CN211442751U - Bladeless aircraft capable of tilting - Google Patents
Bladeless aircraft capable of tilting Download PDFInfo
- Publication number
- CN211442751U CN211442751U CN201921713300.9U CN201921713300U CN211442751U CN 211442751 U CN211442751 U CN 211442751U CN 201921713300 U CN201921713300 U CN 201921713300U CN 211442751 U CN211442751 U CN 211442751U
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- power
- aircraft
- paddle
- rotating shaft
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Abstract
The utility model discloses a tiltable bladeless aircraft, which comprises an aircraft body and two power devices symmetrically arranged at two sides of the aircraft body; the power device comprises a paddle-free power fan, a rotating shaft and a power motor, wherein one end of the rotating shaft is connected with the machine body, the other end of the rotating shaft is rotationally connected with the paddle-free power fan, the power motor is arranged on the paddle-free power fan, and a cyclone accelerator is arranged on the rotating shaft; the fuselage is in the shape of an airfoil; the machine body is provided with a central control ring, the central control ring controls the bladeless power fan to change at a certain angle with the horizontal plane of the machine body, the change range is 0-90 degrees, and a bladeless power device is arranged in the inner cavity of the central control ring; a battery for supplying power to the aircraft is mounted inside the fuselage. The utility model discloses can realize high-efficient, stable and long voyage time, but also can effectual utilization can vert the function realize free change flight gesture.
Description
Technical Field
The utility model relates to an aircraft technical field, concretely relates to bladeless aircraft can empty to change.
Background
The main components of the traditional unmanned helicopter for generating lift force are generated by interaction between the rotation of blades in a rotor system and air, the blades are connected with a rotor main shaft by virtue of a hub, the hub is a key component which is continuously changed, and the configuration technology is the core technology of the helicopter. The early articulated hub not only has a flapping hinge, a shimmy hinge and a variable pitch hinge, but also has various bearings, shimmy reducers, limiters and the like, has a complex structure and a large number of parts, and not only has high manufacturing cost, expensive maintenance cost, large maintenance workload and poorer safety. Bladeless fans were first introduced in the united kingdom in 2009 and were originally called "air multipliers". The biggest difference of the bladeless fan is that the bladeless fan can output wind power without fan blades of a traditional fan. There are very few reports in the prior art of bladeless fans for use on aircraft.
Disclosure of Invention
The utility model discloses the problem that will solve is: the utility model provides a no leaf aircraft can vert, can realize high-efficient, stable and long voyage, but also can the free change flight attitude of function realization that effectual utilization can vert.
The utility model discloses a solve the technical scheme that above-mentioned problem provided and do: a tiltable bladeless aircraft comprises a fuselage and two power devices symmetrically arranged on two sides of the fuselage; the power device comprises a paddle-free power fan, a rotating shaft and a power motor, wherein one end of the rotating shaft is connected with the machine body, the other end of the rotating shaft is rotationally connected with the paddle-free power fan, the power motor is arranged on the paddle-free power fan, and a cyclone accelerator is arranged on the rotating shaft; the fuselage is in the shape of an airfoil; the machine body is provided with a middle hole control ring, the middle hole control ring controls the power fan without the paddle to change at a certain angle with the horizontal plane of the machine body, the change range is 0-90 degrees, and a power device without the paddle is arranged in the inner cavity of the middle hole control ring; a battery for supplying power to the aircraft is mounted inside the fuselage.
Preferably, the power fans without the blades can generate power during vertical take-off and landing, and the pitching action is realized by rotating the power fans without the blades on two sides connected with the aircraft body and the control ring with the middle hole to enable the aircraft to generate angular deviation during flying.
Compared with the prior art, the utility model has the advantages that: the utility model is not only suitable for the field of aerial geophysical prospecting, but also suitable for agriculture and forestry operation, aerial photography observation, material transportation and other aspects, and has the advantages of heavy load, high efficiency, stability, safety, convenience, low cost and the like; and structurally, the design of the aerofoil fuselage provides good aerodynamic characteristics for the entire aircraft. The utility model discloses unmanned aerial vehicle can realize VTOL and hover the utility model discloses the first paddle-free fan that will not be used for unmanned aerial vehicle has overcome following technological problem: the problem of power distribution of a blade-free fan for an unmanned aerial vehicle is solved; and secondly, the problem that the unmanned aerial vehicle powered by the paddle-free fan has the vertical take-off and landing state and the high-speed forward flight state conversion is solved.
Drawings
The accompanying drawings, which are described herein, serve to provide a further understanding of the invention and constitute a part of this specification, and the exemplary embodiments and descriptions thereof are provided for explaining the invention without unduly limiting it.
Fig. 1 is a front view of the overall structure of the present invention.
Fig. 2 is a top view of the overall structure of the present invention.
Fig. 3 is a side view of the present invention with tilting.
Fig. 4 is a front view of the present invention at a 90 ° tilt angle.
Fig. 5 is a sectional view of the connection between the rotating shaft and the bladeless power fan according to the present invention.
The attached drawings are marked as follows: 1. the device comprises a rotating shaft, 2 a blade-free power fan, 3 a machine body, 4 a middle hole control ring, 5 and a power motor.
Detailed Description
The following detailed description will be made with reference to the accompanying drawings and examples, so that how to implement the technical means of the present invention to solve the technical problems and achieve the technical effects can be fully understood and implemented.
The specific embodiment of the utility model is shown in fig. 1 to 5, a tiltable bladeless aircraft, which comprises a fuselage 3 and two power devices symmetrically arranged at two sides of the fuselage 3; the power device comprises a paddle-free power fan 2, a rotating shaft 1 and a power motor 5, one end of the rotating shaft 1 is connected with a machine body 3, the other end of the rotating shaft 1 is rotatably connected with the paddle-free power fan 2, the power motor 5 is installed on the paddle-free power fan 2, and a cyclone accelerator is installed on the rotating shaft 1; the fuselage 3 is in the shape of a wing; a middle hole control ring 4 is arranged on the machine body 3, the middle hole control ring 4 controls the paddle-free power fan 2 to change at a certain angle with the horizontal plane of the machine body 3, the change range is 0-90 degrees, and a paddle-free power device is arranged in the inner cavity of the middle hole control ring 4; a battery for supplying power to the aircraft is arranged inside the fuselage 3; after the airflow is accelerated by the cyclone accelerator, three channels are respectively a paddle-free power fan on the left side of the airframe, a paddle-free power fan on the right side of the airframe and a hollow control ring, the airflow is sprayed out through the acceleration to provide power for the vertical take-off and landing and hovering of the aircraft, and the hollow control ring is mainly used for the vertical take-off and landing and hovering of the aircraft; during takeoff, the lift systems on the two sides of the aircraft body tilt forward slightly to generate most of lift and a small part of forward flight thrust; the pitching motion of the airplane is controlled by the tilting angles of the wings at the left side and the right side together with the lift system; the roll motion is controlled by the differential motion of the lift systems on both sides of the fuselage.
Two power fans without blades on two sides of the aircraft body provide power for the whole aircraft during flying, the tilting angle of the two fans is controlled to be 0-90 degrees, and the flying attitude is changed by changing different tilting angles during flying, so that the two power fans can be used for controlling the flying height and lifting of the aircraft; the 90-degree state is kept during cruising flight, so that forward flight power can be provided during flight; when the incoming flow speed is very high, the tilting angle of the power fans without the blades on the two sides can be controlled, the flight direction of the aircraft can be adjusted in time, forward flying power is provided for the aircraft, and the wind resistance performance is improved.
Furthermore, the power fans 2 without blades can generate power during vertical take-off and landing, and the pitching action is realized by rotating the power fans 2 without blades on two sides connected with the aircraft body 3 and the control ring 4 with the middle hole to enable the aircraft to generate angle deviation during flight.
The utility model discloses the theory of operation of aircraft: the unmanned aerial vehicle body adopts an integral streamline shape, has small air resistance, and adopts two rotatable paddle-free lift systems to generate lift force and thrust force required by the flight of a helicopter. The working principle of the paddle-free lift system is as follows: the bladeless fan utilizes an electric motor in the middle fixed shaft to suck air, the air flow speed is increased through the cyclone accelerator, the air is sprayed out through the bladeless fans in the middle of the machine bodies on two sides, the nearby air is driven to enter the fan ring and is blown out outwards at a high speed, and the two effects are superposed to generate power required by flight.
The utility model has the advantages that: the utility model is not only suitable for the field of aerial geophysical prospecting, but also suitable for agriculture and forestry operation, aerial photography observation, material transportation and other aspects, and has the advantages of heavy load, high efficiency, stability, safety, convenience, low cost and the like; and structurally, the design of the aerofoil fuselage provides good aerodynamic characteristics for the entire aircraft. The utility model discloses unmanned aerial vehicle can realize VTOL and hover the utility model discloses the first paddle-free fan that will not be used for unmanned aerial vehicle has overcome following technological problem: the problem of power distribution of a blade-free fan for an unmanned aerial vehicle is solved; and secondly, the problem that the unmanned aerial vehicle powered by the paddle-free fan has the vertical take-off and landing state and the high-speed forward flight state conversion is solved.
The foregoing is illustrative of the preferred embodiments of the present invention only, and is not to be construed as limiting the claims. The present invention is not limited to the above embodiments, and the specific structure thereof is allowed to be changed. All changes which come within the scope of the independent claims of the invention are to be embraced within their scope.
Claims (2)
1. A kind of inclinable bladeless aircraft, characterized by: comprises a machine body (3) and two power devices symmetrically arranged at two sides of the machine body (3); the power device comprises a paddle-free power fan (2), a rotating shaft (1) and a power motor (5), one end of the rotating shaft (1) is connected with the machine body (3), the other end of the rotating shaft (1) is rotationally connected with the paddle-free power fan (2), the power motor (5) is installed on the paddle-free power fan (2), and a cyclone accelerator is installed on the rotating shaft (1); the fuselage (3) is in the shape of a wing; a middle hole control ring (4) is arranged on the machine body (3), the middle hole control ring (4) controls the paddle-free power fan (2) to change at a certain angle with the horizontal plane of the machine body (3), the change range is 0-90 degrees, and a paddle-free power device is arranged in the inner cavity of the middle hole control ring (4); the fuselage (3) is internally equipped with a battery for supplying power to the aircraft.
2. The tiltable bladeless aircraft according to claim 1, wherein: the power fans (2) without the blades can generate power when taking off and landing vertically, and the pitching action is realized by rotating the power fans (2) without the blades at two sides connected with the aircraft body (3) and the control ring (4) with the middle hole to enable the aircraft to generate angle deviation during flying.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921713300.9U CN211442751U (en) | 2019-10-14 | 2019-10-14 | Bladeless aircraft capable of tilting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921713300.9U CN211442751U (en) | 2019-10-14 | 2019-10-14 | Bladeless aircraft capable of tilting |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211442751U true CN211442751U (en) | 2020-09-08 |
Family
ID=72317608
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921713300.9U Expired - Fee Related CN211442751U (en) | 2019-10-14 | 2019-10-14 | Bladeless aircraft capable of tilting |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211442751U (en) |
-
2019
- 2019-10-14 CN CN201921713300.9U patent/CN211442751U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200908 Termination date: 20211014 |
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| CF01 | Termination of patent right due to non-payment of annual fee |