CN201712789U - Wingless aircraft - Google Patents
Wingless aircraft Download PDFInfo
- Publication number
- CN201712789U CN201712789U CN2010201859378U CN201020185937U CN201712789U CN 201712789 U CN201712789 U CN 201712789U CN 2010201859378 U CN2010201859378 U CN 2010201859378U CN 201020185937 U CN201020185937 U CN 201020185937U CN 201712789 U CN201712789 U CN 201712789U
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- wing
- aircraft
- aerocraft
- wingless
- wingless aircraft
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Abstract
The utility model relates to a wingless aircraft, which comprises an aircraft body. The wingless aircraft is characterized in that a gas jet opening is disposed on the upper surface of the aircraft body and provided with a control plate, and the control plate is connected with the aircraft body through an adjusting rod. The wingless aircraft can realize perpendicular lifting and suspension. The upper surface of the wingless aircraft generates airflow, and flow velocity difference is directly generated between the upper and lower surfaces of the wingless aircraft, thereby generating lifting power of the wingless aircraft. Compared with the existing aircrafts (such as air buses), the wingless aircraft is not limited by wings or landing sites, can be larger and is more reasonable in structure.
Description
Affiliated technical field
The utility model relates to a kind of aviation machine.
Background technology
According to aerodynamic principle, in the air rate difference of object upper and lower surface, the air pressure on the surface that flow velocity is slow so just produced difference of pressure, has just had the lift of air greater than the fast surface of flow velocity.Around this principle, and the method for aerocraft employing now is, makes air from wing two surface flow by wing cutting air, because the shape difference of wing upper and lower surface makes the flow velocity difference of air, and has produced lifting force of wings.So no matter existing aerocraft is fixed-wing (as big capable passenger plane) or movable wing (as helicopter), all must rely on wing and carry out work.
Summary of the invention
The purpose of this utility model provides a kind of upper and lower surface current difference of body that utilizes own and produces the no wing aerocraft of lift to remedy the deficiency of prior art.
The technical solution adopted in the utility model is: no wing aerocraft, comprise body, and it is characterized in that: the upper surface at body is provided with gas ejection ports, and control desk is arranged on the gas ejection ports, connects by adjust bar between control desk and the body.
The beneficial effects of the utility model are: the no wing aerocraft in the present technique has aerocraft is arranged the now comprehensive characteristics of (fixed-wing and movable wing).Method that its former because present technique adopts is to allow the upper surface of no wing aerocraft produce air-flow, and it is poor to make the upper and lower surface of the no wing aerocraft air-flow velocity directly occur, thus generation to no wing aerocraft lift.(what point out to be that this novel aircrafts obtains lift here at this is no wing aerocraft itself, but not there is not the wing of wing aerocraft, wing be not no wing aerocraft must) when the air flow unanimity of the upper surface that makes no wing aerocraft, no wing aerocraft just obtains a reciprocal horizontal thrust (also obtaining lift upwards simultaneously), no wing aerocraft also just can parallel motion, when the air flow of the upper surface of no wing aerocraft inconsistent, but flow to two or more different directions, the reversing sense thrust of acquisition is cancelled each other (and the air rate of the upper surface of novel aircrafts is greater than air rate of lower surface), the lift of no wing aerocraft with regard to only having obtained to make progress, just not having wing aerocraft can vertical takeoff and landing and aerial the suspension.Compare with present aerocraft (as airliner), do not have the restriction of wing and landing site, it is bigger that no wing aerocraft can be made, more reasonable structure.
Below in conjunction with accompanying drawing, the utility model is further described by embodiment:
Description of drawings
Fig. 1 is the structural representation of the utility model embodiment;
No wing aerocraft comprises butterfly body 1, is provided with gas ejection ports 2 at the upper surface of butterfly body 1, and control desk 3 is arranged on the gas ejection ports 2, connects by adjust bar 4 between control desk 3 and the butterfly body 1.
The specific embodiment
Embodiment:
After adjust bar 4 was regulated height, control desk 3 produced with respect to butterfly body 1 angle of inclination, thereby makes the injection direction of air-flow that deviation be arranged, and dish-like body 1 has just obtained the ability of parallel motion simultaneously.
The utility model can be realized vertical takeoff and landing and aerial the suspension; Wing and aerocraft merge, and open the epoch of no wing aviation; But ultra-large type, that can build is bigger than modern airdreadnought, (not having the restriction of wing and landing site); Also can be used as the first-selection of individual aerocraft, (no wing can make aerocraft area under same lift littler, but and vertical takeoff and landing and aerial the suspension); Can also realize changeable layman (restriction of no wing, its shape can be changeable); (it is far away that Fixed-Wing has voyage, and speed is fast, the characteristics that load carrying ability is big to have the comprehensive advantage of fixed-wing and movable wing aerocraft.The movable wing aerocraft has vertical takeoff and landing and the aerial characteristics that suspend); Energy loss-rate modern aircraft is low.
Claims (1)
1. do not have wing aerocraft, comprise body, it is characterized in that: the upper surface at body is provided with gas ejection ports, and control desk is arranged on the gas ejection ports, connects by adjust bar between control desk and the body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201859378U CN201712789U (en) | 2010-05-11 | 2010-05-11 | Wingless aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201859378U CN201712789U (en) | 2010-05-11 | 2010-05-11 | Wingless aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201712789U true CN201712789U (en) | 2011-01-19 |
Family
ID=43458788
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201859378U Expired - Fee Related CN201712789U (en) | 2010-05-11 | 2010-05-11 | Wingless aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201712789U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620751A (en) * | 2015-09-07 | 2016-06-01 | 吴锜 | Saucer type vertical lifting type flight device |
-
2010
- 2010-05-11 CN CN2010201859378U patent/CN201712789U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620751A (en) * | 2015-09-07 | 2016-06-01 | 吴锜 | Saucer type vertical lifting type flight device |
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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: 20110119 Termination date: 20140511 |