KR20230166757A - Aircraft - Google Patents

Abstract

The present invention relates to flying vehicles.
According to an embodiment of the present invention, a plurality of air flow means for generating air flow inside the disc-shaped aircraft frame are symmetrically arranged, and the air flowing into the interior of the aircraft frame is pressurized and discharged downward by the air flow means. Disclosed is an aircraft configured to provide stable lift without exposing rotary blades such as propellers to the outside, and to enable tilting control of the motor and propeller constituting the air flow means.

Description

Aircraft

The present invention relates to an aircraft, and more specifically, a plurality of air flow means for generating air flow inside a disk-shaped aircraft frame are symmetrically arranged, and the air flowing into the inside of the aircraft frame is moved by the air flow means. It relates to an aircraft that is configured to be pressurized and discharged from the bottom, providing stable buoyancy without exposing rotary blades such as propellers to the outside, and enabling tilting control of the motor and propeller constituting the air flow means.

Various forms of aircraft capable of flight, equipped with rotating wings such as propellers, have been proposed.

However, conventional unmanned aerial vehicles have a limitation in that they can be exposed to safety accidents because their rotary wings, such as propellers, are exposed to the outside.

In addition, the conventional unmanned aerial vehicle as described above had limitations in providing the ability to freely switch forward and backward and left and right while stopped in place during flight.

Republic of Korea registered patent 10-2049599 (registered on November 21, 2019) Republic of Korea registered patent 10-2018975 (registered on August 30, 2019)

The present invention was developed in consideration of the above problems, and a plurality of air flow means for generating air flow inside the disc-shaped aircraft frame are arranged symmetrically, and the air flowing into the inside of the aircraft frame is transferred to the air flow means. It is configured to be pressurized and discharged to the bottom by providing a stable lifting force without exposing the rotating blades such as a propeller to the outside, and to provide a flying vehicle configured to enable tilting control of the motor and propeller constituting the air flow means.

According to one aspect of the present invention for achieving the above object, a main body portion; an outer body portion formed in a ring shape surrounding the outside of the main body portion and disposed at a distance from the outside of the main body portion; The main body portion and the outer body portion are connected and integrally coupled, and include at least a plurality of first connection frames arranged to connect the outer side of the main body portion and the inner side of the outer body portion, and configured to allow air flow in the vertical direction. Connection frame part; And a transverse support bar and a transverse support bar disposed symmetrically in a ring-shaped space between the outer side of the main body portion and the inner side of the outer body portion and extending to the left and right, respectively, from the middle portion of the first connection frame. It includes a motor installed at each end of both sides and a propeller driven by each of the motors, and a plurality of air flow means configured to pressurize and discharge air introduced from the upper part to the lower part, wherein the transverse support rod is a rotating means. Disclosed is an aircraft that is capable of rotating to one side or the other, and is configured to control tilting of the motor and propeller by rotating to one side or the other of the transverse support rod.

Preferably, an operating lever is provided as the rotation means on one side of the transverse support bar, and the operating lever is connected to a tilting control means installed in the main body through a link element, and the tilting control means is connected to the link. The transverse support bar is configured to rotate to one side or the other by manipulating and controlling the element in the pulling or pushing direction.

Preferably, the connection frame portion includes a plurality of upper first connection frames disposed to connect the outside of the main body portion and the inside of the outer body portion, and a plurality of second connection frames connecting adjacent upper first connection frames, It is arranged to connect the outside of the main body portion and the inside of the outer body portion and includes a plurality of lower first connection frames disposed at intervals below the upper first connection frame, and the air flow means is configured to 1 It is installed based on the connecting frame.

Preferably, the outer body portion is configured to provide buoyancy so that the aircraft can float on water.

Preferably, the present invention includes a plurality of net frames installed along the outer edge of the connection frame portion and extending in an outward direction; and a structural net coupled to the plurality of net frames and installed to form a ring shape surrounding an outer side of the outer body portion.

Preferably, the present invention includes a plurality of net frames installed along the upper outer edge of the connection frame portion and extending in an upper outer direction; A net for falling objects installed so as to receive falling objects from the upper part by combining the edges of the plurality of net frames; and a structural net coupled to the plurality of net frames and installed to form a ring shape surrounding an outer side of the outer body portion.

Preferably, each of the net frames is installed on an upper outer edge of each of the first connection frames.

