CN1556006A - Mechanical rotating two wing deflected ascent small airplane - Google Patents
Mechanical rotating two wing deflected ascent small airplane Download PDFInfo
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- CN1556006A CN1556006A CNA2004100030198A CN200410003019A CN1556006A CN 1556006 A CN1556006 A CN 1556006A CN A2004100030198 A CNA2004100030198 A CN A2004100030198A CN 200410003019 A CN200410003019 A CN 200410003019A CN 1556006 A CN1556006 A CN 1556006A
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Abstract
An obliquely lifting small airplane featues that the rotay-wings of helicopter and the wings of propeller-type airplane are combined, and the their angles can be regulated for oblique lifting or flying forward. Its advantages are good use of air lifting, saving fuel oil and simple structure.
Description
Affiliated technical field
The present invention relates to a kind of aircraft, especially the rotor of helighro and propeller aeroplane lifting force of wings principle are combined, produce angled lift and flight pulling force, utilize the air in advancing more, reach fuel saving, purpose quick, simple in structure.
Background technology
At present, known autogyro is that the rotation of leaning on driving engine to drive rotor produces to raising force, by changing the angle generation pulling force forward of rotor, aircraft is flown aloft.It is considered herein that: known helicopter only depends on rotor to produce power, needs large-area wing oar and high-performance driving engine, and power and fuel that it expends are excessive.
Summary of the invention
Big and consumption fuel is big for the wing oar face that overcomes known autogyro waits not enoughly, the invention provides a kind of later-model similar autogyro, not only fuel saving but also power plant simple, move brisk.
The technical solution adopted for the present invention to solve the technical problems is: under the situation of the rotor that keeps known autogyro, setting up the wing that can change front rake above the rear portion of aircraft or below the rotor with rotor, this wing bench section should be to go up circle flat (one hundred exerts sharp theorem) down, as the propeller aeroplane wing, can produce lift.The place ahead is provided with the shifting chute that can supply rotor to rotate on the head of fuselage, also be wing rail mark groove, require to adjust at any time the angle of rotor according to flight, wing also rotates with rotor simultaneously, big, the generation lift of the angle of rotor during rising, wing also produces lift and holder power by air, can produce lift as screw propeller machine wing, the lift of two additions exceeds known helicopter lift, when the angle of rotor is changeed hour, the lift of its generation has become pulling force fully, and the power of wing has also become holder power and lift fully.The deficiency of the pulling force that will bear when advancing with regard to the rotor that has changed known helicopter like this and two power of lift.Therefore, this rotor wing oar of the present invention should be littler than the area of existing helicopter.Be made as ordinate if aircraft moved ahead, rise to vertical line, two lines are crossed as 90 °, pulling force maximum when the angle of rotor is 0 °, and lift is 0, the holder power of wing, lift maximum.Therefore the best climbing angle degree should be 45 °, because this angle rotor and wing have been shared 50% of the power that moves ahead and raising force separately.Exactly when the front rake of rotor and wing is 45 °: the lift=pulling force that moves ahead, it is considered herein that and lean forward when being 45 °, be the best climbing angle degree.45 ° with top rade as far as possible need not, so characteristic of the present invention is an oblique ascension.Also be the oblique ascension aircraft.Aircraft the time should take trend opposite when rising to operate in landing.
The invention has the beneficial effects as follows: the function of existing helicopter has the function of propeller aeroplane, the advantage of two machines that get both again.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is a full view of the present invention
Fig. 2 is the lateral plan of the present invention when rising
Fig. 3 is the lateral plan of the present invention when moving ahead
Fig. 4 is a front elevation of the present invention
Fig. 5 is a top view of the present invention
Fig. 6 is coexist the design side figure that derives on the axle of rotor of the present invention and wing
Fig. 7 is the design (two-seater) of deriving of the present invention
Fig. 8 is the design of deriving of the present invention, and two rotors are in the wing both sides
Fig. 9 is a wing forward leaning angle scheme drawing of the present invention
Among the figure: 1, rotor, 2, wing, 3, the rotational angle groove of rotor, 4, the tail rudder that hangs down, 5, the engine installation place, 6, wing turning cylinder (hydraulic pressure)
The specific embodiment
The best angle that leans forward of rotor of the present invention and wing is 45 °, is meant when rising.More than 45 ° generally speaking need not, if but the point that lands during because of oblique ascension around the building influence is arranged, need go straight up to, should have high speed rotating equipment to rise at a high speed to drive rotor, only need a moment.The activity of wing is by turning cylinder, and the axle before the wing should be the twin shaft that bearing is arranged, and is fixed on machine item top, and the rear axle binding is fixed on the following fore-set, and fore-set should be a hydraulic efficiency gear equipment, is used for controlling the angle of wing.As Fig. 2, shown in Figure 3.The rotation of wing also can be taked other scheme, as mechanisms such as planar linkage, cam, spiral, worm screws, therefrom selects preferred plan.Fig. 8 is the comparatively ideal design of deriving of the present invention.Only need to rotate wing and can adjust forward leaning angle.
Materials of the present invention remove skeleton and power plant, all should adopt light material, to reduce the own wt of aircraft.
Claims (5)
1, a kind of aviette, the raising force and the pulling force that moves ahead are born jointly by its rotor and wing, and aircraft obtains the power that needs according to rising or needs when moving ahead are adjusted the common angle of both wings.
2, aircraft according to claim 1, rotor and wing produce lift and pulling force jointly, and wing is a principal character of the present invention.
3, aircraft according to claim 1 is a common angle of adjusting both wings as required, and the angle function amount of wing and rotor should be a distinctive marks of the present invention.
4, aircraft according to claim 1, adjusting as required that the common angle of both wings, wing and rotor can rotate is main characteristic of the present invention.
5, the angle of aircraft according to claim 1, wing can be adjusted, and the center of gravity of aircraft should keep the both wings rotation not influence on the stable position of fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2004100030198A CN1556006A (en) | 2004-01-11 | 2004-01-11 | Mechanical rotating two wing deflected ascent small airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2004100030198A CN1556006A (en) | 2004-01-11 | 2004-01-11 | Mechanical rotating two wing deflected ascent small airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1556006A true CN1556006A (en) | 2004-12-22 |
Family
ID=34350755
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2004100030198A Pending CN1556006A (en) | 2004-01-11 | 2004-01-11 | Mechanical rotating two wing deflected ascent small airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1556006A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101870355A (en) * | 2010-06-03 | 2010-10-27 | 杨茂亮 | Coaxial double-rotary wing and tilt wing aircraft |
| CN103129737A (en) * | 2013-03-27 | 2013-06-05 | 南京傲翼伟滕自动化科技有限公司 | Inclined fixed wing unmanned plane |
| US8888046B2 (en) | 2008-09-22 | 2014-11-18 | Airbus Operations Gmbh | Fuel management system |
-
2004
- 2004-01-11 CN CNA2004100030198A patent/CN1556006A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8888046B2 (en) | 2008-09-22 | 2014-11-18 | Airbus Operations Gmbh | Fuel management system |
| CN101870355A (en) * | 2010-06-03 | 2010-10-27 | 杨茂亮 | Coaxial double-rotary wing and tilt wing aircraft |
| CN103129737A (en) * | 2013-03-27 | 2013-06-05 | 南京傲翼伟滕自动化科技有限公司 | Inclined fixed wing unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |