KR102572063B1 - Aircraft with outer body - Google Patents

Abstract

The present invention relates to an air vehicle having an outer body part.
According to an embodiment of the present invention, the main body part and the outer body part forming a ring shape surrounding the outer side are coupled through the connecting frame part, and a plurality of motors are driven in the ring-shaped space between the outer side of the main body part and the inner side of the outer body part. An air vehicle having an outer body configured to reduce the risk of a safety accident due to exposure of a propeller and to provide various additional functions using the outer body is disclosed.

Description

Aircraft with an outer body {Aircraft with outer body}

The present invention relates to an aircraft having an outer body, and more particularly, a body and an outer body part forming a ring shape surrounding the outer body are coupled through a connecting frame, and a ring formed by the outer side of the body and the inner side of the outer body. A plurality of motor-driven air flow means are symmetrically arranged in the space between the shapes to reduce the risk of safety accidents due to propeller exposure and to provide various additional functions using the outer body. it's about

There have been proposed unmanned aerial vehicles equipped with rotary blades such as propellers to be able to fly, and in particular, to provide various additional functions by being configured such that the aircraft can float on water.

As an example of the prior art, Korean Registered Patent No. 10-2049599 (registered on November 21, 2019) relates to a drone for marine monitoring, which provides a structure in which horizontal thrust is generated while a vertically arranged drive motor is tilted at an angle to provide a maritime After landing, a drone capable of horizontal movement on the sea level was proposed to inspect various maritime environments.

As another example of the prior art, Korean Registered Patent No. 10-2018975 (registered on August 30, 2019) relates to a waterborne drone for measuring radioactivity in rivers and a method for controlling the same, which is remotely controlled or programmed or artificial intelligence. A configuration for an autonomous vehicle equipped with a propeller for flight generating lift and a floating body floating on the surface of the water is proposed to selectively travel on water.

However, since the conventional unmanned aerial vehicle as described above has a rotary wing such as a propeller exposed to the outside, there is a limit in that it may be exposed to a safety accident when approaching a monitoring or measurement object while moving. In addition, there are limitations in providing various additional functions due to the exposed structure of the rotor blades.

Korean Registered Patent No. 10-2049599 (registered on November 21, 2019) Korean Registered Patent No. 10-2018975 (registered on August 30, 2019)

The present invention has been devised in view of the above problems, and the main body part and the outer body part forming a ring shape surrounding the outer side are coupled through the connecting frame part, and the outer part of the main body part and the inner part of the outer body part form a ring-shaped gap. A plurality of motor-driven air flow means are symmetrically arranged in space to reduce the risk of safety accidents due to exposure of propellers and to provide an aircraft having an outer body configured to provide various additional functions using the outer body. The purpose.

According to one aspect of the present invention for achieving the above object, the body portion; an outer body portion formed in a ring shape surrounding the outside of the body portion and disposed at a distance from the outside of the body portion; a connection frame unit integrally coupled to the main body unit and the outer body unit and configured to enable air flow in a vertical direction; and symmetrically arranged in a ring-shaped space between the outer side of the main body part and the inner side of the outer body part, installed based on the connecting frame part, and air introduced from the upper part using a propeller driven by a motor is blown into the lower part. An air vehicle configured to include a plurality of air flow means configured to be pressurized and discharged is disclosed.

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

Preferably, the outer body portion at least partially includes a hollow element, and buoyancy can be provided by using air injected into the hollow element.

Preferably, the outer body portion is at least partially made of a buoyant material to provide buoyancy.

Preferably, the present invention is installed along the upper periphery of the connection frame unit, a plurality of net frames extending upward; and a net for falling objects installed such that edges are coupled to the plurality of net frames to receive falling objects from above.

Preferably, the present invention is installed along the outer periphery of the connecting frame unit, a plurality of net frames extending outwardly; and a structural net coupled to the plurality of net frames and installed to form a ring shape surrounding an outer side surface of the outer body part.

