CN2382652Y - Composite rotary wing of aeroplane - Google Patents
Composite rotary wing of aeroplane Download PDFInfo
- Publication number
- CN2382652Y CN2382652Y CN 99221738 CN99221738U CN2382652Y CN 2382652 Y CN2382652 Y CN 2382652Y CN 99221738 CN99221738 CN 99221738 CN 99221738 U CN99221738 U CN 99221738U CN 2382652 Y CN2382652 Y CN 2382652Y
- Authority
- CN
- China
- Prior art keywords
- base plate
- blade
- rotor
- main shaft
- rotary wing
- 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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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model relates to a rotary wing of an aircraft, blades are distributed uniformly around a main shaft, a circular cover which is connected with blade tips covers the periphery of the blades, a bottom plate which is arranged in the circular cover is positioned under the blades, the upper bottom surface of the bottom plate is distributed with more than two baffle plates, both sides of the baffle plates are curved surfaces, and an annular space is left between the circular cover and the edge of the bottom plate. The rise thrust obtained by the rotary wing is distributed uniformly along the circumferential direction of the main shaft, and thus, when the rotary wing rotates, the utility model has smooth rise and small vibration.
Description
The utility model relates to the rotor of aircraft
The rotor of existing aircraft, its main shaft links to each other with rotor head, is connected with on the rotor head around the uniform blade of main shaft (more than two).During the rotor rotation, the upper and lower surface of blade forms pressure reduction, thereby obtains lift upwards, and aircraft is risen.The rotor of said structure requires to have kinetic balance and static balance preferably, otherwise has bigger vibration during rotation, thus its making is had relatively high expectations, but, when this rotor rotates, still have certain vibration owing to exist Mismachining tolerance.
The purpose of this utility model is to provide a kind of lift equilibrium, the less compound rotor of aircraft of vibration.
For achieving the above object, the utility model adopts following scheme: each blade 3 is uniform around main shaft 9, shroud 1 is connected with the blade tip of each blade 3, make the border seal of each blade 3, shroud 1 is an annular, is positioned at shroud 1 and is provided with base plate 7 below blade 3, is furnished with two with overhead gage 2 on base plate 7 upper bottom surfaces, the two side faces of baffle plate 2 is a curved surface, leaves annular space 8 between the edge of shroud 1 and base plate 7.
By such scheme as seen, during the rotation of this rotor, the air of blade top is sucked in the shroud by blade, and the blade upper and lower surface produces pressure reduction, and promptly air less than the pressure of air to the blade lower surface, makes rotor obtain lift to the pressure of blade upper surface; Simultaneously, the baffle plate that the air that is inhaled into rotates on base plate is compressed to the edge of base plate, and extrudes through annular space, thereby makes rotor obtain thrust upwards.Because air-flow is from the annular space pass-out, thus the thrust that makes progress that this rotor obtains circumferentially uniform along main shaft, thereby, rise steady during the rotor rotation and vibrate little.
Description of drawings:
The constructional drawing of Fig. 1, the utility model one embodiment;
The birds-eye view of Fig. 2, Fig. 1;
The A-A cutaway view of Fig. 3, Fig. 1.
Referring to Fig. 1, Fig. 2, each blade 3 is connected on the rotor head 4 and is uniform around rotor head 4, and the axis of rotor head 4 is coaxial with main shaft 9, and blade 3, rotor head 4 and shroud 1 are an integral body.Main shaft 9 links to each other with base plate 7, and base plate 7 is provided with a boss 6 and is connected with rotor head 4 by bolt 5 by this boss 6, and main shaft 9, base plate 7, baffle plate 2 and boss 6 are an integral body.The axis of shroud 1 and 7 annular spaces 8 of base plate is coaxial with main shaft 9.
Referring to Fig. 3, base plate 7 is discoid, and boss 6 is positioned at the center of base plate 7, and each baffle plate 2 intersects and the upper bottom surface of base plate 7 is evenly separated with the boss 6 at base plate 7 centers.The span of 7 annular space 8 width of shroud 1 and base plate is the 1/100-1/50 of shroud 1 external diameter.
Claims (3)
1, the compound rotor of aircraft, each blade (3) is uniform around main shaft (9), it is characterized in that: shroud (1) is connected with the blade tip of each blade (3), be positioned at shroud (1) in blade (3) below and be provided with base plate (7), be furnished with the baffle plate (2) more than two on base plate (7) upper bottom surface, the two side faces of baffle plate (2) is a curved surface, leaves annular space (8) between the edge of shroud (1) and base plate (7).
2, the compound rotor of aircraft according to claim 1 is characterized in that: main shaft (9) links to each other with base plate (7), and each blade (3) is connected on the rotor head (4), and base plate (7) connects with rotor head (4).
3, the compound rotor of aircraft according to claim 1 is characterized in that: each baffle plate (2) intersects at the center of base plate (7) and the upper bottom surface of base plate (7) is evenly separated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 99221738 CN2382652Y (en) | 1999-07-24 | 1999-07-24 | Composite rotary wing of aeroplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 99221738 CN2382652Y (en) | 1999-07-24 | 1999-07-24 | Composite rotary wing of aeroplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2382652Y true CN2382652Y (en) | 2000-06-14 |
Family
ID=34012251
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 99221738 Expired - Fee Related CN2382652Y (en) | 1999-07-24 | 1999-07-24 | Composite rotary wing of aeroplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2382652Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101549754B (en) * | 2009-04-29 | 2012-05-23 | 北京航空航天大学 | Rotary fixed wing composite aircraft and design method thereof |
| CN107554754A (en) * | 2017-09-06 | 2018-01-09 | 邓安迪 | A kind of aircraft lift（Or thrust）Device |
| WO2019095841A1 (en) * | 2017-11-16 | 2019-05-23 | 唐良伦 | Aircraft impeller and aircraft |
-
1999
- 1999-07-24 CN CN 99221738 patent/CN2382652Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101549754B (en) * | 2009-04-29 | 2012-05-23 | 北京航空航天大学 | Rotary fixed wing composite aircraft and design method thereof |
| CN107554754A (en) * | 2017-09-06 | 2018-01-09 | 邓安迪 | A kind of aircraft lift（Or thrust）Device |
| WO2019095841A1 (en) * | 2017-11-16 | 2019-05-23 | 唐良伦 | Aircraft impeller and aircraft |
| US11401029B2 (en) | 2017-11-16 | 2022-08-02 | Lianglun TANG | Aircraft impeller and aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |