KR102563256B1 - Aircraft with a separate and detachable boarding space - Google Patents

Abstract

The present invention relates to an aircraft having a boarding space capable of separation and separation.
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. The type air flow means is symmetrically arranged to reduce the risk of safety accidents due to exposure of propellers, and a boarding space capable of separation and separation is provided so that occupants can escape safely in the event of a safety accident. An air vehicle having a boarding space is disclosed.

Description

Aircraft with a boarding space capable of separation and detachment {Aircraft with a separate and detachable boarding space}

The present invention relates to an aircraft having a boarding space capable of separation and detachment, and more particularly, a main body part and an outer body part forming a ring shape surrounding the outside are coupled through a connecting frame part, and the outer part of the main body part and the inner part of the outer body part are connected. A plurality of motor-driven air flow means are symmetrically arranged in the space between the ring shapes to reduce the risk of a safety accident due to exposure of the propeller, and a boarding space capable of separation and separation is provided to prevent safety accidents in the event of a safety accident. It relates to an aircraft having a boarding space capable of separation and separation configured to allow occupants to escape safely.

Various types of drone-type air vehicles capable of flying equipped with rotary blades such as propellers have been proposed. A drone-type air vehicle was initially proposed mainly for use as an unmanned air vehicle, but recently, an air vehicle for boarding has also been proposed.

As an example of the prior art, Republic of Korea Patent Registration No. 10-2033248 (registered on October 10, 2019) relates to a rescue drone and a system including the same, which is disposed on both sides of the main body and generates thrust for aerial flight. And, a configuration including a wearing device disposed at the lower end of the main body and worn by the victim to board the drone, and a shock absorber disposed at the lower end of the wearing device and absorbing shock during landing has been proposed.

As another example of the prior art, Republic of Korea Registered Patent No. 10-2233066 (registered on March 23, 2021) relates to a drone-type aircraft body having an interior space for a person to board; a plurality of arm parts configured to be connected to the aircraft body in a symmetrical form; a propeller configured at the front end of the arm portion to rotate at high speed; A configuration including auxiliary wings configured on both sides of the aircraft body was proposed.

However, since the above-described conventional air vehicles have rotary blades such as propellers exposed in a direction accessible to occupants, there is a limitation in that they are vulnerable to safety accidents.

In addition, the conventional aircraft as described above has a limitation in that it does not provide a safety means for occupants to safely escape from the aircraft in the event of a failure of a major part such as a propeller.

Korean Registered Patent No. 10-2033248 (registered on October 10, 2019) Korean Registered Patent No. 10-2233066 (registered on March 23, 2021)

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 the space to reduce the risk of a safety accident due to exposure of the propeller, and a boarding space that can be separated and separated is provided so that the occupant can escape safely in the event of a safety accident. It is an object of the present invention to provide an air vehicle having a boarding space capable of separation and detachment configured to do so.

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; 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; and an upper body portion coupled to an upper portion of the main body portion, capable of being separable from the main body portion in an upward direction, and capable of being boarded by a person.

Preferably, a parachute for the upper body is installed on the upper side of the upper body, and the upper body is configured to be separated and separated from the body in an upward direction by air resistance force received by the unfolding of the parachute for the upper body.

Preferably, a plurality of parachutes for the main body are symmetrically installed on the upper side of the main body, and the parachute for the main body is configured to unfold after the opening time of the parachute for the upper body.

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

The present invention as described above has the advantage of providing an aircraft configured to reduce the risk of safety accidents due to exposure of propellers and to enable safe escape of occupants in the event of a safety accident by providing a boarding space capable of separation and separation.

In addition, the present invention has the advantage that the parachute for the upper body can be separated from the main body in an upward direction and a parachute for the upper body is installed on the upper body on which a person can ride, so that the upper body can be easily separated from the main body and fall safely.

In addition, the present invention has the advantage that a plurality of parachutes for the main body are symmetrically installed on the upper side of the main body so that the main body can fall safely.

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 a partial cross-sectional view of an air vehicle according to an embodiment of the present invention;
7 is a perspective view of an air vehicle 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 a perspective view of a partial excerpt of an air vehicle according to an embodiment of the present invention;
10 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 element from another element. 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 6 is a partial cross-sectional view of an aircraft according to an embodiment of the present invention, Figure 7 is a perspective view of an aircraft according to an embodiment of the present invention, Figure 8 is a flight vehicle according to an embodiment of the present invention It is another perspective view.

The aircraft F of this embodiment is configured to be usable for passenger use, including an upper body portion 70 on which a person can ride.

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. It is good to be made of a synthetic resin material having sufficient strength so that a person can ride.

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. The installed number of air flow means 40 may be changed.

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 passengers of the aircraft F may be exposed to the side of the propeller. Reduce the risk of possible safety accidents.

In addition, in the aircraft F of this embodiment, since the air flow means 40 is not directly exposed to the upper or lower side through the connection frame portion 30, the passengers of the aircraft F are on the upper or lower surface of the propeller. Reduce the risk of safety accidents that may occur due to exposure. Reference numeral 11 is a landing leg of the aircraft F.

The aircraft F of this embodiment is coupled to the upper side of the body portion 10, and includes an upper body portion 70 that can be separated and separated from the body portion 10 in the upper (U) direction and can be boarded by a person. It is composed by

Referring to FIGS. 6 and 7, a person can ride inside the upper body portion 70 configured in a substantially disk shape, and the lower part of the upper body portion 70 is in the coupling space portion 10-1 of the body portion 10. An approximately cylindrical assembly portion 70-1 for insertion and coupling is formed extending downward.

For example, the coupling space portion 10-1 of the main body portion 10 is formed in a hollow cylindrical shape, and the cylindrical coupling body portion 70-1 formed in the lower portion of the upper body portion 70 is inserted into it. Thus, a docked coupled state is achieved.

In this way, through the structure in which the cylindrical assembly part 70-1 formed in the lower part of the upper body part 70 is inserted and coupled through the upper opening of the coupling space part 10-1 of the main body part 10, the present The upper body portion 70 of the aircraft (F) of the embodiment is capable of separation and separation from the body portion 10 in the upper (U) direction. Through this separation and separation structure, it is possible to escape from the body portion 10 by separation of the upper body portion 70 itself on which the person boarded even if a person does not directly take an escape operation when an abnormality of the aircraft F occurs.

The separation and detachment structure, if the upper body portion 70 can be separated and separated from the body portion 10 in the upper (U) direction, does not necessarily have to be configured in a cylindrical shape, and other configurations (eg, polygonal cylindrical shape, conical shape) , polygonal cone shape, rod shape, etc.)

Since it is difficult for a general occupant to use a parachute, the escape structure as described above is advantageous in providing safety to occupants. In particular, when a shock absorbing means such as an airbag is installed inside the upper body portion 70, there is an advantage in preventing the impact from landing on the upper body portion 70 from directly reaching the occupant.

In addition, since the upper body part 70 is separated and separated in the upper (U) direction of the body part 10, a natural and quick separation and separation operation can be provided in conjunction with the upper body parachute 82 to be described later.

Preferably, a coupling release unit 502 driven on/off by the upper body separation control unit 500 is provided on the inner surface of the hollow cylindrical shape of the coupling space 10-1 of the body unit 10. It can be. For example, the coupling release means 502 may be configured in the form of a protruding piece that is driven forward/backward (S1-S2) by a driving means such as a hydraulic or pneumatic cylinder or a motor, and the coupling body portion 70 of the upper body portion 70 -1) It can be inserted into the concave portion 70-3 formed on the side surface to form a coupled state, or can be retreated from the concave portion 70-3 to release the coupled state. Of course, the coupling release means 502 can be modified and configured with various known means.

For example, when the controller 2 of the aircraft F detects the fall of the aircraft F from the fall detection sensor 402, it controls the upper body separation control means 500 so that the coupling release means 502 is coupled. Control to release the locked state.

The air vehicle F of this embodiment is provided with a parachute to prevent human life/property loss at the crash site and occupant's life accident caused by a fall when the air flow means 40 malfunctions.

To this end, a parachute 82 for the upper body 70 is installed on the upper side of the upper body 70, and the upper body 70 is affected by the air resistance AF received when the parachute 82 for the upper body 70 is unfolded. It may be configured to be separated and separated from (10) in the upper (U) direction (see FIG. 7).

For example, when an abnormality occurs in the aircraft F, the parachute 82 for the upper body part installed on the upper side of the upper body part 70 is launched upward from the storage space 70-2 by the trigger means AP and unfolds. , The upper body portion 70 is separated and separated from the body portion 10 in the upward (U) direction by the air resistance force (AF) received by the unfolded upper body parachute 82 .

The separated upper body part 70 can land safely through the upper body parachute 82, and through this, a person riding on the upper body part 70 can safely land.

The trigger means (AP) of the parachute 82 has various known means, and for example, the parachute 82 inside the storage space 70-2 is controlled by a spring mechanism controlled on / off by the parachute control means 400 The parachute expands while being launched upward, or compressed air is instantaneously supplied to the inside of the parachute 82 in the storage space 70-2 by the compressed air supply unit controlled on/off by the parachute control unit 400. The deployment of the parachute can be achieved in such a way that the upper portion is deployed.

