KR20220141959A - Aircraft with outer body - Google Patents

Abstract

The present invention relates to an aircraft provided with an outer body part. According to an embodiment of the present invention, a main body part and an outer body part forming a ring shape surrounding the outside of the main body part are coupled through a connection frame part, and a plurality of motor-driven air flow means are 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 so that risk of accidents due to propeller exposure can be reduced and various additional functions using the outer body part can be provided.

Description

Aircraft with outer body

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

It is possible to fly by having a rotating blade such as a propeller, and in particular, unmanned aerial vehicles that are configured to float on water and provide various additional functions have been proposed.

As an example of the prior art, Republic of Korea Patent Registration No. 10-2049599 (registered on November 21, 2019) relates to a drone for marine monitoring. After landing, it is possible to move horizontally at sea level, so a drone capable of inspecting various marine environments was proposed.

As another example of the prior art, Republic of Korea Patent Registration No. 10-188975 (registered on August 30, 2019) relates to a hand-held drone for measuring river radiation and a control method thereof, In order to selectively travel on water, a configuration related to an autonomous vehicle having a propeller for flight generating lift and a floating body floating on the water surface was proposed.

However, the conventional unmanned aerial vehicle as described above has a limitation in that it may be exposed to a safety accident when it comes close to a monitoring or measurement object while moving because a rotating blade such as a propeller is exposed to the outside. In addition, there was a limit in providing various additional functions by the exposed structure of the rotary blade.

Republic of Korea Patent Registration 10-2049599 (Registered on November 21, 2019) Republic of Korea Patent Registration 10-2018975 (Registered on August 30, 2019)

The present invention has been devised in view of the above problems, wherein the main body and the outer body portion forming a ring shape surrounding the outer side are coupled through the connecting frame portion, and between the outer body portion and the ring shape formed by the inner side of the outer body portion A plurality of motor-driven air flow means are symmetrically arranged in space to reduce the risk of a safety accident due to exposure of the propeller and to provide an aircraft having an outer body portion configured to provide various additional functions using the outer body portion 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 outer side of the main body portion and disposed in a state of having a gap from the outer side of the main body portion; a connecting frame unit configured to connect and integrally combine the main body and the outer body and allow air to flow in a vertical direction; and a ring-shaped space formed between the outer side of the main body and the inner side of the outer body, installed based on the connecting frame, and using a propeller driven by a motor, the air introduced from the upper portion of the lower portion A plurality of air flow means configured to be discharged under pressure; is disclosed an aircraft configured to include.

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

Preferably, the outer body part at least partially includes a hollow element, and it is possible to provide buoyancy by using air injected into the hollow element.

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

Preferably, the present invention includes a plurality of net frames installed along the upper periphery of the connection frame part and formed to extend upwards; And it is configured to further include a; and a rim is coupled to the plurality of net frames for a falling object installed to receive a falling object falling from the top.

Preferably, the present invention includes a plurality of net frames installed along the periphery of the connection frame portion and formed to extend outwardly; and 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 part.

Preferably, the present invention includes a plurality of net frames installed along the upper periphery of the connection frame part and extending in an upper outer direction; a net for falling objects installed so as to receive a falling object falling from an upper portion by coupling an edge to the plurality of net frames; and 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 part.

Preferably, the connection frame part includes a plurality of first connection frames arranged to connect the outside of the main body and the inside of the outer body part, and a plurality of second connection frames that connect the adjacent first connection frames. and each of the net frames is installed outside the upper side of each of the first connection frames.

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

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

Preferably, the transverse support bar can be rotated to one side or the other side by a rotation means, and tilting control of the motor and the propeller is possible by rotation of the transverse support bar to one side or the other side.

Preferably, a lever for operation is provided on one side of the lateral support rod as the rotation means, and the lever for operation 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 rod is configured to rotate to one side or the other side by operating and controlling the element in a pulling direction or a pushing direction.

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

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

According to the present invention as described above, the body part and the outer body part forming a ring shape surrounding the outer side are coupled through the connection frame part, and a plurality of motor-driven type in the space between the ring shape formed between the outer side of the main body part and the inner part of the outer body part. Since the air flow means is symmetrically disposed, there is an advantage in that the risk of a safety accident due to exposure of the propeller is reduced and various additional functions using the outer body part are provided.

1 is a perspective view of an aircraft according to an embodiment of the present invention;
Figure 2 is a bottom direction perspective view 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;
5A is a partial cross-sectional perspective view of an aircraft according to an embodiment of the present invention;
5B is another partial cross-sectional perspective view of an aircraft 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 aircraft 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 partially excerpted perspective view of an aircraft according to an embodiment of the present invention;
11 is another perspective view of an aircraft according to an embodiment of the present invention;
12 is another bottom-direction perspective view of an aircraft according to an embodiment of the present invention;
13 is a control configuration diagram of an aircraft according to an embodiment of the present invention.

