KR102678897B1 - Electric vertical take-off and landing drone - Google Patents

Abstract

The present invention relates to a main body; a left wing frame protruding outward on the left side of the main body; A left boom provided at the end of the left wing frame and having a major axis length on the front and rear sides; A left wing protruding outside the left boom; A right wing frame protruding outward on the right side of the main body; A right boom provided at the end of the right wing frame and having a major axis length on the front and rear sides; A right wing protruding outside the right boom; and a plurality of thrust units provided on each of the left and right booms and capable of generating thrust in the forward and vertical directions of the main body, respectively.

Description

Drone Taxi{ELECTRIC VERTICAL TAKE-OFF AND LANDING DRONE}

The present invention relates to a drone taxi (eVTOL) capable of vertical takeoff and landing.

More specifically, left and right thrust means that enable thrust generation in the forward direction are provided at the tip of each of the left and right booms, and left and right lifting means that enable thrust generation in the vertical direction are provided on one left side. By being provided on each of the boom and the right boom, when the propellers of the left and right thrust means provided on the front end rotate, lift is generated over the left and right wings provided on the rear of the left and right thrust means, ensuring the stability of transition flight. It's about drone taxis that can do it.

Unmanned aerial vehicles come in various forms depending on the purpose of use, such as rotary wing and fixed wing.

A rotary wing UAV is an unmanned aerial vehicle capable of vertical takeoff and landing by generating lift through multiple rotors, and has the advantage of being easy to control the aircraft's attitude. On the other hand, rotary wing unmanned aerial vehicles have a short operating time, and their operating speed is relatively slow compared to fixed wing unmanned aerial vehicles. In addition, the rotor must be maintained in a constant rotation state to maintain operation.

Fixed-wing UAVs generate lift using the wings of a typical aircraft, and are equipped with a control panel that can rotate up and down at the rear of the wings to control the attitude of the UAV during flight. However, unlike rotary-wing aircraft, fixed-wing UAVs are capable of taking off and landing. Since a certain glide distance is required for takeoff and landing, there are restrictions on operations for takeoff and landing.

Accordingly, in order to compensate for the shortcomings of fixed-wing UAVs, tilt-type UAVs capable of taking off and landing in the vertical direction have been developed and used.

A tilt-type vertical takeoff and landing drone is an unmanned aerial vehicle capable of moving forward and taking off and landing in the vertical direction by using the rotation of the rotor and the generation of lift by the wings. When taking off and landing in the vertical direction, the rotor is positioned so that it faces the vertical direction. Takeoff and landing can be performed through the thrust generated by this, and when moving in the forward direction, the rotor is positioned to face the forward direction (horizontal direction) and the thrust generated by this is used.

However, a tilt-type vertical takeoff and landing drone must change the position of the rotor by rotating it for forward thrust or vertical thrust, so a configuration for changing the rotor position must be added, and the resulting manufacturing cost and Not only does the manufacturing time increase, but there is a problem in ensuring the safety of operation of the unmanned aerial vehicle due to frequent accidents that occur when the rotor position changes.

Registered Patent Publication No. 10-1682670 (2016.11.29.)

The present invention was developed to solve the above problems, and the problem to be solved by the present invention is that left and right thrust means that enable thrust generation in the forward direction are provided at the front end of each of the left and right booms, and the vertical Left and right lifting means that enable thrust generation in each direction are provided on each of the left and right booms, so that when the propellers of the left and right thrust means provided at the front end rotate, the left and right thrust means are rearward. The goal is to provide a drone taxi that can secure the stability of transition flight by generating lift over the left and right wings.

In addition, another problem to be solved by the present invention is that one right boom is provided with a right thrust means and a pair of right lifting means capable of generating thrust in the forward and vertical directions, respectively, and one left boom is provided with a forward thrust means. As the left thrust means and a pair of left lift means are provided to generate thrust in each direction and the vertical direction, a pair of booms is equipped with six propellers consisting of rotors capable of generating thrust, so that the engine or mount The goal is to provide a drone taxi that can be manufactured by simplifying the configuration.

