wing B rear side is provided with wing flap B5, aileron B2, and the downside of rear wing is provided with one group of driving engine B1, and the upside of rear wing is provided with direction wing B3, and the direction wing is provided with yaw rudder B4.
EmbodimentTwo,
Fig. 2 is another many power wings of fore-and-aft direction rudder aircraft provided by the invention, it comprises: forebody is provided with front wing A, front wing A rear side is provided with wing flap A5, aileron A2, the downside of front wing is provided with one group of driving engine A1, the upside of front wing is provided with direction wing A3, and the direction wing is provided with yaw rudder A4; Fuselage afterbody is provided with rear wing B, and rear wing B rear side is provided with wing flap B5, aileron B2, and the downside of rear wing is provided with one group of driving engine B1, and the upside of rear wing is provided with direction wing B3, and the direction wing is provided with yaw rudder B4; Be arranged with front slave wing C on the fuselage of front wing A below, front slave wing C rear side is provided with wing flap C5, aileron C2, and the downside of the front slave wing is provided with one group of driving engine C1.
EmbodimentThree,
Fig. 3 is another many power wings of fore-and-aft direction rudder aircraft provided by the invention, it comprises: forebody is provided with front wing A, and front wing A rear side is provided with wing flap A5, aileron A2, and the downside of wing is provided with one group of driving engine A1, the upside of front wing is provided with direction wing A3, and the direction wing is provided with yaw rudder A4; Fuselage afterbody is provided with rear wing B, and rear wing B rear side is provided with wing flap B5, aileron B2, and the downside of rear wing is provided with one group of driving engine B1, and the upside of rear wing is provided with direction wing B3, and the direction wing is provided with yaw rudder B4; Be arranged with front slave wing C on the fuselage of front wing A below, front slave wing C rear side is provided with wing flap C5, aileron C2, and the downside of the front slave wing is provided with one group of driving engine C1; Be arranged with rear slave wing D on the fuselage of rear wing B below, rear slave wing D rear side is provided with wing flap D5, aileron D2, and the downside of the rear slave wing is provided with one group of driving engine D1.
Owing to adopted technique scheme take-off weight is large, flight balance good, turn radius is little so that many power wings of the fore-and-aft direction rudder aircraft that the present invention relates to has, change the orientation fast, take off and landing and sliding apart from the advantage such as short.
Claims (3)
1. many power wings of fore-and-aft direction rudder aircraft comprises it is characterized in that the fuselage of aircraft:
The front and rear bilateral symmetry of a, fuselage is provided with front wing (A), rear wing (B);
B, front wing (A) rear side are provided with wing flap (A5), aileron (A2), and the downside of front wing is provided with one group of driving engine (A1), and the upside of front wing is provided with the direction wing (A3), and the direction wing is provided with yaw rudder (A4);
C, rear wing (B) rear side are provided with wing flap (B5), aileron (B2), and the downside of rear wing is provided with one group of driving engine (B1), and the upside of rear wing is provided with the direction wing (B3), and the direction wing is provided with yaw rudder (B4).
2. many power wings of again fore-and-aft direction rudder aircraft according to claim 1, it is characterized in that: be arranged with the front slave wing (C) on the fuselage of front wing (A) below, the front slave wing (C) rear side is provided with wing flap (C5), aileron (C2), and the downside of the front slave wing is provided with one group of driving engine (C1).