The present invention may be embodied in various other forms without departing from its technical spirit or main characteristics. Accordingly, the embodiments of the present invention are merely illustrative in all respects and should not be construed as limiting.

The terms 1st, 2nd, etc. are used only for the purpose of distinguishing one component from another component. For example, without departing from the scope of the present invention, a first component may be referred to as a second component, and similarly, a second component may also be referred to as a first component.

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 another component may exist in between.

As used herein, the singular expression includes the plural expression unless the context clearly dictates otherwise. In the present application, terms such as "comprises" or "comprising", "have" and the like are intended to represent the presence of elements or combinations thereof described in the specification, and the possibility that other elements or features may be present or added. It is not precluded.

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

Figure 1 is a perspective view of an aircraft according to an embodiment of the present invention, Figure 2 is a bottom direction 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, Figure 4 is of the present invention A bottom view of an aircraft according to an embodiment, FIG. 5A is a partial sectional perspective view of the aircraft according to an embodiment of the present invention, FIG. 5B is another partial sectional perspective view of an aircraft according to an embodiment of the present invention, FIG. 6 is an embodiment of the present invention Another perspective view of an aircraft according to an example.

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

In the aircraft (F) of this embodiment, the main body portion 10 and the outer body portion 20 forming a ring shape surrounding the outer side are coupled through the connection frame portion 30 . Preferably, the body portion 10, the outer body portion 20 and the connecting frame portion 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 described below. It is preferable to be made of a synthetic resin material having sufficient strength so that the net 52 for falling objects and the net 54 for structure 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 main body portion 10 and is disposed to have a gap with the outer side 10a of the main body portion 10 .

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

The plurality of air flow means 40 are symmetrically disposed in the ring-shaped interspace S formed between the outer side 10a of the main body 10 and the inner 20a of the outer body 20 . 1 and 2, a case in which a total of eight air flow means 40 are installed is illustrated. 11, a case in which a total of six air flow means 40 are installed as a modification is illustrated.

The plurality of air flow means 40 is installed based on the connection frame part 30, and is configured so that the air introduced from the upper part is pressurized and discharged to the lower part using the propeller 46 driven by the motor 44. .

In more detail, the connection frame unit 30 includes a plurality of upper first connection frames 31 arranged to connect the outer side 10a of the main body 10 and the inner side 20a of the outer body unit 20 . -1), a plurality of second connection frames 32 connecting the adjacent upper first connection frames 31-1, and the outer portion 10a of the main body 10 and the outer body portion 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 at the lower portion of 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 portion 20, the aircraft (F) is a building in which a fire has occurred for the purpose of rescue, etc. The propeller 46 of the air flow means 40 collides with a wall of a building or the like when flying or floating in proximity to or close to a person in water to prevent damage or a risk of colliding with a person in distress.

In addition, in the aircraft (F) of this embodiment, the air flow means 40 through the connection frame part 30 is not directly exposed to the upper side or the lower side, so the aircraft (F) is close to the building for the purpose of saving lives or the building When entering the interior, 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 denotes a landing leg of the aircraft (F).

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

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

As another example, the outer body part 20 is at least partially composed of the buoyancy material 22 to provide buoyancy (refer to FIG. 5B ). The buoyancy material 22 may be filled in the outer body part 20 . For example, as the buoyancy material 22, a urethane foam used in a conventional 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 main body portion 10, it provides a stable floating state of the aircraft (F), and through this, Make it easy for the survivors to access the aircraft (F).

7 is another perspective view of an aircraft according to an embodiment of the present invention, FIG. 8 is another perspective view of an aircraft according to an embodiment of the present invention, and FIG. 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. As an example, the net 52 for a falling object may be used to move a person in a building through a window in a state in which the flying vehicle F is close to a building where a fire has occurred for the purpose of rescue and the like to move to a safe point. 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 upper side (U) periphery of the connection frame unit 30 and are formed to extend upwards.

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

Preferably, the vehicle (F) of this embodiment is configured to include a rescue net (54). As an example, the rescue net 54 may be used for lifesaving purposes in which the aircraft F of this embodiment is rescued by gripping the net when the aircraft F of this embodiment approaches the survivors on the water and is floating on the water.

To this end, a plurality of net frames 50 are installed along the periphery of the connection frame part 30 and are formed to 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 surface of the outer body portion 20 . Preferably, the structural net 54 is preferably formed in a shape having a width extending to the lower portion of the aircraft (F) to facilitate the grip of the survivors on the water.