In addition, another problem to be solved by the present invention is that the left thrust means and the right thrust means for generating thrust in the forward direction are provided on the front end of the left boom and right boom, so that when the propeller rotates, the air flow sent to the rear causes the left thrust means to generate thrust in the forward direction. A flow is generated over the wing and right wing, and as a result, even if the speed of the drone taxi is low, lift is generated on the left wing and right wing by the left and right thrust means provided on the leading edge, which is very advantageous for low-speed flight and transition flight. The goal is to provide drone taxis.

In order to solve the above problems, the drone taxi according to the present invention includes a main body; A left wing frame protrudes outward on the left side of the main body; A left boom provided at the end of the left wing frame and having a major axis length on the front and rear sides; The left wing protrudes outward from the left boom; A right wing frame protrudes outward on the right side of the main body; A right boom provided at the end of the right wing frame and having a major axis length on the front and rear sides; The right wing protrudes outward from the right boom; and a plurality of thrust units provided on each of the right boom and left boom and capable of generating thrust in the forward and vertical directions of the main body, respectively. I want to solve it.

In the present invention, left and right thrust means that enable thrust generation in the forward direction are provided at the front end of each of the left and right booms, and left and right lifting means that enable thrust generation in the vertical direction are provided with one left boom and one left boom. By being provided on each right boom, when the propellers of the left and right thrust means provided on the front end rotate, lift is generated over the left and right wings provided on the rear of the left and right thrust means, so it is advantageous for low-speed flight and transition flight. This has a remarkable effect in ensuring stability.

In addition, the present invention is provided with a right thrust means and a pair of right lifting means capable of generating thrust in the forward and vertical directions on one right boom, respectively, and a pair of right lifting means on one left boom, respectively capable of generating thrust in the forward and vertical directions. By providing a left thrust means capable of generating thrust and a pair of left lifting means, a pair of booms is equipped with six propellers consisting of rotors capable of generating thrust, thereby simplifying the configuration of the engine and mount. Since it can be manufactured, it is possible to design a simple configuration of a drone taxi, and it has the remarkable effect of minimizing manufacturing costs.

In addition, the present invention is provided with a left thrust means and a right thrust means for generating thrust in the forward direction at the front end of the left boom and right boom, so that the air flow sent to the rear when the propeller rotates flows over the left wing and right wing. This is generated, and as a result, even if the speed of the drone taxi is small, lift is generated on the left and right wings by the left and right thrust means provided on the leading edge, which has a very advantageous effect in low-speed flight and transition flight.

1 is a plan view of a drone taxi according to the present invention.
Figure 2 is a side view of a drone taxi according to the present invention.
Figure 3 is a front view of a drone taxi according to the present invention.
Figure 4 is a plan view showing an example in which the left and right wings are separated in a drone taxi according to the present invention.
Figure 5 is an exemplary diagram showing the air flow caused by the operation of the left and right thrust means in the drone taxi according to the present invention.
Figure 6 is a side view showing an example of a landing part supporting the ground in a drone taxi according to the present invention.
Figure 7 is a side view showing another embodiment of the landing part in the drone taxi according to the present invention.
Figure 8 is a side view showing an example of a landing portion supporting an inclined ground in a drone taxi according to the present invention.
Figure 9 is a front cross-sectional view showing a fixing means for fixing the landing part in the drone taxi according to the present invention.

Advantages and features of the embodiments of the present invention and methods for achieving them will become clear by referring to the embodiments described in detail below along with the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below and may be implemented in various different forms. The present embodiments are merely provided to ensure that the disclosure of the present invention is complete, and that it is common knowledge in the technical field to which the present invention pertains. It is provided to fully inform those who have the scope of the invention, and the present invention is only defined by the scope of the claims. Like reference numerals refer to like elements throughout the specification.

In describing embodiments of the present invention, if a detailed description of a known function or configuration is judged to unnecessarily obscure the gist of the present invention, the detailed description will be omitted. In addition, the terms and words used in the specification and claims are terms defined in consideration of the functions in the embodiments of the present invention, and should not be construed as limited to the usual or dictionary meaning, and the inventor does not pretend to use his or her invention. In order to explain it in the best way, it must be interpreted as meaning and concept consistent with the technical idea of the present invention based on the principle that the concept of the term can be appropriately defined.