For example, when the controller 2 of the aircraft F detects the fall of the aircraft F from the fall detection sensor 402, it controls the parachute control means 400 so that the trigger means AP is the parachute 82 is fired upward from the storage space 70-2 and controlled to unfold. As described above, this control may be performed together with the coupling release operation of the coupling release unit 502 under the control of the upper body separation control unit 500 .

Accordingly, the upper body portion 70 is separated and separated from the body portion 10 in the upper (U) direction by the air resistance force (AF) received when the parachute 82 for the upper body portion is unfolded.

In addition, a plurality of parachutes 84 for the body portion are symmetrically installed on the upper side of the body portion 10, and the parachute for the body portion 84 is configured to unfold after the point at which the parachute for the upper body portion 82 is deployed. do.

Since the body part 10 includes a driving means such as a motor and a propeller and a frame, it has a larger load than the upper body part 70, so it is necessary to install a plurality of parachutes instead of one parachute, and also to ensure a stable fall. It is preferable that a plurality of parachutes are installed symmetrically.

In the illustrated example, a total of three parachutes 84 for the main body are installed, but are not necessarily limited thereto.

The trigger means (AP) and the expansion control configuration of the parachute 84 for the body part may be configured the same or similar to those of the parachute 82 for the upper body part.

However, for smooth separation and detachment of the upper body 70, the parachute 84 for the main body is separated and separated from the main body 10 in the upper (U) direction as the parachute 82 for the upper body is unfolded. Since it is preferable to unfold later, it is preferable that the trigger means (AP) of the parachute 84 for the body part is configured to operate after a predetermined time after the trigger means (AP) of the parachute 82 for the upper body part operates. do. Such control may be performed by logic preset in the control unit 2 . A separate trigger control unit (not shown) connected to the control unit 2 may be installed on the upper body 70 or the main body 10 to set a time difference between the operation of the trigger means AP. Reference numeral 10-2 denotes a storage space for the parachute 84 for the main body.

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.

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 pick up or drop off passengers on the water, or it can land on the water in an emergency to prevent safety accidents.

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 20 of the aircraft (F) of this embodiment is configured to form a ring shape surrounding the outside of the main body 10, it is possible to stably provide the floating state of the aircraft (F).

9 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. 9, 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.

10 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, receive various control information including flight control information from the remote control system 1000, or use the camera 60 Image information captured by the camera, distance measurement information measured by the distance measurement sensor 62, flight position information and flight attitude information, crash accident related information, parachute control information, and the like 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 vehicle F based on a control logic preset in the memory or a control command received from the remote control system 1000, , Operation control of the parachute control unit 400 and operation control of the upper body separation control unit 500 may be executed based on the detected value of the fall detection sensor 402 .

In addition, the controller 2 may generate image information using the camera 60 and generate distance measurement information using the distance measurement sensor 62, and provide the information to a passenger or the remote control system 1000.

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 connecting 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
70: upper body
82: parachute for upper body
84: parachute for main body
F: Aircraft
S: space between rings

Claims (8)

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; and
An upper body portion coupled to an upper side of the body portion, capable of being separated from the body portion in an upward direction, and capable of being ridden by a person;
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 aircraft having a boarding space capable of separation and separation, characterized in that configured to include a propeller installed on each of the motors.
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; and
An upper body portion coupled to an upper side of the body portion, capable of being separated from the body portion in an upward direction, and capable of being ridden by a person;
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 aircraft having a boarding space capable of separation and detachment, characterized in that installed based on the lower first connection frame.
According to claim 1 or 2,
A parachute for the upper body is installed on the upper side of the upper body,
The upper body part has a boarding space capable of separation and separation, characterized in that configured to be separated and separated from the body part in an upward direction by the air resistance force received by the parachute for the upper body part.
According to claim 3,
A plurality of parachutes for the main body are symmetrically installed on the upper side of the main body,
The parachute for the body part is configured to unfold after the point at which the parachute for the upper body part is deployed.
According to claim 1,
The transverse support rod 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 rod to one side or the other side Separation, characterized in that An aircraft with boarding space capable of ejection.
According to claim 5,
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 aircraft having a boarding space capable of separation and detachment, characterized in that the transverse support rod is configured to rotate to one side or the other side by the tilting control unit manipulating and controlling the link element in a pulling direction or a pushing direction. .
delete According to claim 1 or 2,
The outer body portion is configured to provide buoyancy so that the aircraft can float on the water.

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