3. many power wings of fore-and-aft direction rudder aircraft according to claim 2, it is characterized in that: be arranged with the rear slave wing (D) on the fuselage of rear wing (B) below, the rear slave wing (D) rear side is provided with wing flap (D5), aileron (D2), and the downside of the rear slave wing is provided with one group of driving engine (D1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013100502874A CN103072691A (en) | 2013-02-08 | 2013-02-08 | Front-rear-rudder multiple-power-wing airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013100502874A CN103072691A (en) | 2013-02-08 | 2013-02-08 | Front-rear-rudder multiple-power-wing airplane |
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| CN103072691A true CN103072691A (en) | 2013-05-01 |
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| CN2013100502874A Pending CN103072691A (en) | 2013-02-08 | 2013-02-08 | Front-rear-rudder multiple-power-wing airplane |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108674631A (en) * | 2018-04-28 | 2018-10-19 | 昆明鞘翼科技有限公司 | The method that upper limb improves wing rigidity and lift is added on plate wing machine tablet wing |
| CN108725790A (en) * | 2018-04-28 | 2018-11-02 | 昆明鞘翼科技有限公司 | A kind of plate wing machine with upper and lower double-vane |
| CN111017205A (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 | Vertical take-off and landing conveyor |
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| US5098034A (en) * | 1989-11-24 | 1992-03-24 | Lendriet William C | Vertical/short takeoff or landing aircraft having a rotatable wing and tandem supporting surfaces |
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| CN2306952Y (en) * | 1997-03-27 | 1999-02-10 | 黄永吉 | Double-wing aircraft capable of landing or taking-off vertically |
| US20060011778A1 (en) * | 2004-07-15 | 2006-01-19 | Small James G | Rotating flying wing aircraft and control system |
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| BRPI0706140A2 (en) * | 2007-09-21 | 2009-05-12 | Galvao Francisco Leme | multi-floor fuselage tandem biplane |
| CN102131696A (en) * | 2008-08-20 | 2011-07-20 | 水翼艇技术株式会社 | Wig vehicle excluding horizontal stabilizer |
| CN203094448U (en) * | 2013-02-08 | 2013-07-31 | 郭建中 | Airplane with front and rear rudders and multiple power wings |
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2013
- 2013-02-08 CN CN2013100502874A patent/CN103072691A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB429948A (en) * | 1933-12-11 | 1935-06-11 | Boulton & Paul Ltd | Improvement in aeroplanes |
| US3006576A (en) * | 1958-12-19 | 1961-10-31 | Enoch A Elijah | Airplane having two separable flyable sections |
| US3954231A (en) * | 1974-09-09 | 1976-05-04 | Fraser Norman T L | Control system for forward wing aircraft |
| US5098034A (en) * | 1989-11-24 | 1992-03-24 | Lendriet William C | Vertical/short takeoff or landing aircraft having a rotatable wing and tandem supporting surfaces |
| CN2156133Y (en) * | 1993-02-10 | 1994-02-16 | 颜定国 | Simple propeller civil airplane |
| CN2306952Y (en) * | 1997-03-27 | 1999-02-10 | 黄永吉 | Double-wing aircraft capable of landing or taking-off vertically |
| US20060011778A1 (en) * | 2004-07-15 | 2006-01-19 | Small James G | Rotating flying wing aircraft and control system |
| CN200988577Y (en) * | 2005-11-07 | 2007-12-12 | 邵厚洪 | Double airframe triphibian aircraft |
| CN101074052A (en) * | 2007-05-24 | 2007-11-21 | 北流市小古乖工艺品店 | Double-wing plane |
| BRPI0706140A2 (en) * | 2007-09-21 | 2009-05-12 | Galvao Francisco Leme | multi-floor fuselage tandem biplane |
| CN201132608Y (en) * | 2007-10-30 | 2008-10-15 | 叶万章 | Large-scale short-distance rising and landing energy-conserving aerotransport |
| CN102131696A (en) * | 2008-08-20 | 2011-07-20 | 水翼艇技术株式会社 | Wig vehicle excluding horizontal stabilizer |
| CN203094448U (en) * | 2013-02-08 | 2013-07-31 | 郭建中 | Airplane with front and rear rudders and multiple power wings |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108674631A (en) * | 2018-04-28 | 2018-10-19 | 昆明鞘翼科技有限公司 | The method that upper limb improves wing rigidity and lift is added on plate wing machine tablet wing |
| CN108725790A (en) * | 2018-04-28 | 2018-11-02 | 昆明鞘翼科技有限公司 | A kind of plate wing machine with upper and lower double-vane |
| CN111017205A (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 | Vertical take-off and landing conveyor |
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Application publication date: 20130501 |