Therefore, the embodiments described in this specification and the configurations shown in the drawings are only the most preferred embodiments of the present invention and do not represent the entire technical idea of the present invention, so various equivalents can be substituted for them at the time of filing the present application. It should be understood that there may be variations.

Hereinafter, before explaining with reference to the drawings, matters that are not necessary to reveal the gist of the present invention, that is, known configurations that can be easily added by a person skilled in the art will not be shown or described in detail. Let me make it clear that I did not.

First, before describing various embodiments of the present invention in detail with reference to the accompanying drawings, the directions (e.g., “front”, “back”, “left”) of the components described in the following detailed description or shown in the drawings , “right”, “top”, “bottom”, “superior”, “bottom”, “lateral”, “longitudinal”, “frontal”, “dorsal”, “one side”, “other side”, “medial” and “ Regarding terms such as "outside"), it does not simply indicate or mean that it must have a specific direction, and the description of this direction is intended to facilitate explanation of the components with reference to the attached drawings.

The drone taxi according to the present invention relates to a drone taxi (eVTOL) capable of vertical takeoff and landing.

Here, a drone taxi performs the function of moving people, objects, etc. using a flying vehicle (eVTOL) capable of vertical takeoff and landing, and is characterized by being able to move by flying in the sky.

It can be used as a means of flying transportation to reduce traffic congestion on the roads, and can also be used for military purposes such as reconnaissance. It can also be used for monitoring or filming the ecology of livestock and other animals in vast areas. It can be used in a variety of fields, such as rescuing people who fall into a storm or are stranded in a specific place.

Accordingly, the drone taxi according to the present invention has been developed to enable vertical takeoff and landing, so that it can be utilized in the right place in various fields as described above, and since it is intended to move people, securing flight stability is very important, It is characterized by ensuring stability during low-speed flight or transition flight for operating a vertical takeoff and landing aircraft.

Hereinafter, a drone taxi according to the present invention will be described in detail with reference to the attached drawings.

Figure 1 is a plan view of a drone taxi according to the present invention, Figure 2 is a side view of the drone taxi according to the present invention, Figure 3 is a front view of the drone taxi according to the present invention, and Figure 4 is a left view of the drone taxi according to the present invention. , It is a plan view showing an example in which the right wing is separated, and Figure 5 is an example diagram showing the air flow caused by the operation of the left and right thrust means in the drone taxi according to the present invention.

The drone taxi according to the present invention is equipped with left and right thrust means (81, 83) that enable thrust generation in the forward direction and left and right lifting means (82, 84) that enable thrust generation in the vertical direction, respectively. It facilitates the generation of thrust in the forward and vertical directions, and left and right thrust means (81, 83) are provided on the front end of the left boom (30) and right boom (60), so that thrust is generated from the front of the drone taxi. By causing this to occur, when the propellers of the left and right thrust means (82, 84) provided at the front end rotate, they move over the left and right wings (40, 70) provided at the rear of the left and right thrust means (82, 84). This is about a drone taxi that generates lift, which is advantageous for low-speed flight and can secure the stability of transition flight.

This drone taxi will be described with reference to the attached drawings, including a main body (10), a left wing frame (20), a left boom (30), a left wing (40), a right wing frame (50), a right boom (60), It is comprised of a right wing 70, a thrust unit 80, and a tail wing unit 90.

The main body 10 performs the main body function of a drone taxi capable of generating thrust in a direction perpendicular to the forward direction, and is formed to have a selected length and a selected width in the forward direction, as shown in the attached drawing. .

This main body 10 can be configured to provide a separate space where a power unit (battery) that provides power for navigation, a communication unit for communication, a control unit that can control navigation operations, etc. can be provided, and, Of course, it can be configured to provide space for objects or people to board.

Hereinafter, before explaining the left wing frame (20), left boom (30), left wing (40), right wing frame (50), right boom (60), and right wing (70), the left wing frame (20) , the left boom 30 and left wing 40 are located on the left side of the main body 10, and the right wing frame 50, right boom 60, and right wing 70 are located on the right side of the main body 10. It is configured in a symmetrical form on the left and right sides of the main body 10.

If this is explained in more detail with reference to the attached drawings, the left wing frame 20 is formed in a form that protrudes outward on the left side of the main body 10.

This left wing frame 20 is preferably made integrally with the main body 10, and in order to form the left wing 40, the starting point of the left wing 40 is formed from the main body 10.

The left boom 30 is provided at the end of the left wing frame 20 and has a major axis length on the front and rear sides. That is, as shown in the attached drawing, the left boom 30 is provided in a form that crosses the left wing frame 20 and the left wing 40.

This left boom 30 may be in the form of a long pipe front and rear, and includes a left thrust means 81 for generating thrust in the forward direction and a pair of left lifting means 82 for generating thrust in the vertical direction. ) are combined.

In addition, the left boom 30 is provided with a hollow interior, providing a space for cables or rotors for the operation of the left thrust means 81, which consists of a rotor capable of generating thrust, and the pair of left lift means 82. It can be configured to provide.

At this time, the left thrust means (81) coupled to the left boom (30) is coupled to the front end of the left boom (30), and a pair of left lifting means (82) are coupled to the rear side of the left thrust means (81). They are provided spaced apart, but may be spaced apart from each other and configured as a pair.

In detail, as shown in FIG. 1, a pair of left lifting means 82 may be provided on the front and rear sides, respectively, with respect to the left wing frame 20.

The left wing 40 is coupled to the outside of the left boom 30 in a protruding form.

At this time, the left wing 40 may be configured to be attachable to and detachable from the left wing frame 20.

For example, if described with reference to FIG. 4, two or more grooves are formed on the end surface of the left wing frame 20, and the end surface of the corresponding left wing 40 is provided with a protrusion that fits into the grooves. It can be.

Depending on the design conditions, the grooves and protrusions may be made of magnetic materials or iron materials.

Accordingly, the left wing 40 can be easily and stably mounted and detached through magnetic force while having a protrusion inserted into the groove of the left wing frame 20.

Furthermore, the combination of the left wing frame 20 and the left wing 40 is an interference fit in addition to attachment and detachment by magnetic force. When the protrusion provided on the left wing 40 is inserted into the groove formed in the left wing frame 20, the left wing 40 is connected to the left wing frame 20. The coupling force between the left wing frame 20 and the left wing 40 can be improved by fastening a separate fixing pin that penetrates the groove on the outside of the wing frame 20.

Meanwhile, Figure 4 shows an example in which a protrusion is formed on the end surface of the left wing 40. However, depending on the design conditions, a groove cut inward is formed on the end surface of the left wing 40, and the groove is inserted into the groove. Of course, the protrusion may be formed to protrude from the end surface of the left wing frame 20.

The right wing frame 50 has a structure that is symmetrical to the left wing frame 20 with respect to the main body 10, and is protruded outward on the right side of the main body 10.

This right wing frame 50 is preferably made integrally with the main body 10, and in order to form the right wing 70, the starting point of the right wing 70 is formed from the main body 10.

The right boom 60 is provided at the end of the right wing frame 50 and has a major axis length on the front and rear sides. That is, as shown in the attached drawing, the right boom 60 is provided in a form that crosses the right wing frame 50 and the right wing 70.

This right boom 60 may be in the form of a long pipe front and rear, and includes a right thrust means 83 for generating thrust in the forward direction and a pair of right lifting means 84 for generating thrust in the vertical direction. ) are combined.

In addition, the right boom 60 is provided with a hollow interior, providing a space for cables or rotors for the operation of the right thrust means 83, which consists of a rotor capable of generating thrust, and the pair of right lift means 84. It can be configured to provide.

At this time, the right thrust means (83) coupled to the right boom (60) is coupled to the front end of the right boom (60), and a pair of right lifting means (84) are coupled to the rear side of the right thrust means (83). They are provided spaced apart, but may be spaced apart from each other and configured as a pair.

In detail, as shown in FIG. 1, a pair of right lifting means 84 may be provided on the front and rear sides, respectively, with respect to the right wing frame 50.

The right wing 70 is coupled to the outside of the right boom 60 in a protruding form.

At this time, the right wing 70 may be configured to be attachable to and detachable from the right wing frame 50, and may have the same coupling structure as that of the left wing 40 and the left wing frame 20.

With this configuration, the left wing frame 20, left boom 30, and left wing 40 are provided on the left side of the main body 10, and the right wing frame 50, right boom 60, and right wing are provided on the left side of the main body 10. (70) has a symmetrical structure and is provided on the right side of the main body (10).

The thrust unit 80 is provided on each of the left boom 30 and the right boom 60, and performs a function of enabling thrust generation in the forward and vertical directions of the main body 10, respectively.

In detail, as shown in the attached drawing, left thrust means 81 and Right thrust means (83) is provided.

As shown in FIGS. 2 and 3, the left thrust means 81 and the right thrust means 83 are provided with a vertical propeller at the tip of the left boom 30 and the tip of the right boom 60, respectively. , As the rotation area is implemented in a vertical form during operation, the drone taxi is able to generate thrust in the forward direction.

In addition, a pair of left lifting means 82 are provided on the upper side of the left boom 30 and spaced apart from each other to enable thrust generation in the vertical direction of the main body 10, and have a symmetrical structure, so that the right boom 60 A pair of right lifting means 84 are provided on the upper side and spaced apart from each other.

As shown in FIG. 1, the pair of left lifting means 82 and the pair of right lifting means 84 have propellers in a horizontal form, so that the rotation area during operation is implemented in a horizontal form, so that the drone Enables the taxi to generate thrust in the vertical direction.

Furthermore, the left thrust means 81 and a pair of left lifting means 82 are provided on one left boom 30 having a major axis length on the front side and the rear side, as shown in FIGS. 1 and 2, and the rotation axis center is They are provided spaced apart from each other so that the front and rear sides are in a straight line, and the right thrust means (83) and the pair of right lift means (84) are formed on a single right boom (60) with the rotation axis on the front and rear straight lines. They are provided as spaced apart from each other as possible.

This makes it possible to manufacture the engine and mount by simplifying the configuration, as the left boom 30 and the right boom 60, which are a pair, are equipped with six propellers made of rotors capable of generating thrust.

That is, one left boom (30) is provided with both a left thrust means (81) and a left lift means (82) that enable the generation of thrust in the forward and vertical directions, and each right boom (60) is provided with a left thrust means (81) and a left lift means (82). By ensuring that both the right thrust means (83) and the right lift means (84) are provided to enable generation of thrust in the forward direction and vertical direction, separate propellers for generation of thrust in the forward direction and vertical direction are provided. Since there is no need to connect each mount, the configuration of the drone taxi can be manufactured simply and concisely.

At this time, each of the left thrust means 81 and the right thrust means 83 consisting of a propeller will be configured so that the upper end where the rotation area of the propeller is formed is formed above the top of the left wing 40 and the right wing 70. You can.

Meanwhile, the left thrust means 81 and the right thrust means 83 are provided at the tip of the left boom 30 and the tip of the right boom 60, respectively, to generate thrust in the forward direction, as shown in Figure 5. As described above, when the propellers of the left thrust means 81 and the right thrust means 83 provided on the front end rotate, the left wing 40 provided on the rear of the left thrust means 81 and the right thrust means 83 ) and the right wing (70), so it is advantageous for low-speed flight and transition flight, and stability can be secured.

To elaborate, transition flight refers to the transition stage where the direction of flight is changed when flying in a straight direction and flying in a perpendicular direction, and securing the stability of transition flight is very important.

In other words, after a vertical takeoff and landing (VTOL) airplane flies in the vertical direction, it flies in a hovering state (the speed in the straight direction is 0) until it reaches the normal speed to obtain thrust in the straight direction. , stability during transition flight is very important.

Accordingly, the drone taxi according to the present invention is equipped with left thrust means 81 and right thrust means 83 for generating thrust in the forward direction at the front ends of the left boom 30 and right boom 60 to rotate the propeller. The air flow sent to the rear generates a flow over the left wing (40) and right wing (70), and as a result, the speed of the drone taxi is at least on the leading edge of the left wing (40) and right wing (70). Lift is generated by the left thrust means 81 and the right thrust means 83, which is very advantageous for low-speed flight and transition flight.

