KR20180102781A - Unmanned aircraft - Google Patents

Abstract

Provided is an unmanned aircraft, which comprises: a rotor for rotating at least one propeller around a rotary shaft; a fuselage having a hollow unit in which the rotary shaft is disposed; a support frame for supporting the rotor to the fuselage; a cover covering the hollow unit and having a suction hole opened to suck outdoor air in the center of the cover; and an impeller disposed in the upper portion of the rotary shaft and allowing the outdoor air sucked through the suction hole to be expanded outward from the rotary shaft by rotation.

Description

UNMANNED AIRCRAFT

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an unmanned flight device, and more particularly, to a unmanned flight device capable of flying with a single shaft rotor and a propeller.

In recent years, unmanned aerial vehicles (UAVs) have become widely popular as hobby vehicles as well as military or civilian reconnaissance aircraft, and a variety of unmanned aerial vehicles have been developed.

1 is a perspective view of a conventional unmanned aerial vehicle. As shown in Fig. 1, the conventional unmanned flight control apparatus 10 is configured such that a plurality of rotors 12a to 12d rotate the propeller to float the moving body 11 in the air. At this time, the power of at least one of the plurality of rotors 12a to 12d is regulated, thereby enabling takeoff and landing of the moving body 11 and change of direction.

However, in the conventional unmanned flight control apparatus 10, a plurality of propellers are exposed to the outside, and various problems may occur.

Specifically, a plurality of propellers exposed to the outside may cause the propeller or the obstacle to be damaged by the rotation due to interference with the surrounding obstacles during the flight, and the rotating propeller may be a threat to people or animals. In addition, the propeller can easily interfere with an adjacent object even when not in flight, which makes it difficult to store and transport the unmanned flight device 100. When the unmanned airplane device 100 crashes due to collision with surrounding obstacles, There is a problem in that the rotation of the vehicle can interfere with the surrounding obstacle and can not be taken off again.

On the other hand, a camera is mounted on an unmanned flight device for free photographing without restriction of a photographing position, and a lot of photographing using an unmanned flight device has been attempted. Reference numeral 3 in Fig. 1 denotes a camera, A rotatable support frame for permitting rotation about the longitudinal or lateral axis so that the camera 13 can be placed horizontally or vertically irrespective of the motion of the moving body 11 for stable photographing of the camera 3. [ It refers to a gimbal.

The present invention aims to provide a unmanned flight device having a single shaft rotor and a propeller capable of causing a large thrust without causing interference with an external obstacle.

In order to solve the above-described problems, the present invention provides a turbine engine including a rotor for rotating at least one propeller about a rotary shaft, a body having a hollow portion in which the rotary shaft is disposed, and a support frame for supporting the rotor in the body, The apparatus comprising: a cover which covers the hollow portion, the cover having an inlet port opened to suck ambient air in a central portion thereof; and a cover which is located above the rotary shaft and diffuses outside air sucked through the inlet port by rotation to the outside of the rotary shaft And an impeller for an unmanned flight.

The present invention also provides a unmanned flight control device comprising a rotor including a propeller rotating about a rotation axis, a body having a hollow portion in which the rotation axis is disposed, and a support frame for supporting the rotor on the body, The air flow formed by the rotation of the hollow portion is sucked from the upper side of the hollow portion and discharged to the lower side of the hollow portion so that the air flow is larger than the diameter of the propeller in which the outside air is sucked on the upper side of the hollow portion, Provides a unmanned flight device with a cover with a small aperture inlet.

According to one embodiment, the cover is positioned on the body so that the propeller is not exposed above the top surface of the cover, and the cover is formed into a convexly curved surface of a convex shape to facilitate high- .

According to one embodiment, the fuselage is annular, and the upper peripheral surface of the fuselage may be a cycloid-shaped curved surface extending from the curved surface of the cover.

According to one embodiment, the body is annular, and the thickness may become narrower from the inside to the outside.

According to an embodiment, the diameter of the inlet port through which the outside air is sucked may be smaller than the diameter of the propeller.

According to an embodiment of the present invention, the outside air sucked through the intake port is diffused by the impeller, and the propeller can generate thrust using the airflow formed by the impeller.

According to one embodiment, the propeller includes first and second propellers disposed above and below the rotary shaft, and the first and second propellers rotate in opposite directions to generate thrust, Can have the shape of the incoming light along the moving direction of the outside air around the propeller.

According to one embodiment, the impeller may include a conical body and a plurality of spiral-shaped rotating blades formed on the outer surface of the body.

According to one embodiment, the cover has a buoyancy providing space between an air flow generated by rotation of the impeller and the propeller and an inside of an upper portion of the cover, and the buoyancy providing space is vacuum or low pressure by the air flow So that buoyancy can be provided to the unmanned flight device.

According to one embodiment, the unmanned aerial vehicle includes a plurality of support frames, and at least one of the support frames may be tubularly provided with electric wiring or communication wiring in the rotor.

According to one embodiment, at least one said support frame is rotatable about its longitudinal axis, said rotatable support frame being arranged at each of the front, rear, left and right sides of said rotor, along the longitudinal direction of said rotatable support frame And at least one blade formed.

According to one embodiment, each of the rotatable support frames includes a blade on either side, and the flight direction of the unmanned flight device can be changed according to the rotation of the rotatable support frame.