Preferably, the present invention is installed along the upper periphery of the connection frame unit, a plurality of net frames extending in the upper outer direction; A net for falling objects installed such that edges are coupled to the plurality of net frames to receive falling objects from above; and a structural net coupled to the plurality of net frames and installed to form a ring shape surrounding an outer side surface of the outer body part.

Preferably, the connection frame unit includes a plurality of first connection frames arranged to connect the outside of the body part and the inside of the outer body part, and a plurality of second connection frames connecting adjacent first connection frames. And, each of the net frames is installed on the upper periphery of each of the first connection frames.

Preferably, the connection frame unit includes a plurality of upper first connection frames arranged to connect an outside of the main body part and an inside of the outer body part, and a plurality of second connection frames connecting adjacent first connection frames to the upper side; It is configured to include a plurality of lower first connection frames arranged to connect the outer side of the main body and the inner side of the outer body portion and arranged to have a gap under the upper first connection frame, wherein the air flow means is the lower first connection frame. 1 It is installed on the basis of a connecting frame.

Preferably, the connection frame unit includes a plurality of first connection frames arranged to connect the outside of the body part and the inside of the outer body part, and a plurality of second connection frames connecting adjacent first connection frames. And, the air flow means, a transverse support rod extending to the left and right from the middle position of the first connecting frame, respectively, a motor installed at both ends of the transverse support rod, and installed on each of the motors It consists of a propeller.

Preferably, the transverse support rod is capable of rotating to one side or the other side by a rotation means, and is configured to enable tilting control of the motor and the propeller by rotating the transverse support rod to one side or the other side.

Preferably, an operating lever is provided as the pivoting means on one side of the transverse support rod, 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 By operating and controlling the element in a pulling direction or a pushing direction, the transverse support rod is configured to rotate to one side or the other side.

Preferably, the present invention is configured to further include a camera installed on an upper side of any one of the main body part and the connection frame part.

Preferably, the present invention is installed on the upper side of any one of the body part or the connection frame part and is disposed toward a preset direction; is configured to further include a distance measurement sensor.

In the present invention as described above, the body portion and the outer body portion forming a ring shape surrounding the outer portion are coupled through the connecting frame portion, and a plurality of motor-driven types are formed in the space between the outer portion of the body portion and the inner portion of the outer body portion forming a ring shape. Since the air flow means is symmetrically arranged, there is an advantage of reducing the risk of a safety accident due to exposure of the propeller and providing various additional functions using the outer body.

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

The present invention may be embodied in other various forms without departing from its technical spirit or essential characteristics. Therefore, the embodiments of the present invention are mere examples in all respects and should not be construed in a limited manner.

The terms first, second, etc. are used only for the purpose of distinguishing one component from another. For example, a first element may be termed a second element, and similarly, a second element may be termed a first element, 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 or connected to the other component, but other components may exist in the middle.

Singular expressions used in this application include plural expressions unless the context clearly dictates otherwise. In this application, terms such as "comprise" or "have" or "have" are intended to express that the components described in the specification or a combination thereof exist, but the possibility that other components or features may exist or be added. It is not precluded.

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

1 is a perspective view of an aircraft according to an embodiment of the present invention, Figure 2 is a perspective view of a bottom direction 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, Figure 4 is a side view of the aircraft according to an embodiment of the present invention A bottom view of an aircraft according to an embodiment, 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 an embodiment of the present invention Another perspective view of the aircraft according to the example.

The aircraft F of this embodiment provides a configuration suitable for being used for lifesaving purposes, for example, in proximity to a building on fire or in proximity to a victim on the water.

In the flight body F of this embodiment, the body portion 10 and the outer body portion 20 forming a ring shape surrounding the outside are coupled through a connecting frame portion 30. Preferably, the body part 10, the outer body part 20, and the connection frame part 30 may be made of a lightweight elastic synthetic resin material, and in particular, a lightweight material capable of airtight structure to provide buoyancy as will be described later. At the same time, it is preferable to be made of a synthetic resin material having sufficient strength so that the net for falling objects 52 and the structural net 54 can be installed.