The tail wing portion 90 is provided to connect the rear end of the left boom 30 and the rear end of the right boom 60, and includes a horizontal stabilizer 91 and a vertical wing portion 92.

The horizontal stabilizer 91 connects the rear end of the left boom 30 and the rear end of the right boom 60, and is made in the form of a plate to maintain the center of the main body 10 during drone taxi flight.

The vertical wings 92 are provided at both ends of the horizontal stabilizer 91 and form a pair, and are composed of an upper wing part protruding above the horizontal stabilizer 91 and a lower wing part protruding downward.

Here, the lower wing portion is configured to support the ground when the drone taxi lands, and depending on design conditions, wheels capable of rolling motion may be provided to facilitate movement from the ground.

At this time, the main body (10), left wing frame (20), left boom (30), left wing (40), right wing frame (50), right boom (60), and right wing (70) to configure the taxi drone. and the tail wing portion 90 may be made of a carbon fiber composite material that has excellent overall strength and is light in weight, and in some configurations, may be made of various materials such as metal, plastic, and expanded polypropylene (EPP).

Figure 6 is a side view showing an example of a landing part supporting the ground in a drone taxi according to the present invention.

Depending on design conditions, the main body 10 may be provided with a landing portion 11 provided at the bottom to support the ground.

This landing part 11 is protruding from the lower part of the main body 10 and supports the ground, so that the drone taxi is stably supported from the ground when landing.

At this time, as shown in FIG. 3, the landing portion 11 may be composed of a pair of protruding portions in contact with the ground, and may be configured so that the distance between them gradually increases as it goes downward.

Accordingly, when the drone taxi lands on the ground, the lower wing part of the vertical wing part 92 and the landing part 11 support the ground, so that it is maintained horizontally from the ground and supported in a stable state.

Figure 7 is a side view showing another embodiment of the landing part in the drone taxi according to the present invention, Figure 8 is a side view showing an example of the landing part supporting an inclined ground in the drone taxi according to the present invention, and Figure 9 is a side view showing an example of the landing part supporting the inclined ground in the drone taxi according to the present invention. This is a front cross-sectional view showing the fixing means for fixing the landing part in the following drone taxi.

Meanwhile, FIG. 6 shows an example in which the landing part 11 is provided in a protruding form at the lower part of the main body 10. However, depending on the design conditions, as shown in FIG. 7, the main body increases from the front side to the back side. The lower surface of (10) is formed with an inclined surface (11a), and the landing part (11) can be configured to slide forward and backward along the inclined surface (11a).

This is to compensate for the tilt of the main body 10 in the process of the drone taxi taking off from the ground. By adjusting the position of the landing unit 11 along the inclined surface 11a and then supporting the ground, The inclination angle of the main body 10 can be changed.

That is, when explaining with reference to FIG. 8, by adjusting the inclination angle of the main body 10 from the ground so that the propellers of the left lifting means 82 and the right lifting means 84 maintain a horizontal direction, eccentricity occurs during drone taxi flight. Minimize and ensure stable flight upward.

At this time, the landing part 11 that slides along the inclined surface 11a may be configured to be fixed by a separate fixing means 12.

For example, as shown in FIG. 9, a fitting groove 12a having a 'T' cross section cut inward is formed at the lower end of the main body 10 where the inclined surface 11a is formed, and the fitting groove 12a ) has a long shape on the front and back sides along the inclined surface 11a, and one side is open so that the landing portion 11 is inserted into the open space. In response to this, a fitting protrusion 12b having a 'T' cross section that fits into the fitting groove 12a is formed at the top of the landing portion 11, and the outer and fitting grooves are formed along the longitudinal direction of the long axis of the fitting groove 12a. A plurality of fixing grooves 12c communicating with (12a) are formed on the side, and through holes 12d penetrating both sides of the fitting projection 12b are formed, and the through holes 12d and the fixing groove 12c are formed. A fixing pin (12e) inserted into may be provided.

Accordingly, when the landing part 11 slides along the inclined surface 11a, the landing part 11 is fixed at the moved position by inserting a fixing pin 12e into the fixing groove 12c and the through hole 12d. It can be fixed firmly.