Preferably, the present invention is configured to include an upper body part that is coupled to the upper side of the main body part and on which a person can ride.

The present invention as described above provides stable buoyancy without exposing rotating blades such as propellers to the outside.

In addition, the present invention is configured to enable tilting control of the motor and propeller constituting the air flow means, thereby enabling rapid and stable flight control.

1 is a perspective view of an aircraft according to an embodiment of the present invention;
Figure 2 is a perspective view from the bottom of an aircraft according to an embodiment of the present invention;
3 is a side view of an aircraft according to an embodiment of the present invention;
4 is a bottom view of an aircraft according to an embodiment of the present invention;
Figure 5a is a partial cross-sectional perspective view of an aircraft according to an embodiment of the present invention;
Figure 5b is another partial cross-sectional perspective view of an aircraft according to an embodiment of the present invention;
Figure 6 is another perspective view of an aircraft according to an embodiment of the present invention;
Figure 7 is a partial perspective view of an aircraft according to an embodiment of the present invention;
Figure 8 is another perspective view of an aircraft according to an embodiment of the present invention;
Figure 9 is another perspective view of an aircraft according to an embodiment of the present invention;
Figure 10 is another perspective view of an aircraft according to an embodiment of the present invention;
Figure 11 is another perspective view of an aircraft according to an embodiment of the present invention;
Figure 12 is a control configuration diagram of an aircraft according to an embodiment of the present invention.

The present invention can be implemented in various other forms without departing from its technical spirit or main features. Accordingly, the embodiments of the present invention are merely examples in all respects and should not be construed as limited.

Terms such as first, second, etc. are used only for the purpose of distinguishing one component from another component. For example, a first component may be named a second component, and similarly, the second component may also be named a first component without departing from the scope of the present invention.

When a component is referred to as being “connected” or “connected” to another component, it may be directly connected to or connected to the other component, but other components may also exist in between.

As used in this application, singular expressions include plural expressions, unless the context clearly dictates otherwise. In this application, terms such as “comprise”, “provide”, “have”, etc. are intended to express the presence of the components described in the specification or a combination thereof, but do not indicate the possibility that other components or features may be present or added. It is not excluded in advance.

Hereinafter, preferred embodiments according to the present invention will be described in detail with reference to the attached drawings.

Figure 1 is a perspective view of an aircraft according to an embodiment of the present invention, Figure 2 is a bottom perspective view of an aircraft according to an embodiment of the present invention, Figure 3 is a side view of an aircraft according to an embodiment of the present invention, and Figure 4 is a perspective view of an aircraft according to an embodiment of the present invention. A bottom view of an aircraft according to an embodiment of the present invention, Figure 5A is a partial cross-sectional perspective view of an aircraft according to an embodiment of the present invention, Figure 5B is another partial cross-sectional perspective view of an aircraft according to an embodiment of the present invention, and Figure 6 is an implementation of the present invention. Another perspective view of an aircraft according to an example, Figure 7 is a perspective view of a partial excerpt of an aircraft according to an embodiment of the present invention.

In the aircraft (F) of this embodiment, the main body portion 10 and the outer body portion 20 forming a ring shape surrounding the outside thereof are coupled through the connection frame portion 30.

For example, the main body 10 may be formed in a cylindrical or disk shape, but is not limited thereto.

The outer body portion 20 forms a ring shape surrounding the outer side 10a of the main body portion 10 and is disposed at a distance from the outer side 10a of the main body portion 10.

The connection frame portion 30 connects the main body portion 10 and the outer body portion 20 to integrally combine the outer side 10a of the main body portion 10 and the inner side of the outer body portion 20 ( It includes at least a plurality of first connection frames 31 arranged to connect 20a) and is configured to allow air flow in the up and down directions (U-D).

Preferably, the connection frame portion 30 may be configured to include a plurality of second connection frames 32 connecting adjacent first connection frames 31.

The plurality of air flow means 40 are symmetrically disposed in the ring-shaped space S between the outer side 10a of the main body 10 and the inner side 20a of the outer body 20.

The plurality of air flow means 40 are installed based on the connecting frame portion 30 and are configured to pressurize and discharge air introduced from the top to the bottom using a propeller 46 driven by a motor 44. .

Preferably, the aircraft F of this embodiment is configured to enable tilting control of the motor 44 and propeller 46.

