CN2767322Y - Circular wing aerobat - Google Patents
Circular wing aerobat Download PDFInfo
- Publication number
- CN2767322Y CN2767322Y CN 200420054077 CN200420054077U CN2767322Y CN 2767322 Y CN2767322 Y CN 2767322Y CN 200420054077 CN200420054077 CN 200420054077 CN 200420054077 U CN200420054077 U CN 200420054077U CN 2767322 Y CN2767322 Y CN 2767322Y
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- CN
- China
- Prior art keywords
- duct
- utility
- model
- power device
- sheets
- 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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Abstract
The utility model relates to a circular wing aircraft. The utility model is formed by that a power device is arranged in a duct; an embarkation cabin is arranged on the power device; a drive shaft which is connected with a screw propeller is assembled at the top part of the power device, and the outer side wall of the power device is connected with a support frame so as to be fixed on the inner wall of the duct; the lower end of the duct is provided with diversion sheets, the diversion sheets are arranged in parallel in the crisscross and equidistant manner, the lower end of the diversion sheets is provided with wind direction sheets and a landing shelf is fixed at the bottom end of the duct. The utility model has the main application in aerial photography, advertisement propaganda, communication relay, escaped criminal pursuit, traffic guidance, counter-terrorism warfare, military intelligence reconnaissance, etc.
Description
Affiliated technical field
The utility model relates to a kind of single airflight vehicle, especially can vertical takeoff and landing, and the vehicle that can aloft fly.
Background technology
At present, known early stage individual lift device subject matter is under power, and Power train is undesirable, and sensor and automatic control technology are immature at that time.Modern ordinary fixed wing individual lift device takes off to land and needs special-purpose airfield runway, needs higher speed and could produce enough lift, causes the generation when taking off landing of about 50% left and right sides aircraft accident, and park occupied ground on ground very big.Modern common rotor individual lift device great majority adopt single rotor magnetic tape trailer paddle structure of helicopter.The rotor of high speed revolution is fatal threats to the personnel of disembarking.The blade of high speed revolution also is easy to run into object and produces aircraft accident; Air resistance and induced drag cause flying speed lower more greatly.
Summary of the invention
The technical problems to be solved in the utility model is: overcome that weak point provides a kind of pontoon type circuit umbrella individual lift device that all can be used as the vehicle in land, sea and air in the above-mentioned technology.
The technical scheme that its technical matters that solves the utility model adopts is:
In the duct engine installation is installed, be equipped with on it and carry the storehouse, the engine installation top is equipped with the transmission shaft that links to each other with screw propeller, be fixedly connected on the duct inwall with support on the engine installation lateral wall, the duct lower end part is equipped with the flow deflector of crisscross equidistant arrangement in parallel, its lower end part is equipped with the wind direction sheet, and alighting gear is packed in the duct bottom.
The beneficial effects of the utility model are:
1, anywhere vertical takeoff and landing, hover, noise is very low during orbit, and is disguised very good;
2, it has fast, the mobility strong of speed, can do various aerobatics;
3, flight efficiency height, and fuel saving, so easy maintenance is economical and practical;
4, comformability is strong; Adapt to the city, country, factory, seashore, naval vessels, grassland, high mountain, the vertical takeoff and landing flight that express highway etc. are local;
5, wide application: can take photo in the sky on civilian, advertising, communication repeating, the oil pipeline supervision, the monitoring of fire flood situation pursues and captures an escaped prisoner guiding of traffic etc.; The advantage that has other vehicle to hardly match equally militarily, fight-terrorism warfare, military situation is scouted, antisubmarine clearance, the strike of all types of target, attacks armed helicopter and low-to-medium altitude cruise missile etc.The utility model is a kind of rational in infrastructure, design ingenious, function admirable, convenient and practical individual lift device.
Description of drawings:
Fig. 1 is a structural representation of the present utility model;
Fig. 2 is the section-drawing of A-A among Fig. 1;
Fig. 3 is the birds-eye view of Fig. 1;
Fig. 4 is a schematic perspective view of the present utility model.
The specific embodiment
Below in conjunction with accompanying drawing and example the utility model is described in further details.
By Fig. 1-Fig. 3 as can be known the utility model be: in the duct 1 engine installation 5 is installed, be equipped with on it and carry storehouse 2, engine installation 5 tops are equipped with the transmission shaft 9 that links to each other with screw propeller 3, be fixedly connected on duct 1 inwall with support 4 on engine installation 5 lateral walls, duct 1 lower end part is equipped with the flow deflector 6 of crisscross equidistant arrangement in parallel, its lower end part is equipped with wind direction sheet 7, and alighting gear 8 is packed in duct 1 bottom.
1 inside, letter described in the utility model road is equipped with aircraft engine installation 5, the lift-launch storehouse 2 of installing on it, carry storehouse 2 inner main carrying aircraft control convenience and fuel goods and materials, screw propeller 3 is connected with transmission shaft 9, for the flight of aircraft provides power, support 4 by with being connected of engine installation 5 and duct 1, guaranteed the stability of aircraft flight, flow deflector 6 can actv. guarantees the stable emissions of slip-stream, the wind direction sheet 7 of its underpart connection is by the flight attitude of swing controlling aircraft, alighting gear 8 is positioned at duct 1 bottom, provides a supporting role when the aircraft grounding and landing.
Claims (1)
1, a kind of ring rotor aircraft, comprise engine installation (5) is installed in the duct (1), it is characterized in that: engine installation (5) is installed in the duct (1), be equipped with on it and carry storehouse (2), engine installation (5) top is equipped with the transmission shaft (9) that links to each other with screw propeller (3), be fixedly connected on duct (1) inwall with support (4) on engine installation (5) lateral wall, duct (1) lower end part is equipped with the flow deflector (6) of crisscross equidistant arrangement in parallel, its lower end part is equipped with wind direction sheet (7), and alighting gear (8) is packed in duct (1) bottom.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420054077 CN2767322Y (en) | 2004-12-28 | 2004-12-28 | Circular wing aerobat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420054077 CN2767322Y (en) | 2004-12-28 | 2004-12-28 | Circular wing aerobat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2767322Y true CN2767322Y (en) | 2006-03-29 |
Family
ID=36681182
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200420054077 Expired - Fee Related CN2767322Y (en) | 2004-12-28 | 2004-12-28 | Circular wing aerobat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2767322Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102285449A (en) * | 2011-06-07 | 2011-12-21 | 北京邮电大学 | Coaxial double-rotor wing ducted aircraft |
| CN104859840A (en) * | 2015-06-01 | 2015-08-26 | 何春旺 | Ducted power device and aircraft |
| CN106927023A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of agricultural plant protection controls culvert type unmanned plane with rudder face |
-
2004
- 2004-12-28 CN CN 200420054077 patent/CN2767322Y/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102285449A (en) * | 2011-06-07 | 2011-12-21 | 北京邮电大学 | Coaxial double-rotor wing ducted aircraft |
| CN104859840A (en) * | 2015-06-01 | 2015-08-26 | 何春旺 | Ducted power device and aircraft |
| CN106927023A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of agricultural plant protection controls culvert type unmanned plane with rudder face |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20060329 Termination date: 20101228 |