CN213800156U

CN213800156U - Tilting oar-free ducted aircraft

Info

Publication number: CN213800156U
Application number: CN202022547006.4U
Authority: CN
Inventors: 吴远航; 朱清华; 赵猛; 刘佳; 王昊
Original assignee: Nanjing University of Aeronautics and Astronautics
Current assignee: Nanjing University of Aeronautics and Astronautics
Priority date: 2020-11-06
Filing date: 2020-11-06
Publication date: 2021-07-27
Anticipated expiration: 2030-11-06

Abstract

The utility model discloses a tilting propellerless ducted aircraft, comprising: a fuselage, a wing, a propellerless duct, a guide tube, a tilting mechanism and a power device; the number of the wings is two, respectively It traverses the middle of the fuselage; the number of the paddleless ducts is four, which are respectively installed at the ends of the two wings, and are connected with the power unit through the guide tube; the paddleless duct is connected to the tilting mechanism Through the connection, the tilting mechanism pulls the propellerless duct to tilt by extending and retracting its connecting rod; the tilting mechanism is controlled by the aircraft controller by means of electrical communication. The utility model uses a propellerless duct as a lift and thrust system, and compared with a helicopter, a rotary-wing aircraft such as a tilt-rotor has high safety, and there is no risk of the rotor flying out.

Description

Tilting oar-free ducted aircraft

Technical Field

The utility model belongs to the technical field of the aviation, specifically indicate a no oar duct aircraft verts.

Background

With the continuous development of the aviation industry, the aviation technology is continuously developing towards high speed, vertical take-off and landing and variability. Various new types of aircraft meeting these requirements are available, and typical aircraft include tiltrotor aircraft, tailstock-type VTOL aircraft, and hybrid high-speed helicopters represented by U.S. X3 and S97.

Besides the innovative aircraft which is arranged by adjusting the lift force and the thrust of the aircraft, a plurality of novel lift force generation systems are also provided, such as shaftless ducts, swirl rotors and the like. However, in these techniques, the rotor is used as a device for generating vertical lifting force, and one or more blades rotating at high speed are exposed outside, which is highly dangerous. With the intensive research on aerodynamics in recent years, products for innovative application of aerodynamics such as bladeless fans are also appearing on the market today. The utility model discloses borrow for reference this bladeless fan's theory, provide an aircraft with no oar duct production lift and thrust.

Disclosure of Invention

An object of the present invention is to provide a rotor aircraft without oar that verts to solve among the prior art device that the rotor produced VTOL lift, all have one or more high-speed rotatory paddle to expose externally, have stronger dangerous problem. The utility model discloses a vert oar duct aircraft does not have the oar duct by four oar ducts adorn in the point portion of two pairs of wings as lift and thrust system. The four oar-free ducts can rotate 90 degrees around the span chord of the aircraft wing; when the oar-free duct is in the vertical direction, the oar-free duct generates lift force to enable the aircraft to take off and land vertically, and when the oar-free duct rotates to the horizontal direction, the oar-free duct generates thrust to enable the aircraft to fly forwards at a high speed.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the utility model discloses a vert oar duct aircraft that does not have, include: the aircraft comprises an airframe, wings, a non-oar duct, a flow guide pipe, a tilting mechanism and a power device;

the number of the wings is two, and the two wings respectively transversely penetrate through the middle of the fuselage;

the number of the oar-free ducts is four, the four oar-free ducts are respectively arranged at the end parts of the two wings and are connected with the power device through the flow guide pipe;

the power device is fixed in the machine body;

the oar-free duct is connected with the tilting mechanism, and the tilting mechanism pulls the oar-free duct to tilt through a telescopic connecting rod of the tilting mechanism;

the tilt mechanism is controlled by an aircraft controller in electrical communication.

Further, the longitudinal section of the non-oar duct is in an airfoil shape.

Furthermore, the interior of the non-oar duct is a cavity, and a round air hole communicated with the flow guide pipe is arranged on the side close to the wing.

Furthermore, the upper part of the non-oar duct is provided with an annular air gap, and the air flow accelerated by the turbine is uniformly sprayed out through the air gap.

Furthermore, the power device is a gas turbine or an electric turbine, the front end of the turbine is communicated with the external space, gas is accelerated by the turbine and flows into the inner cavity of the non-paddle duct through the flow guide pipe, the space at the rear end of the turbine is completely closed except the flow guide pipe, and the gas is discharged only through the flow guide pipe.

Furthermore, the tilting mechanism is a hydraulic actuator cylinder or a steering engine and is fixedly connected to the end part of the wing.

The utility model has the advantages that:

(1) the utility model discloses a no oar duct is lift and thrust system, compares in the helicopter, and rotor class aircraft security such as rotor verts is high, can not have the rotor departure risk.

(2) The utility model discloses no oar duct can vert, therefore it can VTOL but also can fly at a high speed, has the potentiality of supersonic speed flight.

(3) The utility model discloses a no oar duct longitudinal section shape is symmetrical wing section, has increased the wing area in other words before high-speed when flying, and the lift is big, and does not have the oar dish structure, and the resistance is little, therefore the lift-drag ratio is big.

(4) The power device of the utility model can work under water if selecting the electric turbine, thus being capable of being used as an air-water amphibious aircraft.