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

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

The net 52 for the falling object is installed so that the edge 52a is coupled to the plurality of net frames 50 to receive the falling object 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 surface of the outer body portion 20 .

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

Through this configuration, the aircraft (F) of this embodiment comes up to the upper side of the aircraft (F) by grasping the rescue net 54 when floating and approaching the shipwreck on the water and landing on the water, and the falling object net 52 You can rescue the survivors by moving to a safe spot while riding on top.

10 is a partially extracted perspective view of an aircraft 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 connecting frame unit 30 includes a plurality of first connecting frames 31 arranged to connect the outer side 10a of the main body 10 and the inner side 20a of the outer body unit 20 , and , is configured to include a plurality of second connection frames 32 connecting the adjacent first connection frames 31 .

In addition, the air flow means 40, the transverse support rods 42 respectively extending to the left and right from the middle position of the first connection frame 31, and the transverse support rods 42 at both ends of the It is configured to include a motor 44 installed in each, and a propeller 46 installed in each of the motors 44 . It is preferable that the lateral support rods 42 extend symmetrically to the left and the right with the same length, respectively.

As an example, the transverse support bar 42 can rotate 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 the propeller 46 by the rotation of the motor. For example, for the rotation of the transverse support bar 42 , the transverse support bar 42 is rotatably supported by a bearing 47 installed in the first connection frame 31 .

A lever 43 for operation is provided on one side of the transverse support rod 42 as the rotation means. For example, the lever 43 for operation 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 operation lever 43 is connected to the tilting control means 49 installed in the body portion 10 through a link element 45 . The link element 45 may be configured in the form of a bar made of a metal material, but is not limited thereto.

By operating and controlling the tilting control means 49 in the pulling direction (D1) or the pushing direction (D2) of the link element 45, the lateral support rod 42 is moved to one side (R1) or the other side (R2). It is configured to be rotated.

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 lateral A total of four air flow means 40 connected to the direction support rod 42 are provided and are symmetrically installed.

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

For example, the tilting control means 49 includes a tilting control motor 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, the ends of the two link elements 45 are connected and installed to face each other, and the link element 45 is pulled according to the rotation direction and the rotation angle of the motor shaft 47b. (D1) or the operation control is made in the pushing direction (D2), the air flow means 40 is controlled to tilt. Depending on the direction and angle in which the air flow means 40 is tilted, the flight direction and speed of the aircraft F, and the flight height may be controlled.

Figure 11 is another perspective view of the vehicle according to an embodiment of the present invention, Figure 12 is another bottom direction perspective view of the vehicle according to an embodiment of the present invention.

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

The camera 60 is installed on the upper side of any one of the body part 10 or the connection frame part 30 .

The camera 60 may be a well-known digital camera, preferably a PTZ (Pan Tilt Zoom) camera capable of controlling a shooting angle.

The camera 60 executes a shooting operation under the control of the control unit 2, and the aircraft F is close to a building where a fire has occurred or is in close proximity to a person in distress on water to take a picture of the on-site situation during lifesaving activities and remotely control it An image is generated so that it can be wirelessly transmitted to the system 1000 .

Preferably, the aircraft (F) of this embodiment is installed on the upper side of any one of the main body part 10 or the connection frame part 30 and a distance measuring sensor 62 disposed toward a preset one side direction. consists of including As a modification, the distance measuring sensor 62 may be integrally installed with the camera 60 .

The distance measuring sensor 62 may be a variety of known sensors, for example, any one of an ultrasonic sensor, an infrared sensor, a LIDAR sensor, a radar (RADAR) sensor, or a camera sensor (Passive Sensor) can be used An appropriate sensor may be selected in consideration of a required measuring distance and a measuring environment.

The distance measurement sensor 62 executes distance measurement under the control of the controller 2, and measures the proximity distance to the building when the aircraft F of this embodiment approaches the building, and the vehicle F and the building The control unit 2 provides information for executing direction/speed control of the air flow means 40 so as to maintain the proximity distance with the sieve at the required distance. As a modification, the control unit 2 by transmitting information about the measured distance to the remote control system 1000 and receiving control information for controlling the direction/speed of the air flow means 40 from the remote control system 1000 It is also possible to perform direction/speed control of the false air flow means 40 .

Preferably, the vehicle (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 when the aircraft F of this embodiment operates in a fire suppression operation.

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

The vehicle F of this embodiment includes a control unit 2 and a communication unit 4, and although not shown, a charging/discharging battery for power supply, 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 may be provided. The control unit 2 and the communication unit 4 may be installed in the body unit 10 .

