CN1335248A - Helicopter with driving rotary wings - Google Patents
Helicopter with driving rotary wings Download PDFInfo
- Publication number
- CN1335248A CN1335248A CN 00112409 CN00112409A CN1335248A CN 1335248 A CN1335248 A CN 1335248A CN 00112409 CN00112409 CN 00112409 CN 00112409 A CN00112409 A CN 00112409A CN 1335248 A CN1335248 A CN 1335248A
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- Prior art keywords
- helicopter
- rotor
- driving
- engine
- thrust
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Abstract
The present invention relates to the field of aerial craft technology and solves the problem that the driving force of helicopter must pass through one serial of driving mechanisms before it reaches to the rotating wings resulting in complicated structure, low efficiency and more noise. The present invention is that inside or at ends of the rotary wings as well as in the fuselage, engines and driving mechanisms in the same specification are installed. The present invention can utilize the power of engines and makes helicopter comfortable and more safe.
Description
The invention belongs to the aviation aircraft technical field.
According to the knowledge of the applicant, modern autogyro kind is more, but all is by engine drive centre of gration one propeller hub that is installed on the helicopter, drives rotor by propeller hub and makes high speed revolution, add other adjusting Auxiliary Propulsion Unit, make autogyro obtain vertical lift and flight.The engine power of this autogyro is delivered to rotor by a series of drivings device, its driving device complex structure, the technical requirements height, not only cost height, and the engine power degree of utilization is lower, and the antagonistic force that huge rotor produces cannot be eliminated, and its noise and vibration is difficult to make the people to feel comfortably cool, and part is thousands of here, and the damage of any one part all can produce terrible consequences.
Purpose of the present invention is exactly the groundwork according to autogyro, needn't engine efficiency be made full use of by removing to drive rotor behind a series of drivings device again, has simplified driving system, and the traveling comfort of autogyro, safety are greatly improved.
The present invention is achieved in that a kind of active helicopter, it is characterized in that, in the centre of each rotor of helicopter or the thrust or the draft force apparatus of the same driving engine of specification and driving thereof be housed near terminal position, the direction of thrust or draft force apparatus is to be the same circumferencial direction in the center of circle with the center of gyration, the same driving engine and the thruster of driving thereof also are housed on the aircraft fuselage, and its effect is as the booster of regulating state of flight.
Its engine-driven thrust or draft force apparatus can be the propeller that is driven by put-put, also can be turbojets.
Because the centre or the proximal end of every rotor are equipped with the engine thrust device, when engine operation, each driving engine produces a moment, drive rotor wraparound commentaries on classics center rotation, because it is same circumferencial direction that the starting of every rotor drives thrust, many rotors just high speed revolution get up, and the shape of cross section of rotor is the same with modern autogyro, and initiatively the rotor rotor craft of going straight up to can carry out vertical lift and flight.Auxiliary the pushing away that is installed in the fuselage both sides helped device, can bring into play the regulating action of aspects such as acceleration, deceleration, direction adjustment.
Because the development of current technology, driving engine can be made lessly, can be directly installed on fully on the rotor, and the rotor inner space can be used as fuel tank again and uses.By several small-sized driving engine direct drive rotors separately, pass through driving system → propeller hub (centre of gration) → rotor only to replace by a driving engine, be feasible in technology.Its advantage is: reduced complicated driving device, cost-cutting greatly not only, also can increase safety greatly, because contingency has one to break down in several driving engines, aircraft can also fly, the probability that several driving engines break down simultaneously is very little, has so just improved the safety performance of flight greatly.Because driving engine is not directly installed on the fuselage, there are not problems such as its antagonistic force and vibration, noise again, improved the level of comfort of aircraft widely.
The present invention is further illustrated below in conjunction with an embodiment (the active helighro that four oar screw propellers promote).
Fig. 1 is the front view of principle of work structural representation of the present invention.
Fig. 2 is the birds-eye view of principle of work structural representation of the present invention.
The principle schematic that Fig. 3 drives for rotor of the present invention.
Among the figure: 1, rotor 2, screw propeller 3, fuselage 4, boosting screw propeller 5, fuel tank 6, driving engine 7, centre of gration
As can be seen from Figure 3, rotor 1 is housed on the centre of gration 7, and engine-driven screw propeller 2 is housed in the centre of rotor 1.Rotor 1 can be done freely to rotate around centre of gration 7, the cross-sectional plane of rotor 1 is common streamline contour, during driving engine 6 work, screw propeller 2 is made high speed revolution, make it produce a thrust, promptly produce a moment with respect to centre of gration 7, this moment makes rotor 1 make high speed revolution around centre of gration 7 anticlockwise directions, and driving engine on another rotor and screw propeller also are like this.When rotor 1 high speed revolution, make air-flow produce a lift that makes progress according to its streamline contour section of fluid mechanics law, drive aircraft and rise, this also is the flight theory of general autogyro.
