CN1172054A - Aerobat - Google Patents
Aerobat Download PDFInfo
- Publication number
- CN1172054A CN1172054A CN 97110497 CN97110497A CN1172054A CN 1172054 A CN1172054 A CN 1172054A CN 97110497 CN97110497 CN 97110497 CN 97110497 A CN97110497 A CN 97110497A CN 1172054 A CN1172054 A CN 1172054A
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- CN
- China
- Prior art keywords
- storehouse
- horizontal power
- loading
- power
- cabin
- 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.)
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Abstract
The flying vehicle which can vertically take off and land and has no need of turning and can randomly fly forwards, backwards, leftwards and rightwards is composed of control cabin, horizontal power cabin, vertical power cabin, loading cabin, centripetal thrust ball bearing, epicycle gear train and direction control power machine. Said control cabin is fixedly connected with the horizontal power cabin, and the loading cabin, control cabin and horizontal power cabin can move round the vertical axis of the air vehicle.
Description
The present invention relates to a kind of aerospace flight vehicle.
At present, in the known aircraft, go straight up to function and aloft hover, the energy vertical takeoff and landing (VTOL), turn radius is little, but route speed is not high, and flying height is little, and the route speed of air injection aerial vehicle is big, but can not aloft hover, can not need not to turn arbitrarily forwards, backwards about flight, can not vertical takeoff and landing (VTOL).
The objective of the invention is: a kind of aircraft is provided, and it can not only vertical takeoff and landing (VTOL), can aloft hover, and route speed is big, and climb altitude is big, and just aloft need not to turn and can be arbitrarily to fly about forwards, backwards.
The object of the present invention is achieved like this: control storehouse and horizontal power storehouse connect firmly, the inner ring of horizontal power storehouse and radial thrust bearing connects firmly, the outer ring of loading storehouse and radial thrust bearing connects firmly, the tie-rod of planetary gear train and horizontal power storehouse connect firmly, one center gear and the loading storehouse of planetary gear train connect firmly, another center gear of planetary gear train connects with the power take-off shaft of direction control engine, and direction control engine and horizontal power storehouse connect firmly.Between control storehouse and the horizontal power storehouse air by-pass passage can be arranged, the cylindrical hollow passage in this air by-pass passage same level power bin and loading storehouse communicates.The hollow channel that vertical power bin is arranged in loading storehouse or horizontal power storehouse is fixed on loading storehouse or the horizontal power storehouse.The horizontal power storehouse has at least the pair of parallel symmetry to be fixed on to revolve paddle motor or jet engine in the storehouse, and vertical power bin has at least one to revolve paddle motor or jet engine.The barycenter in loading storehouse, vertical power bin, horizontal power storehouse, control storehouse is on vertical axis separately, four vertical axis coincides with the vertical axis of aircraft, the barycenter of whole aircraft is on the plane at the driving engine place in horizontal power storehouse, and on the vertical axis of aircraft, on the vertical axis of driver's seat aircraft in the control storehouse.All can rotate around the vertical axis of aircraft in loading storehouse and horizontal power storehouse and control storehouse.During use, make vertical power bin work earlier, driving engine in the vertical power bin makes pressurized air or the downward high speed jet of combustion gas, under the recoil effect, aircraft vertical uplift or hover in the air then, makes the work of horizontal power storehouse, driving engine in the horizontal power storehouse makes pressurized air or combustion gas high speed jet backward, and aircraft is flight forward just.When will be arbitrarily flying about forwards, backwards, close the driving engine in horizontal power storehouse, start direction control engine, the power of direction control engine is through planetary gear train, the loading storehouse is rotated around the vertical axis of aircraft, know according to angular momentum conservation law: when the loading storehouse when vertical axis rotates, horizontal power storehouse and control storehouse are also simultaneously around the vertical axis backward rotation, when the horizontal power storehouse turns to required angle with the control storehouse, closing direction control engine, start the driving engine in horizontal power storehouse, aircraft is flight in the desired direction just.Also can not close the driving engine in horizontal power storehouse, start direction control engine, aircraft is just turned to the left and right.
Use such scheme, aircraft can vertical takeoff and landing (VTOL), can aloft hover, and just aloft need not to turn can be arbitrarily to fly about forwards, backwards.The route speed height, flying height is big.
Below in conjunction with accompanying drawing, the present invention is further described for example:
Fig. 1 is this routine vertical section structure scheme drawing
Fig. 2 is the birds-eye view of this routine aircraft
Fig. 3 is the birds-eye view in horizontal power storehouse
Among the figure, 10, control the storehouse; 11, operator's saddle; 20, horizontal power storehouse; 21, right horizontal power storehouse driving engine; 22, left horizontal power storehouse driving engine; 30, loading storehouse; 40, vertical power bin; 50, air by-pass passage; 51, pillar; 60, horizontal power storehouse hollow channel; 70, radial thrust bearing; 81, planetary gear train center gear; 82, satellite gear; 83, planetary gear train center gear; 84, planetary gear train tie-rod; 90, direction control engine.