In addition, the air flow means 40 includes transverse support bars 42 extending to the left and right, respectively, from the middle position of the first connection frame 31, and at both ends of the transverse support bars 42. It is comprised of a motor 44 installed respectively, and a propeller 46 installed on each motor 44.

For example, the transverse support bar 42 can be rotated to one side (R1) or the other side (R2) by a rotation means, and one side (R1) or the other side (R2) of the transverse support bar 42 It is configured to enable tilting control of the motor 44 and propeller 46 by rotation.

An operating lever 43 is provided on one side of the transverse support bar 42 as the rotation means.

The operating lever 43 is connected to the tilting control means 47 installed on the main body 10 through a link element 45.

The tilting control means 47 controls the link element 45 in the pulling direction D1 or the pushing direction D2, so that the transverse support bar 42 is moved to one side R1 or the other side R2. It is structured so that it can rotate on its own.

For example, the connection frame portion 30 includes a plurality of upper first connection frames 31 arranged to connect the outer side 10a of the main body portion 10 and the inner side 20a of the outer body portion 20. 1), a plurality of second connection frames 32 connecting the adjacent upper first connection frame 31-1, the outside 10a of the main body 10, and the inside of the outer body 20 It is arranged to connect (20a) and includes a plurality of lower first connection frames 31-2 arranged at intervals below the upper first connection frame 31-1.

The air flow means 40 may be installed based on the lower first connection frame 31-2.

Preferably, the outer body portion 20 is configured to provide buoyancy so that the aircraft F can float on water.

For example, the outer body portion 20 at least partially includes a hollow element 21 and is configured to provide buoyancy using air injected into the hollow element 21.

As another example, the outer body portion 20 is at least partially composed of a buoyancy material 22 to provide buoyancy.

Preferably, the aircraft (F) of this embodiment is configured to include an upper body portion (70) that is coupled to the upper side of the main body portion (10) and on which a person can ride.

Figure 8 is another perspective view of an aircraft according to an embodiment of the present invention, Figure 9 is another perspective view of an aircraft according to an embodiment of the present invention, and Figure 10 is another perspective view of an aircraft according to an embodiment of the present invention.

Preferably, the aircraft F of this embodiment is configured to include a net 52 for falling objects.

For this purpose, a plurality of net frames 50 are installed along the upper (U) outer edge of the connection frame portion 30 and extend upward.

The net 52 for falling objects is installed so that an edge 52a is coupled to the plurality of net frames 50 to receive falling objects from the top.

Preferably, the vehicle F of this embodiment is configured to include a structural net 54.

For this purpose, a plurality of net frames 50 are installed along the outer edge of the connection frame portion 30 and extend in the outward direction A1.

The structural net 54 is coupled to the plurality of net frames 50 and is installed to form a ring shape surrounding the outer side of the outer body portion 20.

Preferably, the aircraft (F) of this embodiment is configured to include a net 52 for falling objects and a structural net 54.

For this purpose, a plurality of net frames 50 are installed along the upper (U) outer edge of the connection frame portion 30 and extend in the upper outer direction (U, A1).

The net 52 for falling objects is installed so that an edge 52a is coupled to the plurality of net frames 50 to receive falling objects from the top.

The structural net 54 is coupled to the plurality of net frames 50 and is installed to form a ring shape surrounding the outer side of the outer body portion 20.

In order to provide the net installation structure as described above, the connection frame portion 30 includes a plurality of pieces arranged to connect the outer side 10a of the main body portion 10 and the inner side 20a of the outer body portion 20. It is configured to include a first connection frame 31 and a plurality of second connection frames 32 connecting adjacent first connection frames 31, and each net frame 50 is connected to each of the first connection frames 31. It is installed outside the upper (U) side of the connection frame (31).

Figure 11 is another perspective view of an aircraft according to an embodiment of the present invention.

Preferably, the aircraft (F) of this embodiment is configured to include a camera (60).

The camera 60 is installed on the upper side of either the main body 10 or the connection frame 30.

Preferably, the aircraft F of this embodiment is configured to include a distance measurement sensor 62.

For example, the camera 60 is installed on the upper side of the main body 10 and includes a distance measurement sensor 62 disposed toward one preset direction.

Figure 12 is a control configuration diagram of an aircraft according to an embodiment of the present invention.