Drawings

FIG. 1 is an overall outline view of the high-speed forward flight state of the present invention;

FIG. 2 is an overall outline view of the vertical take-off and landing state of the present invention;

FIG. 3 is a schematic view of the engine connected to a non-bladed duct;

fig. 4 is a structural view of the tilting mechanism of the present invention;

fig. 5 is a longitudinal sectional view of the oar-free duct of the present invention;

fig. 6 is a top view of the oar-free duct of the present invention;

in the figure, 1-fuselage, 2-wing, 3-no-propeller duct, 4-honeycomb duct, 5-tilting mechanism, 6-power device and 7-inner cavity.

Detailed Description

In order to facilitate understanding of those skilled in the art, the present invention will be further described with reference to the following examples and drawings, which are not intended to limit the present invention.

Referring to fig. 1-6, the utility model discloses a vert and do not have oar duct aircraft, include: the aircraft comprises an airframe 1, wings 2, a non-oar duct 3, a flow guide pipe 4, a tilting mechanism 5 and a power device 6;

the number of the wings 2 is two, and the two wings respectively transversely penetrate through the middle of the fuselage 1;

the number of the oar-free ducts 3 is four, the four oar-free ducts are respectively arranged at the end parts of the two wings 2 and are connected with the power device 6 through the flow guide pipe 4;

the oar-free duct 3 is connected with the tilting mechanism 5 through a connecting rod, and the tilting mechanism 5 pulls the oar-free duct 3 to tilt through the telescopic connecting rod of the tilting mechanism 5;

the tilting mechanism 5 is controlled by the aircraft controller by means of electrical communication.

The longitudinal section of the non-paddle duct 3 is in an airfoil shape, so that the integral lift-drag ratio of the aircraft during flying is larger, the interior of the non-paddle duct 3 is a cavity, a circular air hole is formed in the side close to the wing and communicated with the flow guide pipe 4, an annular air gap is formed in the upper portion of the non-paddle duct 3, airflow accelerated by the turbine is uniformly sprayed out through the air gap, and the aircraft obtains thrust and lift force.

The power device 6 is a gas turbine or an electric turbine, the front end of the turbine is communicated with the external space, gas is accelerated by the turbine and flows into the inner cavity 7 of the non-paddle duct through the guide pipe 4, the space at the rear end of the turbine is completely closed except the guide pipe, and the gas is discharged only through the guide pipe 4.

The tilting mechanism 5 is a hydraulic actuator cylinder or a steering engine and is fixedly connected to the end part of the wing.

The utility model discloses a tilting paddle-free duct aircraft working principle as follows:

the gas turbine engine or the electric turbine sucks external gas flow into the engine to accelerate the gas flow, the rear end of the turbine is of a closed structure, and accelerated gas can only flow out of the flow guide pipe, enters the inner cavity 7 of the non-paddle duct 3 and finally flows out of a gas gap at the upper end of the non-paddle duct. The accelerated gas momentum is increased, so that the momentum theorem shows that the paddle-free duct can bear the force in the direction opposite to the airflow acceleration, and in addition, the accelerated airflow flows out from the middle of the paddle-free duct, so that the dynamic pressure of the gas in the inner area of the paddle-free duct is high, the static pressure is low, and the airflow at the upper end of the paddle-free duct is pressed to the rear of the paddle-free duct to further increase the force in the direction opposite to the airflow. Thereby providing lift or thrust for the aircraft, generating lift when the oar-free duct is in the vertical upward direction, and generating thrust when the channel is in the horizontal direction.

The operation principle in vertical take-off and landing is similar to that of a common four-rotor aircraft, and the aircraft is operated by adjusting the force generated by the four oar-free ducts. Thereby it adjusts the gesture that the size of four lift changes the aircraft and manipulates the aircraft flight to be different with ordinary four rotor craft, thereby the utility model discloses thereby then control the aircraft gesture through the size of the produced power of four ducts of the volume that the inside valve of adjustment water conservancy diversion comes control outflow and manipulate the aircraft flight.

The utility model discloses the theory of operation when flying before high-speed, four ducts only do not regard as controlling means as thrust device, control the size of thrust through the valve size in the change honeycomb duct. The control surface of the aircraft is the same as that of a common fixed wing aircraft, and the attitude of the aircraft is adjusted through ailerons, elevators and rudder.

The utility model discloses the concrete application way is many, and the above-mentioned only is the preferred embodiment of the utility model, should point out, to ordinary skilled person in this technical field, under the prerequisite that does not deviate from the utility model discloses the principle, can also make a plurality of improvements, and these improvements also should be regarded as the utility model discloses a scope of protection.

Claims

1. The utility model provides a tilting paddle-less duct aircraft which characterized in that includes: the aircraft comprises an airframe, wings, a non-oar duct, a flow guide pipe, a tilting mechanism and a power device;

the power device is fixed in the machine body;

2. The tilting default duct aircraft according to claim 1, wherein a longitudinal section of the default duct is airfoil shaped.

3. The tilt-oar-free ducted aircraft according to claim 1, wherein the inside of the oar-free duct is a cavity, and a circular air hole is provided on the side close to the wing and communicated with the flow guide pipe.

4. The tilt-oar-free ducted aircraft according to claim 1, wherein the upper portion of the oar-free ducted aircraft is provided with an annular air gap through which the air flow accelerated by the turbine is uniformly ejected.

5. The tiltrotor unmanned aircraft according to claim 1, wherein the power plant is a gas turbine or an electric turbine, the front end of the turbine is communicated with the external space, the gas is accelerated by the turbine and flows into the inner cavity of the unmanned duct through the draft tube, the space at the rear end of the turbine is completely closed except the draft tube, and the gas is discharged only through the draft tube.

6. The tilt featherless ducted aircraft as claimed in claim 1 wherein the tilt mechanism is a hydraulic ram or steering engine attached to the ends of the wings.