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

The outer body portion 20 forms a ring shape surrounding the outer side 10a of the body portion 10 and is disposed with a gap from the outer side 10a of the body portion 10 .

The connection frame part 30 connects the main body part 10 and the outer body part 20 to be integrally coupled, and is configured to enable air flow in the vertical direction (U-D).

The plurality of air flow means 40 are symmetrically disposed in a ring-shaped space S formed between the outer 10a of the main body 10 and the inner 20a of the outer body 20 . In the case of the embodiment of FIGS. 1 and 2, a case where a total of 8 air flow means 40 are installed is exemplified. In the case of the embodiment of FIG. 11, a case in which a total of six air flow means 40 are installed as a modified example is exemplified.

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

More specifically, the connecting frame part 30 includes a plurality of upper first connecting frames 31 arranged to connect the outer side 10a of the main body part 10 and the inner side 20a of the outer body part 20. -1), the plurality of second connecting frames 32 connecting the adjacent upper first connecting frames 31-1, the outer side 10a of the main body 10 and the outer body 20 It is arranged to connect the inner side 20a and is configured to include a plurality of lower first connecting frames 31-2 arranged to have a gap under the upper first connecting frame 31-1.

For example, the air flow means 40 is installed based on the lower first connection frame 31-2.

Through this configuration, in the aircraft F of this embodiment, since the air flow means 40 is not directly exposed to the side through the outer body 20, the aircraft F is a building in which a fire has occurred for the purpose of rescue. The propeller 46 of the air flow means 40 collides with the wall of a building or the like during flight or floating close to a shipwreck or a shipwrecked person on the water to prevent damage or collision with the shipwrecked person.

In addition, since the flight vehicle (F) of this embodiment is not directly exposed to the upper or lower side through the connection frame portion 30, the air flow means 40 is not directly exposed to the building or building for the purpose of lifesaving. When entering the inside, the propeller 46 of the air flow means 40 collides with various structures protruding from the ceiling or wall of the building to prevent damage or the risk of colliding with a person. Reference numeral 11 is a landing leg of the aircraft F.

Preferably, the outer body portion 20 is configured to provide buoyancy so that the vehicle F can float on the water. Through this buoyancy structure, the aircraft F of this embodiment can be used for lifesaving purposes in close proximity to a victim on the water.

For example, the outer body part 20 at least partially includes a hollow element 21 and is configured to provide buoyancy by using air injected into the hollow element 21 (see FIG. 5A). . To this end, it is preferable that the outer body portion 20 is made of a lightweight synthetic resin material capable of an airtight structure so as to provide buoyancy. As a modified example, it is also possible to install an air tube for providing buoyancy inside the outer body part 20 .

As another example, the outer body portion 20 is at least partially made of a buoyant material 22 to provide buoyancy (see FIG. 5B). The buoyancy material 22 may be filled inside the outer body portion 20 . For example, as the buoyancy material 22, urethane foam used in a normal life jacket or life ring may be used, but is not limited thereto.

Since the outer body portion 20 of the aircraft F of this embodiment is configured to form a ring shape surrounding the outside of the body portion 10, it stably provides a floating state on the water of the aircraft F, and through this, to the water It allows the survivors in the vehicle to easily access the vehicle (F).

7 is another 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.

Preferably, the aircraft F of this embodiment is configured to include a net 52 for falling objects. For example, the net 52 for falling objects may be used to move a person in a building to a safe point through a window in a state where the aircraft F is close to a building where a fire has occurred for the purpose of rescue. As another example, the net 52 for falling objects may be used for loading and transporting objects in a building.

To this end, a plurality of net frames 50 are installed along the outer edge of the upper side (U) of the connection frame unit 30 and extend upward.

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

Preferably, the aircraft (F) of this embodiment is configured to include a rescue net (54). For example, the rescue net 54 may be used for lifesaving purposes in which the aircraft F of the present embodiment is close to the victim on the water, lands on the water, and is rescued by holding the net when the victim floats.

To this end, a plurality of net frames 50 are installed along the periphery of the connection frame unit 30 and extend in an 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 part 20 . Preferably, the rescue net 54 is preferably formed in a shape having a width extending to the lower part of the aircraft F so as to facilitate grasping of the victim on the water.

Preferably, the aircraft F of this embodiment includes a net 52 for falling objects and a net 54 for rescue.

To this end, a plurality of net frames 50 are installed along the outer edge of the upper side (U) of the connection frame unit 30 and extend in the upper and outer directions (U and A1).

The net 52 for the falling objects is installed so that the rims 52a are coupled to the plurality of net frames 50 to receive the objects falling 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 part 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, each of the net frames 50 is each of the first It is installed on the outer side of the upper side (U) of the connecting frame (31).

Through this configuration, the aircraft F of the present embodiment approaches the victim on the water, lands on the water, and when floating, the survivor grasps the rescue net 54 and comes up to the upper side of the aircraft F, and the net 52 for falling objects You can rescue the person in distress by moving to a safe point while on board.

10 is a perspective view of a partial excerpt of an air vehicle according to an embodiment of the present invention.

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

To this end, the connection frame unit 30 includes a plurality of first connection frames 31 arranged to connect the outer side 10a of the main body unit 10 and the inner side 20a of the outer body unit 20, and , It is configured to include a plurality of second connecting frames 32 connecting adjacent first connecting frames 31.

In addition, the air flow means 40, the transverse support bar 42 extending to the left and right, respectively, from the middle portion of the first connecting frame 31, at both ends of the transverse support bar 42 It is configured to include motors 44 installed respectively, and propellers 46 installed on each of the motors 44. It is preferable that the transverse support rods 42 each extend symmetrically to the left and right sides with the same length.

For example, the lateral support bar 42 can be rotated to one side (R1) or the other side (R2) by means of rotation, and one side (R1) or the other side (R2) of the lateral support bar 42 It is configured to enable tilting control of the motor 44 and the propeller 46 by rotation of the motor 44 and the propeller 46. For example, the transverse support rod 42 is rotatably supported by a bearing 47 installed on the first connecting frame 31 for rotation of the transverse support rod 42 .

An operating lever 43 is provided on one side of the transverse support bar 42 as the pivoting means. For example, the operating lever 43 is exposed through one side of the first connection frame 31, and one end of the link element 45 may be connected to this portion.

The operating lever 43 is connected to the tilting control means 49 installed in the main body 10 through a link element 45 . The link element 45 may be configured in the form of a bar of a metal material, but is not limited thereto.

By operating and controlling the tilting control means 49 in the pulling direction D1 or pushing direction D2 of the link element 45, the transverse support bar 42 is moved to one side R1 or the other side R2. It is configured so that self-rotation takes place.

As an example, the aircraft F of FIGS. 1 and 2 has a total of eight motors 44 and a total of eight propellers 46 installed, and two motors 44 and two propellers 46 are one transverse A total of four air flow means 40 connected to the direction support rod 42 are provided and installed symmetrically.

As illustrated in Fig. 10, two air flow means 40 disposed oppositely at 180 degrees are controlled by one tilt control means 49, and another two air flow means 40 disposed orthogonally to these air flow means 40. The air flow means 40 is controlled by another tilting control means 49'.

For example, the tilting control unit 49 has a motor for tilting control installed therein, and includes a motor shaft 47b and a first link 47a connected to the motor shaft 47b. On both sides of the first link 47a, ends of two link elements 45 are connected to face each other, and the direction in which the link element 45 is pulled according to the rotation direction and rotation angle of the motor shaft 47b Operation control is performed in (D1) or in the pushing direction (D2), so that the air flow means 40 is controlled to tilt. Depending on the direction and angle at which the air flow unit 40 is tilted, the flight direction, speed, and flight height of the aircraft F may be controlled.

Figure 11 is another perspective view of the aircraft according to an embodiment of the present invention, Figure 12 is another bottom perspective view of the 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 an upper side of either the body part 10 or the connection frame part 30 .

The camera 60 is a known digital camera, and preferably may be a PTZ (Pan Tilt Zoom) camera capable of controlling a photographing angle.

The camera 60 executes a photographing operation under the control of the control unit 2, and remotely controls by photographing the on-site situation when the aircraft F is close to a building on fire or close to a victim on the water during lifesaving activities. An image is generated so that it can be wirelessly transmitted to the system 1000 .

Preferably, the flight vehicle (F) of this embodiment is installed on the upper side of any one of the body portion 10 or the connection frame portion 30 and the distance measuring sensor 62 disposed toward a preset one direction consists of including As a modified example, the distance measuring sensor 62 may be integrally installed in the camera 60 .

Various known sensors may be used as the distance measurement sensor 62, and for example, any one of an ultrasonic sensor, an infrared sensor, a LIDAR sensor, a radar sensor, or a camera sensor may be used. can be used An appropriate sensor may be selected in consideration of a required measurement distance and measurement environment.

The distance measurement sensor 62 performs distance measurement under the control of the control unit 2, and measures the proximity distance between the aircraft F and the building when the aircraft F of this embodiment approaches the building. The control unit 2 provides information for executing direction/speed control of the air flow means 40 so as to maintain a proximity distance to the air flow unit 40 at a required distance. As a modified example, information on the measured distance is transmitted to the remote control system 1000, control information for direction/speed control of the air flow means 40 is transmitted from the remote control system 1000, and the control unit 2 The direction/speed control of the air flow means 40 may be performed.

Preferably, the aircraft F of this embodiment is configured to include a warning light 90. The warning light 90 provides a function of notifying the surroundings of this state during the fire suppression operation of the aircraft F of this embodiment.

13 is a control configuration diagram of an air vehicle according to an embodiment of the present invention.

The aircraft F of this embodiment includes a control unit 2 and a communication unit 4, and although not shown, a charging and discharging battery for supplying power, a GPS module for obtaining flight location information, and an altitude sensor for obtaining flight altitude information. , and a gyro sensor for obtaining flight attitude information. The control unit 2 and the communication unit 4 may be installed in the body unit 10 .

The control unit 2 may be understood as a computing means including a CPU and a memory and running computer software for controlling an aircraft. The control unit 2 may wirelessly communicate with the remote control system 1000 through the communication unit 4, and receive various control information including flight control information from the remote control system 1000 or take pictures 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 controller 2 may execute direction/speed control of the air flow means 40 installed in the vehicle F based on a control logic preset in memory or a control command received from the remote control system 1000. .

In addition, the control unit 2 executes generation of image information using the camera 60 and generation of distance measurement information using the distance measurement sensor 62, and flight control or rescue operation control using each information. can run

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

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

10: body part
20: outer body
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 bar
43: operating lever
44: motor
45: link element
46: propeller
47: tilting control means
50: net frame
52: net for falling objects
54: rescue net
60: camera
62: distance measuring sensor
F: Aircraft
S: space between rings

Claims (14)

body part;
an outer body portion formed in a ring shape surrounding the outside of the body portion and disposed at a distance from the outside of the body portion;
a connection frame unit integrally coupled to the main body unit and the outer body unit and configured to enable air flow in a vertical direction;
It is symmetrically disposed in the ring-shaped space between the outer side of the main body and the inner side of the outer body, and is installed based on the connecting frame, and air introduced from the upper part is blown into the lower part using a propeller driven by a motor. a plurality of air flow means configured to be pressurized and discharged;
a plurality of net frames installed along the upper outer edge of the connection frame unit and extending in an upper outer direction;
A net for falling objects installed such that edges are coupled to the plurality of net frames to receive falling objects from above; and
A structural net coupled to the plurality of net frames and installed to form a ring shape surrounding an outer side surface of the outer body unit;
The connecting frame part,
A plurality of first connection frames arranged to connect the outside of the main body and the inside of the outer body;
It is configured to include a plurality of second connection frames connecting adjacent first connection frames,
Each of the net frames is an air vehicle having an outer body, characterized in that installed on the upper periphery of each of the first connection frame.
body part;
an outer body portion formed in a ring shape surrounding the outside of the body portion and disposed at a distance from the outside of the body portion;
a connection frame unit integrally coupled to the main body unit and the outer body unit and configured to enable air flow in a vertical direction; and
It is symmetrically disposed in the ring-shaped space between the outer side of the main body and the inner side of the outer body, and is installed based on the connecting frame, and air introduced from the upper part is blown into the lower part using a propeller driven by a motor. A plurality of air flow means configured to be pressurized and discharged;
The connecting frame part,
A plurality of upper first connecting frames arranged to connect the outside of the main body and the inside of the outer body;
A plurality of second connection frames connecting adjacent upper first connection frames;
It is configured to include a plurality of lower first connecting frames arranged to connect the outer side of the main body and the inner side of the outer body and arranged to have a gap under the upper first connecting frame,
The air flow means is an air vehicle having an outer body, characterized in that installed based on the lower first connection frame.
body part;
an outer body portion formed in a ring shape surrounding the outside of the body portion and disposed at a distance from the outside of the body portion;
a connection frame unit integrally coupled to the main body unit and the outer body unit and configured to enable air flow in a vertical direction; and
It is symmetrically disposed in the ring-shaped space between the outer side of the main body and the inner side of the outer body, and is installed based on the connecting frame, and air introduced from the upper part is blown into the lower part using a propeller driven by a motor. A plurality of air flow means configured to be pressurized and discharged;
The connecting frame part,
A plurality of first connection frames arranged to connect the outside of the main body and the inside of the outer body;
It is configured to include a plurality of second connection frames connecting adjacent first connection frames,
The air flow means,
Transverse support rods extending to the left and right sides from the middle of the first connecting frame, respectively;
Motors installed at both ends of the transverse support rod, respectively;
An air vehicle having an outer body, characterized in that configured to include a propeller installed on each of the motors.
According to any one of claims 1 to 3,
The outer body part is configured to provide buoyancy so that the aircraft can float on the water.
According to claim 4,
The outer body portion at least partially includes a hollow element and is capable of providing buoyancy using air injected into the hollow element.
According to claim 4,
The outer body portion is at least partially composed of a buoyancy material and is capable of providing buoyancy.
According to any one of claims 1 to 3,
a plurality of net frames installed along the upper periphery of the connection frame unit and extending upward; and
An air vehicle having an outer body, characterized in that it is configured to further include; a net for falling objects installed to receive falling objects from above by having edges coupled to the plurality of net frames.
According to any one of claims 1 to 3,
a plurality of net frames installed along the periphery of the connecting frame unit and extending outward; and
An air vehicle with an outer body, characterized in that it is configured to further include; a structural net coupled to the plurality of net frames and installed to form a ring shape surrounding the outer side of the outer body.
delete delete According to claim 3,
The transverse support rod can be rotated to one side or the other side by a rotation means, and the motor and the propeller are configured to control tilting of the motor and the propeller by rotating the transverse support rod to one side or the other side. An aircraft with body parts.
According to claim 11,
One side of the transverse support rod is provided with an operating lever as the pivoting means,
The operating lever is connected to the tilting control means installed in the main body through a link element,
An air vehicle having an outer body, characterized in that the transverse support bar is configured to rotate to one side or the other side by operating and controlling the tilting control unit in a pulling direction or a pushing direction of the link element.
According to any one of claims 1 to 3,
An aircraft with an outer body, characterized in that it is configured to further include; a camera installed on the upper side of any one of the main body and the connection frame.
According to claim 13,
An air vehicle with an outer body part, characterized in that it is configured to further include; a distance measuring sensor installed on the upper side of any one of the main body part and the connection frame part and disposed toward one predetermined direction.

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