CN101934860A - Helicopter using centrifugal rotor engine - Google Patents
Helicopter using centrifugal rotor engine Download PDFInfo
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- CN101934860A CN101934860A CN2009101485812A CN200910148581A CN101934860A CN 101934860 A CN101934860 A CN 101934860A CN 2009101485812 A CN2009101485812 A CN 2009101485812A CN 200910148581 A CN200910148581 A CN 200910148581A CN 101934860 A CN101934860 A CN 101934860A
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- helicopter
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Abstract
The invention discloses a helicopter design using a centrifugal rotor engine. The helicopter using the centrifugal rotor engine directly drives a main rotor wing of the helicopter or drives the main rotor wing of the helicopter after decelerating through a reducer, thereby avoiding the known problems of driving the main rotor wing of the helicopter by wing tip jetting, i.e. the phenomenon that a wing tip jet engine inhales tail gas generated by itself to shut down or cause power descent. The centrifugal rotor engine drives a spindle to rotate and drives a back propulsion propeller to rotate after steering through a steering gear, thereby enhancing the propulsion efficiency of the helicopter, also realizing the functions of a rotorcraft and ensuring that the engine of the helicopter has the advantages of stable work and simple structure.
Description
Technical field
The present invention relates to the jet-driven helicopter of wing tip, especially be different from known use ramjet propulsion or pulse duct as the jet-driven helicopter of wing tip.
Background technology
At present, the jet-driven helicopter of known blade tip uses ramjet propulsion or pulse duct as the blade tip jet drive; But the admission port of driving engine and burning gases air nozzle are in the circumference of a horizontal surface; Driving engine sucks the tail gas of self easily and causes and shut down or power decline.
Summary of the invention
In order to solve existing use ramjet propulsion or pulse duct cause shutdown or power decline because of the waste gas of suction oneself generation easily as the jet-driven helicopter engine of wing tip problem.The invention provides and use me to propose the helicopter of the centrifugal rotor engine (200910148645.9) of patent application as driving engine, the present invention solves the scheme that its technical matters adopts: use centrifugal rotor engine to drive main rotor, perhaps use centrifugal rotor engine to drive main rotor again, to produce raising force through after the speed change; Deflector and change-speed box can be with the takeoff output of centrifugal rotor engine to cardan shafts, and drive the propelling screws rotation, for helicopter provides thrust.
The beneficial effect that the present invention carries is: solved the jet-driven helicopter engine of existing wing tip because the easy problem that sucks the tail gas of self and cause shutdown or power to descend; the dynamic structure of helicopter is simplified; improved the work efficiency and the stability of helicopter, driven propelling screws and improved propulsion coefficient.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is the centrifugal rotor engine scheme drawing among the present invention.
Fig. 2 is one of scheme drawing of the use centrifugal rotor engine among the present invention.
Fig. 3 be the use centrifugal rotor engine among the present invention scheme drawing two.
Fig. 4 is a jet engine scheme drawing under the centrifugal rotor among the present invention.
Fig. 5 is the scheme drawing of the downward jet engine of use centrifugal rotor among the present invention.
Fig. 6 is the scheme drawing of the use centrifugal rotor engine direct drive main rotor among the present invention.
The specific embodiment
In Fig. 1 to Fig. 6,1. centrifugal rotor engine, 2. main shaft, 3. speed change and deflector, 4. main rotor sleeve, 5. main rotor, 6. cardan shaft, 7. propelling screws, the 8. downward jet engine of centrifugal rotor, the 9. downward jet engine spout of centrifugal rotor.
In Fig. 1, centrifugal rotor engine (1) is fixedly linked with main shaft (2).
In Fig. 2, main shaft (2) drives main rotor (5) rotation, and main rotor (5) produces lift; Speed change and deflector (3) can be as required with the takeoff output of main shaft (2) to cardan shaft (6); Cardan shaft (6) drives propelling screws (7) rotation and produces thrust.
In Fig. 3, centrifugal rotor engine (1) drives main shaft (2) rotation, and the power of main shaft (2) is input to speed change and deflector (3), outputs to main rotor sleeve (4) through after the speed change; Main rotor sleeve (4) is captiveed joint with main rotor (5), makes main rotor (5) rotation, produces lift.Speed change and deflector (3) can be as required with the takeoff output of main shaft (2) to cardan shaft (6); Cardan shaft (6) drives propelling screws (7) rotation and produces thrust; After helicopter reached certain speed, centrifugal rotor engine (1) did not drive main rotor (5) rotation, and only drive propelling screws (7) rotation and produce thrust, main rotor (5) spinning down with the wind, this moment, helicopter was in the cyclogyro state of flight.
In Fig. 4, the downward jet engine of centrifugal rotor (8) is center of circle rotation with main shaft (2), and the jet gas of the downward jet engine spout of centrifugal rotor (9) produces and goes up thrust and forward thrust.
In Fig. 5, when taking off, the downward jet engine of centrifugal rotor (8) rotation, the jet gas of the downward jet engine spout of centrifugal rotor (9) produces and goes up thrust and forward thrust, makes helicopter rising, the downward jet engine of centrifugal rotor (8) rotation; Main shaft (2) is not input to power speed change and deflector (3).When flying forward, main shaft (2) also is input to speed change and deflector (3) with power, drives propelling screws (7) rotation and produces thrust.
In Fig. 6, centrifugal rotor engine (1) drives main shaft (2) rotation, and main shaft (2) direct drive and main rotor (5) rotation produce lift.Speed change and deflector (3) can be as required with the takeoff output of main shaft (2) to cardan shaft (6); Cardan shaft (6) drives propelling screws (7) rotation and produces thrust.