Can find out from Fig. 1, Fig. 2,, install four rotors 1 on the top of helicopter fuselage 1, driving engine is equipped with in the centre of every rotor, the screw propeller 2 of driving, the close centre of every rotor 1, fuel tank 5 is arranged, and the main thrust of helicopter is produced by rotor 1.At the fuselage afterbody downside two cover boosting screw propellers 4 are housed, these boosting screw propellers can be regulated the various states of flight, as turning, acceleration, deceleration etc.
The active helicopter, engine power degree of utilization height, safety and comfort, flexible operation, cost are also lower.Real is a major reform of aerospacecraft.
Claims (2)
1, a kind of active helicopter, it is characterized in that, in the centre of each rotor of helicopter or the thrust or the draft force apparatus of the same driving engine of specification and driving thereof be housed near terminal position, the direction of thrust or draft force apparatus is to be the same circumferencial direction in the center of circle with the center of gyration, the same driving engine and the thruster of driving thereof also are housed on the aircraft fuselage, and its effect is as the booster of regulating state of flight.
2, active helicopter according to claim 1 is characterized in that engine-driven thrust or draft force apparatus can be the propeller that is driven by put-put, also can be turbojet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 00112409 CN1335248A (en) | 2000-07-20 | 2000-07-20 | Helicopter with driving rotary wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 00112409 CN1335248A (en) | 2000-07-20 | 2000-07-20 | Helicopter with driving rotary wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1335248A true CN1335248A (en) | 2002-02-13 |
Family
ID=4582269
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 00112409 Pending CN1335248A (en) | 2000-07-20 | 2000-07-20 | Helicopter with driving rotary wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1335248A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101878153A (en) * | 2007-07-24 | 2010-11-03 | 简克劳德·图恩 | Aerial device |
| CN103043211A (en) * | 2012-12-25 | 2013-04-17 | 华南农业大学 | Vertically lifting aircraft |
| CN108163193A (en) * | 2018-02-11 | 2018-06-15 | 桂艳春 | A kind of active main rotor vertically taking off and landing flyer |
| CN108238247A (en) * | 2018-02-11 | 2018-07-03 | 桂艳春 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
| EP3240726A4 (en) * | 2015-01-03 | 2018-12-12 | Joseph B. Seale | Rotary wing vtol with fixed wing forward flight mode |
| CN109018321A (en) * | 2018-07-02 | 2018-12-18 | 寇冠 | Driven rotor craft |
| CN114476043A (en) * | 2021-12-31 | 2022-05-13 | 中国航天空气动力技术研究院 | Electronic distributing type rotor unmanned transport plane |
-
2000
- 2000-07-20 CN CN 00112409 patent/CN1335248A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101878153A (en) * | 2007-07-24 | 2010-11-03 | 简克劳德·图恩 | Aerial device |
| CN101878153B (en) * | 2007-07-24 | 2014-06-25 | 简克劳德·图恩 | Aerial device |
| CN103043211A (en) * | 2012-12-25 | 2013-04-17 | 华南农业大学 | Vertically lifting aircraft |
| EP3240726A4 (en) * | 2015-01-03 | 2018-12-12 | Joseph B. Seale | Rotary wing vtol with fixed wing forward flight mode |
| US10421538B2 (en) | 2015-01-03 | 2019-09-24 | Joseph B. Seale | Rotary wing VTOL with fixed wing forward flight mode |
| CN108163193A (en) * | 2018-02-11 | 2018-06-15 | 桂艳春 | A kind of active main rotor vertically taking off and landing flyer |
| CN108238247A (en) * | 2018-02-11 | 2018-07-03 | 桂艳春 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
| WO2019154067A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Active main rotor blade vertical take-off and landing aircraft |
| WO2019154064A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Gasoline-electric hybrid power vertical take-off and landing aircraft having driving rotors |
| CN108163193B (en) * | 2018-02-11 | 2019-09-20 | 桂艳春 | A kind of active main rotor vertically taking off and landing flyer |
| CN109018321A (en) * | 2018-07-02 | 2018-12-18 | 寇冠 | Driven rotor craft |
| CN114476043A (en) * | 2021-12-31 | 2022-05-13 | 中国航天空气动力技术研究院 | Electronic distributing type rotor unmanned transport plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |