CN203864995U - Double-loop rotor wing used for helicopter - Google Patents
Double-loop rotor wing used for helicopter Download PDFInfo
- Publication number
- CN203864995U CN203864995U CN201420290777.1U CN201420290777U CN203864995U CN 203864995 U CN203864995 U CN 203864995U CN 201420290777 U CN201420290777 U CN 201420290777U CN 203864995 U CN203864995 U CN 203864995U
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- CN
- China
- Prior art keywords
- rotor
- rotor wing
- outer shroud
- loop
- annulus
- Prior art date
- Legal status (The legal status 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 status listed.)
- Expired - Fee Related
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- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The utility model relates to a double-loop rotor wing used for a helicopter. The double-ring rotor wing comprises an internal loop rotor wing and an external loop rotor wing. The inner side of a circular loop of the internal loop rotor wing sleeves a magnetic bearing, and inclined blades are arranged on the outer side of the circular loop of the internal loop rotor wing at intervals. The inner side of a circular loop of the external loop rotor wing sleeves the magnetic bearing, and blades opposite to the inclined blades of the internal loop rotor wing in direction are arranged on the outer side of the circular loop of the external loop rotor wing at intervals. The magnetic bearing is fixed on bases. The internal loop rotor wing is capable of rotating horizontally. The external loop rotor wing is capable of inclining front and back and rotating back and forth. The double-loop rotor wing has the advantages that by means of adopting the high-efficiency double-loop rotor wing, and on the premises that the diameter of the helicopter is smaller than 2 meters and the total weight of the helicopter is controlled within 250 kilos, the helicopter can be driven by batteries directly, non-stop flight can last for 1 hour according to existing battery technology, and the double-loop rotor wing can be widely used.
Description
Technical field
The utility model relates to a kind of for the dicyclo rotor on autogyro.
Background technology
At present, autogyro all adopts common rotor, and its efficiency only has 70%.Because power stage requirement is high, cannot use battery as the propulsion source of manned autogyro.And maneuvering system is complicated, moves various; Speed is restricted, and noise is strong.
Summary of the invention
The purpose of this utility model; to provide a kind of for the dicyclo rotor on autogyro; it can realize the driven by power of autogyro and noiselessization, microminiaturization; with magnetic suspension propelling unit or electrical motor, realize flight; adopt battery as energy source; reduce exhaust emission and without flight noise, protection of the environment, is particularly suitable for city and uses.
The utility model is achieved in that described for the dicyclo rotor on autogyro, and it comprises interior ring rotor, outer shroud rotor; Magnetic suspension bearing is entangled in the annulus inner side of described interior ring rotor, and the annulus outside of interior ring rotor is interval with oblique vane; Magnetic suspension bearing is entangled in the annulus inner side of described outer shroud rotor, and the annulus outside of outer shroud rotor is interval with the blade with interior ring rotor blade opposite direction; Magnetic suspension bearing is fixed on pedestal; Interior ring rotor is horizontal surface rotation; Outer shroud rotor can tilt forward and back and come back rotation.
The diametrical position of outer shroud rotor described in the utility model is provided with a pivot shaft, and the supporting seat at the annulus edge of being located at outer shroud rotor is inserted at pivot shaft two ends, and the annulus edge of supporting seat and outer shroud rotor is rotationally connected, and drives outer shroud rotor to tilt forward and back; Midway location at pivot shaft is arranged with two fixed pedestal buttons, each connects the gear that entangles motor the below of two fixed pedestal buttons, the outside of two gears is respectively provided with an arc-shaped gear road, two gears mesh with two arc-shaped gear roads respectively, the rotation of motor forward and reverse direction, drive two gears to walk back and forth on its arc-shaped gear road, drive outer shroud rotor to carry out back rotation simultaneously.
The beneficial effects of the utility model are, owing to adopting efficient dicyclo rotor, and aircraft diameter is less than 2 meters, and flight total weight is controlled in 250 kilograms, can directly adopt battery-operatedly, according to existing battery technology, can reach non-stop flight 1 hour, are widely used.
Accompanying drawing explanation
Fig. 1 is schematic diagram of the present utility model.
Fig. 2 is pivot shaft described in the utility model and driven wheel schematic diagram thereof.
In figure: 1. interior ring rotor, 2. outer shroud rotor, 3. annulus, 4. magnetic suspension bearing, 5. oblique vane, 6. annulus, 7. magnetic suspension bearing, the 8. blade of opposite direction, 9. pivot shaft, 10. supporting seat, 11. fixed pedestal buttons, 12. motors, 13. gears, 14. arc-shaped gear roads.