Among Fig. 1, operator's saddle 11 is arranged on the vertical axis of control storehouse 10 aircraft, control storehouse 10 connects firmly with pillar 51 with horizontal power storehouse 20, control storehouse 10 communicates with air by-pass passage 50 same level power bin hollow channels 60 between the horizontal power storehouse 20, driving engine 21,22 parallel symmetries are fixed on the horizontal power storehouse 20, vertical power bin 40 is arranged in horizontal power storehouse hollow channel 60, and be fixed on the horizontal power storehouse 20, loading storehouse 30 is positioned at the horizontal power storehouse 20 times, the inner ring of radial thrust bearing 70 and horizontal power storehouse 20 connect firmly, the outer ring of radial thrust bearing 70 and loading storehouse 30 connect firmly, loading storehouse 30 can relatively rotate around the vertical axis of aircraft with horizontal power storehouse and control storehouse 10, planetary gear train center gear 81 connects firmly with loading storehouse 30, another center gear 83 connects with the power take-off shaft of direction control engine 90, the tie-rod 84 of planetary gear train is fixed on the horizontal power storehouse 20, and direction control engine 90 is fixed on the horizontal power storehouse 20.
In order to reduce the flight resistance of aircraft, the profile in control storehouse 10 is a convex lens shape, and the profile in horizontal power storehouse 20 and loading storehouse 30 is approximate hollow billiard table.For aircraft flight steady, the barycenter of control storehouse 10, horizontal power storehouse 20, loading storehouse 30, vertical power bin 40 is on vertical axis separately, four vertical axis coincides with the vertical axis of aircraft, the barycenter of whole aircraft is on the plane at the driving engine place in horizontal power storehouse 20, and on the vertical axis of aircraft.
Claims (4)
1, a kind of aircraft, by the control storehouse, the horizontal power storehouse, vertical power bin, the loading storehouse, radial thrust bearing, planetary gear train, direction control engine is formed, it is characterized in that: control storehouse and horizontal power storehouse connect firmly, the inner ring of horizontal power storehouse and radial thrust bearing connects firmly, the outer ring of loading storehouse and radial thrust bearing connects firmly, the tie-rod of planetary gear train and horizontal power storehouse connect firmly, one center gear and the loading storehouse of planet circular system connect firmly, another center gear of planetary gear train connects with the power take-off shaft of direction control engine, and direction control engine and horizontal power storehouse connect firmly.
2, aircraft according to claim 1 is characterized in that: vertical power bin and horizontal power storehouse connect firmly, and vertical power bin is arranged in the hollow channel in horizontal power storehouse.
3, aircraft according to claim 1 is characterized in that: vertical power bin and loading storehouse connect firmly, and vertical power bin is arranged in the hollow channel in loading storehouse.
4, according to claim 1,2,3 described aircraft, it is characterized in that: control storehouse and horizontal power storehouse connect firmly with pillar, and the air by-pass passage of controlling between storehouse and horizontal power storehouse communicates with the hollow channel in loading storehouse and horizontal power storehouse.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97110497 CN1172054A (en) | 1997-05-30 | 1997-05-30 | Aerobat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97110497 CN1172054A (en) | 1997-05-30 | 1997-05-30 | Aerobat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1172054A true CN1172054A (en) | 1998-02-04 |
Family
ID=5171463
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 97110497 Pending CN1172054A (en) | 1997-05-30 | 1997-05-30 | Aerobat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1172054A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102638018A (en) * | 2012-03-25 | 2012-08-15 | 河南省电力公司安阳供电公司 | Remotely-controlled deicing device for high-tension lines |
| WO2014026574A1 (en) * | 2012-08-16 | 2014-02-20 | Chai Guijing | Flight control device for double-spiral saucer-shaped aircraft |
-
1997
- 1997-05-30 CN CN 97110497 patent/CN1172054A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102638018A (en) * | 2012-03-25 | 2012-08-15 | 河南省电力公司安阳供电公司 | Remotely-controlled deicing device for high-tension lines |
| CN102638018B (en) * | 2012-03-25 | 2015-02-04 | 河南省电力公司安阳供电公司 | Remotely-controlled deicing device for high-tension lines |
| WO2014026574A1 (en) * | 2012-08-16 | 2014-02-20 | Chai Guijing | Flight control device for double-spiral saucer-shaped aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C06 | Publication | ||
| PB01 | Publication | ||
| C01 | Deemed withdrawal of patent application (patent law 1993) | ||
| WD01 | Invention patent application deemed withdrawn after publication |