The aircraft (F) of this embodiment is provided with a control unit (2) and a communication unit (4), and although not shown, a rechargeable battery for power supply, a GPS module for obtaining flight location information, and an altitude sensor for obtaining flight altitude information. , and may be equipped with a gyro sensor to obtain flight attitude information. The control unit 2 and the communication unit 4 may be installed in the main body 10.

The control unit 2 may be understood as a computing means that includes a CPU and memory and runs computer software for controlling an aircraft. The control unit 2 can communicate wirelessly with the remote control system 1000 through the communication unit 4, and receives various control information, including flight control information, from the remote control system 1000 or captures the information with a camera. Image information, distance measurement information, flight position information, and flight attitude information may be transmitted to the remote control system 1000.

In addition, the control unit 2 may control the direction/speed of the air flow means 40 installed on the aircraft F based on control logic preset in memory or control commands received from the remote control system 1000. .

In addition, the control unit 2 generates image information using the camera 60 and distance measurement information using the distance measurement sensor 62, and performs flight control or rescue operation control using each information. It can be run.

For example, the remote control system 1000 runs computer software for controlling/monitoring an aircraft and may be a computing device capable of transmitting and receiving wireless information.

Although the present invention has been described with a focus on preferred embodiments with reference to the accompanying drawings, it is clear to those skilled in the art that many various and obvious modifications can be made from this description without departing from the scope of the present invention. Accordingly, the scope of the present invention should be interpreted by the stated claims to include these many modifications.

10: main body
20: Outer body part
21: hollow element
22: Buoyancy material
30: Connection frame part
31: first connection frame
32: second connection frame
40: air flow means
42: Transverse support rod
43: Lever for operation
44: motor
45: Link element
46: propeller
47: Tilting control means
50: net frame
52: Net for falling objects
54: Rescue net
70: Upper body
F: aircraft
S: Space between ring shapes

Claims (8)

main body;
an outer body portion formed in a ring shape surrounding the outside of the main body portion and disposed at a distance from the outside of the main body portion;
The main body portion and the outer body portion are connected and integrally coupled, and include at least a plurality of first connection frames arranged to connect the outer side of the main body portion and the inner side of the outer body portion, and configured to allow air flow in the vertical direction. Connection frame part; and
A transverse support bar and a transverse support bar disposed symmetrically in a ring-shaped space between the outer side of the main body portion and the inner side of the outer body portion and extending to the left and right, respectively, from the middle portion of the first connection frame. It includes a motor installed at each end of both sides and a propeller driven by each of the motors, and a plurality of air flow means configured to pressurize and discharge air introduced from the upper part to the lower part,
The transverse support rod is capable of rotating to one side or the other side by a rotating means, and is configured to enable tilting control of the motor and propeller by rotating to one side or the other side of the transverse support rod. .
According to paragraph 1,
An operating lever is provided on one side of the transverse support rod as the rotation means,
The operating lever is connected to the tilting control means installed in the main body through a link element,
An air vehicle, characterized in that the tilting control means is configured to manipulate and control the link element in a pulling or pushing direction so that the transverse support rod rotates to one side or the other.
According to paragraph 1,
The connection frame part,
A plurality of upper first connection frames arranged to connect the outside of the main body portion and the inside of the outer body portion,
a plurality of second connection frames connecting adjacent upper first connection frames;
It is arranged to connect the outside of the main body portion and the inside of the outer body portion and includes a plurality of lower first connection frames disposed at intervals below the upper first connection frame,
An aircraft, characterized in that the air flow means is installed based on the lower first connection frame.
According to paragraph 1,
An aircraft characterized in that the outer body is configured to provide buoyancy so that the aircraft can float on water.
According to paragraph 1,
A plurality of net frames installed along the outer edge of the connection frame portion and extending in an outward direction; and
A structural net coupled to the plurality of net frames and installed to form a ring shape surrounding an outer side of the outer body portion.
According to paragraph 1,
A plurality of net frames installed along the upper outer edge of the connection frame portion and extending in an upper outer direction;
A net for falling objects installed so as to receive falling objects from the upper part by combining the edges of the plurality of net frames; and
A structural net coupled to the plurality of net frames and installed to form a ring shape surrounding an outer side of the outer body portion.
According to claim 5 or 6,
An aircraft, characterized in that each of the net frames is installed on the upper outer edge of each of the first connection frames.
According to paragraph 1,
An aircraft characterized in that it includes an upper body part that is coupled to the upper side of the main body part and can accommodate a person.

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