The specific embodiment
Described in the utility model for the dicyclo rotor on autogyro, as shown in Figure 1, 2, it comprises interior ring rotor 1, outer shroud rotor 2; Magnetic suspension bearing 4 is entangled in annulus 3 inner sides of described interior ring rotor 1, and annulus 3 outsides of interior ring rotor 1 are interval with oblique vane 5; Magnetic suspension bearing 7 is entangled in annulus 6 inner sides of described outer shroud rotor 2, and annulus 6 outsides of outer shroud rotor 2 are interval with the blade 8 with interior ring rotor blade opposite direction; Magnetic suspension bearing is fixed on pedestal; Interior ring rotor 1 is horizontal surface rotation; Outer shroud rotor 2 can tilt forward and back and come back rotation.In magnetic suspension bearing 4 drives, ring rotor 1 rotates, and produces lift; Magnetic suspension bearing 7 drives outer shroud rotor 2 to rotate backward, and produces lift.
The diametrical position of outer shroud rotor 2 described in the utility model is provided with a pivot shaft 9, and the supporting seat 10 at annulus 6 edges of being located at outer shroud rotor 2 is inserted at pivot shaft 9 two ends, and supporting seat 10 is rotationally connected with annulus 6 edges of outer shroud rotor 2, drives outer shroud rotor 2 to tilt forward and back; Midway location at pivot shaft 9 is arranged with two fixed pedestal buttons 11, each connects the gear 13 that entangles motor 12 below of two fixed pedestal buttons 11, the outside of two gears 13 is respectively provided with an arc-shaped gear road 14, two gears 13 mesh with two arc-shaped gear roads 14 respectively, motor 12 forward and reverse direction rotations, drive two gears 13 to walk back and forth on its arc-shaped gear road 14, drive outer shroud rotor 2 to carry out back rotation simultaneously.
When autogyro hovers, the opposite sense rotation on horizontal surface simultaneously of inner and outer ring rotor, produces lift by rotor, and the torsional moment that the torsional moment that interior ring rotor motion produces is produced by the motion of outer shroud rotor is offset.Inner and outer ring rotor velocity of rotation equates to set according to torsional moment, and interior ring gyroplane rotate speed is calculated and got by lift.If aircraft gross weight is 200 kilograms, interior ring rotor lift is 100 kilograms, and rotating speed just can be decided according to rotor characteristic.Meanwhile, the torsional moment of outer shroud rotor is definite, and rotary speed is also determined.
When aircraft flies forward, outer shroud rotor turns forward around pivot shaft, produces pulling force forward, but the torsional moment causing due to inclination reduces, and need to improve corresponding rotating speed to reach inside and outside torsional moment balance.
When aircraft bends to right, pivot shaft is turned right and is rotated to an angle on horizontal surface, is produced the deflection force of change of flight direction, thereby aircraft is turned to by outer shroud rotor.Left-handed turning in like manner.
Autogyro cabin is located at rotor below.
Claims (2)
1. for the dicyclo rotor on autogyro, it is characterized in that: it comprises interior ring rotor, outer shroud rotor; Magnetic suspension bearing is entangled in the annulus inner side of described interior ring rotor, and the annulus outside of interior ring rotor is interval with oblique vane; Magnetic suspension bearing is entangled in the annulus inner side of described outer shroud rotor, and the annulus outside of outer shroud rotor is interval with the blade with interior ring rotor blade opposite direction; Magnetic suspension bearing is fixed on pedestal; Interior ring rotor is horizontal surface rotation; Outer shroud rotor can tilt forward and back and come back rotation.
2. according to claim 1 for the dicyclo rotor on autogyro, it is characterized in that: the diametrical position of described outer shroud rotor is provided with a pivot shaft, the supporting seat at the annulus edge of being located at outer shroud rotor is inserted at pivot shaft two ends, the annulus edge of supporting seat and outer shroud rotor is rotationally connected, and drives outer shroud rotor to tilt forward and back; Midway location at pivot shaft is arranged with two fixed pedestal buttons, each connects the gear that entangles motor the below of two fixed pedestal buttons, the outside of two gears is respectively provided with an arc-shaped gear road, two gears mesh with two arc-shaped gear roads respectively, the rotation of motor forward and reverse direction, drive two gears to walk back and forth on its arc-shaped gear road, drive outer shroud rotor to carry out back rotation simultaneously.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420290777.1U CN203864995U (en) | 2014-06-04 | 2014-06-04 | Double-loop rotor wing used for helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420290777.1U CN203864995U (en) | 2014-06-04 | 2014-06-04 | Double-loop rotor wing used for helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203864995U true CN203864995U (en) | 2014-10-08 |
Family
ID=51645975
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420290777.1U Expired - Fee Related CN203864995U (en) | 2014-06-04 | 2014-06-04 | Double-loop rotor wing used for helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203864995U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107539480A (en) * | 2016-06-24 | 2018-01-05 | 丁广帅 | A kind of New Ring-like Type rotor |
-
2014
- 2014-06-04 CN CN201420290777.1U patent/CN203864995U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107539480A (en) * | 2016-06-24 | 2018-01-05 | 丁广帅 | A kind of New Ring-like Type rotor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141008 |