Claims (8)
1. one kind is used the wing tip of centrifugal rotor engine to spray helicopter, comprises centrifugal rotor engine (1), main shaft (2), speed change and deflector (3), main rotor sleeve (4), main rotor (5), cardan shaft (6), propelling screws (7), the downward jet engine of centrifugal rotor (8), the downward jet engine spout of centrifugal rotor (9);
It is characterized in that:
Centrifugal rotor engine (1) is captiveed joint with main shaft (2);
Main shaft (2) direct drive main rotor (5) rotation;
Main shaft (2) is adjusted rotating speed rear drive main rotor sleeve (4) rotation through speed change and deflector (3);
Main rotor sleeve (4) drives main rotor (5) rotation;
Main shaft (2) is adjusted rotating speed rear drive cardan shaft (6) rotation through speed change and deflector (3);
Cardan shaft (6) drives propelling screws (7) rotation;
The downward jet engine spout of the centrifugal rotor of the downward jet engine of centrifugal rotor (8) (9) is downward and rear side is jet, thrust and forward thrust in the generation.
2. wing tip according to claim 1 sprays helicopter, it is characterized in that: centrifugal rotor engine (1) is captiveed joint with main shaft (2).
3. wing tip according to claim 1 sprays helicopter, it is characterized in that: make main shaft (2) drive main rotor (5) rotation.
4. wing tip according to claim 1 sprays helicopter, it is characterized in that: after speed change and deflector (3) are adjusted the input speed of main shaft (2) as required, drive main rotor sleeve (4) rotation; Or stop to drive main rotor sleeve (4) rotation.
5. wing tip according to claim 1 sprays helicopter, it is characterized in that: make main rotor sleeve (4) drive main rotor (5) rotation.
6. wing tip according to claim 1 sprays helicopter, it is characterized in that: make speed change and deflector (3) as required with main shaft (2) takeoff output to cardan shaft (6), drive cardan shaft (6) rotation; Or stop takeoff output, cardan shaft (6) is stopped the rotation.
7. wing tip according to claim 1 sprays helicopter, it is characterized in that: make cardan shaft (6) drive propelling screws (7) rotation.
8. wing tip according to claim 1 sprays helicopter, it is characterized in that: make the downward jet engine spout of centrifugal rotor (9) institute jet gas produce thrust upwards; And the driving downward jet engine of centrifugal rotor (8) rotation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101485812A CN101934860A (en) | 2009-06-30 | 2009-06-30 | Helicopter using centrifugal rotor engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101485812A CN101934860A (en) | 2009-06-30 | 2009-06-30 | Helicopter using centrifugal rotor engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101934860A true CN101934860A (en) | 2011-01-05 |
Family
ID=43388485
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009101485812A Pending CN101934860A (en) | 2009-06-30 | 2009-06-30 | Helicopter using centrifugal rotor engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101934860A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112009695A (en) * | 2019-05-30 | 2020-12-01 | 李秋辐 | Circumferential jet engine device |
| CN113120229A (en) * | 2021-05-20 | 2021-07-16 | 李可 | Centrifugal wind wheel air inlet wing tip jet rotor |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5560196A (en) * | 1993-12-15 | 1996-10-01 | Schlote; Andrew | Rotary heat engine |
| WO2000002776A1 (en) * | 1998-07-08 | 2000-01-20 | Victor Michailovich Malishkin | Combined blade for the rotor of an aircraft and aircraft flying method |
| DE102006028885A1 (en) * | 2005-06-21 | 2007-03-22 | Singer, Csaba | Hybrid aircraft e.g. helicopter, has two wings arranged laterally at casing and engaging together with casing by rotating around axis using rotating mechanism, rotation symmetric and mirror symmetrical configuration |
| CN1962361A (en) * | 2006-04-07 | 2007-05-16 | 赵钦 | Helicopter with rotary wing directly propelled by impetus |
| CN2910313Y (en) * | 2005-11-02 | 2007-06-13 | 纳赫曼·奇梅特 | Rotary-wing vehicle system |
| CN101012009A (en) * | 2007-02-08 | 2007-08-08 | 朴娜慧 | Jetocopter |
-
2009
- 2009-06-30 CN CN2009101485812A patent/CN101934860A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5560196A (en) * | 1993-12-15 | 1996-10-01 | Schlote; Andrew | Rotary heat engine |
| WO2000002776A1 (en) * | 1998-07-08 | 2000-01-20 | Victor Michailovich Malishkin | Combined blade for the rotor of an aircraft and aircraft flying method |
| DE102006028885A1 (en) * | 2005-06-21 | 2007-03-22 | Singer, Csaba | Hybrid aircraft e.g. helicopter, has two wings arranged laterally at casing and engaging together with casing by rotating around axis using rotating mechanism, rotation symmetric and mirror symmetrical configuration |
| CN2910313Y (en) * | 2005-11-02 | 2007-06-13 | 纳赫曼·奇梅特 | Rotary-wing vehicle system |
| CN1962361A (en) * | 2006-04-07 | 2007-05-16 | 赵钦 | Helicopter with rotary wing directly propelled by impetus |
| CN101012009A (en) * | 2007-02-08 | 2007-08-08 | 朴娜慧 | Jetocopter |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112009695A (en) * | 2019-05-30 | 2020-12-01 | 李秋辐 | Circumferential jet engine device |
| CN113120229A (en) * | 2021-05-20 | 2021-07-16 | 李可 | Centrifugal wind wheel air inlet wing tip jet rotor |
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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 |
Application publication date: 20110105 |