The control unit 2 includes a CPU and a memory and may be understood as a computing means in which computer software for vehicle control is driven. The control unit 2 may wirelessly communicate 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 photographed with a camera. Image information, distance measurement information, flight location information, flight attitude information, etc. may be transmitted to the remote control system 1000 .

In addition, the control unit 2 may execute direction/speed control of the air flow means 40 installed in the aircraft F based on control logic preset in the 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, generation of distance measurement information using the distance measurement sensor 62, and controls flight or rescue operation using each information. can run

For example, the remote control system 1000 may be a computing means in which computer software for vehicle control/monitoring is driven and wireless information transmission and reception is possible.

Although the present invention has been described mainly in terms of preferred embodiments with reference to the accompanying drawings, it will be apparent to those skilled in the art that many various and obvious modifications can be made therefrom without departing from the scope of the present invention. Accordingly, the scope of the present invention should be construed by the appended claims to cover many such modifications.

10: body part
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 bar
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
60: camera
62: distance measuring sensor
F: aircraft
S: Ring-shaped interspace

Claims (14)

body part;
an outer body portion formed in a ring shape surrounding the outer side of the main body portion and disposed in a state of having a gap from the outer side of the main body portion;
a connecting frame unit configured to connect and integrally combine the main body and the outer body and allow air to flow in a vertical direction; and
It is symmetrically disposed in the ring-shaped space formed between the outer side of the main body and the inner side of the outer body portion, is installed based on the connection frame portion, and uses a propeller driven by a motor to allow air introduced from the upper part to the lower part. A plurality of air flow means configured to be discharged under pressure; an aircraft having an outer body portion configured to include.
According to claim 1,
The outer body portion is an aircraft having an outer body portion, characterized in that configured to provide buoyancy so that the aircraft can float on water.
3. The method of claim 2,
The enclosure part at least partially includes a hollow element, and an air vehicle having an enclosure part, characterized in that it is possible to provide buoyancy by using air injected into the hollow element.
3. The method of claim 2,
The outer body portion is at least partially composed of a buoyancy material to provide buoyancy.
According to claim 1,
a plurality of net frames installed along the upper periphery of the connection frame portion and formed to extend upwards; and
An air vehicle having an outer body part, characterized in that it further comprises a; a net for a falling object installed so as to receive a falling object falling from the upper portion by coupling an edge to the plurality of net frames.
According to claim 1,
a plurality of net frames installed along the periphery of the connection frame part and formed to extend outward; and
The aircraft having an outer body part, characterized in that it further comprises; a structural net coupled to the plurality of net frames and installed to form a ring shape surrounding the outer side surface of the outer body part.
According to claim 1,
a plurality of net frames installed along the upper periphery of the connection frame part and extending in an upper outer direction;
a net for falling objects installed so as to receive a falling object falling from an upper portion by coupling an edge to the plurality of net frames; and
The aircraft having an outer body part, characterized in that it further comprises; a structural net coupled to the plurality of net frames and installed to form a ring shape surrounding the outer side surface of the outer body part.
8. The method of claim 7,
The connecting frame portion,
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 the adjacent first connection frames,
Each of the net frames is an aircraft having an outer body portion, characterized in that installed on the upper outer periphery of each of the first connection frame.
According to claim 1,
The connecting frame portion,
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 the adjacent upper first connection frames;
It is arranged to connect the outer side of the main body and the inner side of the outer body portion and is configured to include a plurality of lower first connecting frames arranged to have a gap in the lower portion of the upper first connecting frame,
The air flow means is an aircraft having an outer body, characterized in that it is installed based on the lower first connection frame.
According to claim 1,
The connecting frame portion,
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 the adjacent first connection frames,
The air flow means,
and transverse support rods respectively extending to the left and right from the middle position of the first connection frame;
a motor installed at both ends of the transverse support rod, respectively;
Aircraft having an outer body part, characterized in that it comprises a propeller installed in each of the motors.
11. The method of claim 10,
The transverse support bar can be rotated to one side or the other side by a rotation means, and the tilting control of the motor and the propeller is possible by rotation of the transverse support bar to one side or the other side. Aircraft with body parts.
12. The method of claim 11,
A lever for operation is provided on one side of the transverse support bar as the rotation means,
The operation lever is connected to the tilting control means installed in the main body through a link element,
An aircraft having an outer body, characterized in that the tilting control means is configured to rotate the lateral support rod to one side or the other side by operating and controlling the link element in a pulling direction or a pushing direction.
According to claim 1,
An aircraft having an outer body part, characterized in that it further comprises; a camera installed on the upper side of any one of the main body part or the connection frame part.
14. The method of claim 13,
Aircraft for fire suppression, characterized in that it further comprises; a distance measuring sensor installed in the upper side of any one of the main body portion or the connection frame portion and arranged toward a preset one side direction.

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