According to this configuration, the drone taxi according to the present invention is provided with left and right thrust means (81, 83) at the front end of each of the left and right booms (30, 60) to enable generation of thrust in the forward direction, and Left and right lifting means (82, 84) that enable thrust generation in each direction are provided on each of the left boom (30) and right boom (60), so that the left and right thrust means (81, When the propeller of 83) rotates, lift is generated over the left and right wings (40, 70) provided on the rear of the left and right thrust means (81, 83), so it is advantageous for low-speed flight and transition flight and ensures stability. You can.

In addition, one right boom 60 is provided with a right thrust means 83 and a pair of right lifting means 84 that are provided to generate thrust in the forward and vertical directions, respectively, and one left boom 30 ) is provided with a left thrust means (81) and a pair of left lift means (82) that are provided to generate thrust in the forward and vertical directions, respectively, so that there are six rotors made up of rotors capable of generating thrust in a pair of booms. As the propeller is provided, the configuration of the engine or mount can be simplified and manufactured, enabling a simple configuration design of the drone taxi and minimizing manufacturing costs.

In the above description, various embodiments of the present invention have been presented and explained, but the present invention is not necessarily limited thereto, and those skilled in the art will understand various embodiments without departing from the technical spirit of the present invention. It can be seen that branch substitution, transformation, and change are possible.

10: main body 11: landing part
11a: slope 12: fixing means
12a: Fitting groove 12b: Fitting protrusion
12c: fixing groove 12d: through hole
12e: fixing pin
20: Left wing frame 30: Left boom
40: Left wing
50: Right wing frame 60: Right boom
70: Right wing
80: thrust unit 81: left thrust means
82: Left lifting means 83: Right thrust means
84: Right lifting means
90: tail wing 91: horizontal stabilizer
92: Vertical wing part

Claims (8)

main body (10);
A left wing frame (20) protruding outward on the left side of the main body (10);
A left boom (30) provided at the end of the left wing frame (20) and having a major axis length on the front and rear sides;
A left wing (40) protruding outward from the left boom (30);
A right wing frame 50 protruding outward on the right side of the main body 10;
A right boom (60) provided at the end of the right wing frame (50) and having a major axis length on the front and rear sides;
A right wing (70) protruding outside the right boom (60);
A plurality of thrust units 80 are provided on each of the left boom 30 and the right boom 60 to generate thrust in the forward direction and vertical direction of the main body 10, respectively; and
It is configured to include a tail wing portion (90) connecting the rear end of the left boom (30) and the rear end of the right boom (60),
The tail wing portion 90 is
A horizontal stabilizer 91 in the form of a plate connecting the rear end of the left boom 30 and the rear end of the right boom 60; and
It is provided at both ends of the horizontal stabilizer 91 and consists of vertical wings 92 consisting of an upper wing and a lower wing,
The main body 10 is
It is configured to include a landing part 11 provided at the bottom to support the ground,
It is composed of a slope (11a) whose bottom surface is inclined from the front side to the back side,
The landing part 11 is
A drone taxi, characterized in that it can slide along the slope (11a).
In claim 1,
The thrust unit 80 is
Left thrust means (81) provided at the front end of the left boom (30) to enable generation of thrust in the forward direction of the main body (10);
A pair of left lifting means (82) provided spaced apart from each other on the upper side of the left boom (30) to enable generation of thrust in the vertical direction of the main body (10);
Right thrust means (83) provided at the front end of the right boom (60) to enable thrust generation in the forward direction of the main body (10); and
A drone taxi characterized by comprising a pair of right lifting means (84) provided at a distance from each other on the upper side of the right boom (60) to enable generation of thrust in the vertical direction of the main body (10).
In claim 2,
The left thrust means 81 and the pair of left lifting means 82 are coupled to a single left boom 30 at a distance from each other so that the rotation axis is formed in a straight line at the front and rear,
The right thrust means (83) and the pair of right lift means (84) are a drone taxi, characterized in that they are spaced apart from each other and coupled to one right boom (60) so that the rotation axis is formed in a straight line at the front and rear.
In claim 2,
Each of the left thrust means 81 and the right thrust means 83 is made of a propeller, and the upper end where the rotation area of the propeller is formed is formed above the tops of the left wing 40 and the right wing 70. Drone taxi characterized by:
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