According to one embodiment, the body may have a thickness such that the blade is not exposed beneath the bottom surface.

According to one embodiment, the UAV may further include a landing gear including a plurality of support legs formed along a part of an inner circumferential surface at a lower end of the body.

According to one embodiment, the support legs may be folded or unfolded by both side ends hinged to the inner peripheral surface of the lower end of the moving body, and the support legs rotate about the hinge axis.

According to one embodiment, the moving body is annular, and the lower outer circumferential surface of the moving body has an upward tapered shape, and the landing gear includes a supporting foot extended from one side of the supporting leg The support leg may be bent upward along the outer surface of the lower portion of the body when the landing gear is folded.

In the UAV according to an embodiment of the present invention, there is no possibility that the propeller rotating because the propeller is not exposed to the outside may interfere with the external obstacle, and thus the possibility of falling of the UAV is small. In addition, since the propeller is not exposed to the outside, it is easy to store and transport the unmanned aerial vehicle.

Since the unmanned aerial vehicle according to the embodiment of the present invention employs a single shaft rotor and a propeller, it has a larger propeller size than a flying body of the same size, so that it can have a relatively large thrust, The thrust is generated by using the air current diffused and diffused outward by the impeller, so that it can have a larger thrust.

In addition, the unmanned flight device according to one embodiment of the present invention has a vacuum space at the upper part inside the upper cover by the diffusion air flow generated by the impeller, and buoyancy can be formed by the vacuum space.

In addition, the UAV according to an embodiment of the present invention may have a low overall height by using a blade disposed on both sides of a support frame for supporting the rotor without a separate rudder structure, Lt; / RTI >

In addition, the UAV according to an embodiment of the present invention has a curved surface of a cycloid shape in which the upper cover is convexed upward, thereby facilitating high-speed airflow movement and allowing flight with low air resistance .

1 is a perspective view of a conventional unmanned aerial vehicle.
2 is a plan view of an unmanned aerial vehicle according to an embodiment of the present invention.
3 is a bottom view of the unmanned aerial vehicle of FIG. 2;
4 is a bottom perspective view of the UAV of FIG. 2;
5 is a front view of the UAV of FIG. 2;
6 is a side view of the UAV of FIG. 2;
7 is a view for explaining a concept of generating thrust in the UAV according to an embodiment of the present invention.
8 is a view illustrating a rudder of an unmanned aerial vehicle according to an embodiment of the present invention.
FIG. 9 is a view for explaining a structure of a rudder and a direction switching method of an unmanned flight control apparatus according to an embodiment of the present invention. Referring to FIG.
10 is a view illustrating an example of operation of the rudder according to the flight direction of the UAV according to the embodiment of the present invention.
11 is a view showing a state where the landing gear of the UAV is unfolded according to an embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings, wherein like reference numerals are used to designate identical or similar elements, and redundant description thereof will be omitted. The suffix "module" and " part "for the components used in the following description are given or mixed in consideration of ease of specification, and do not have their own meaning or role. In the following description of the embodiments of the present invention, a detailed description of related arts will be omitted when it is determined that the gist of the embodiments disclosed herein may be blurred. It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory and are intended to provide further explanation of the invention as claimed. , ≪ / RTI > equivalents, and alternatives.

Terms including ordinals, such as first, second, etc., may be used to describe various elements, but the elements are not limited to these terms.

The terms are used only for the purpose of distinguishing one component from another.

It is to be understood that when an element is referred to as being "connected" or "connected" to another element, it may be directly connected or connected to the other element, . On the other hand, when an element is referred to as being "directly connected" or "directly connected" to another element, it should be understood that there are no other elements in between.

The singular expressions include plural expressions unless the context clearly dictates otherwise.

In this specification, the terms "comprises" or "having ", and the like, are intended to specify the presence of stated features, integers, steps, operations, elements, parts, or combinations thereof, But do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or combinations thereof.

2 is a plan view, Fig. 3 is a bottom view, Fig. 4 is a bottom perspective view, Fig. 5 is a front view, and Fig. 6 is a side elevation view of the unmanned air navigation apparatus according to the embodiment of the present invention. Side view.

2 to 6, the UAV 100 according to an embodiment of the present invention includes a body 110, a cover 120, a rotor 130, support frames 141 to 144, and an impeller (not shown) 150).

However, it is needless to say that the components shown in FIGS. 2 to 6 are not essential, so that an unmanned flight vehicle having more or fewer components can be implemented.

Hereinafter, each component will be described.

The body 110 forms an appearance of the UAV 100. The body 110 has a hollow portion for accommodating the rotor 130 including the propellers 131 and 132 and the hollow body 110 is formed in an annular shape ).

As described above, the body 110 may be in the form of surrounding the hollow portion, and the specific shape is not particularly limited. For example, the body 110 may have a circular or polygonal shape in its longitudinal section, but it is preferable that at least a part of the outer surface is a curved surface in order to minimize resistance to air.

In addition, it is preferable that the body 110 has an empty space, that is, a hollow portion. The hollow portion may include a circuit board for controlling various components included in the UAV 100, an ultrasonic sensor module, A motor for rotating the support frame, a battery for supplying power to various parts, and the like may be mounted.

The rotor 130 is for rotating at least one propeller 131, 132 around a single rotational axis 135, and may include at least one motor (not shown). The rotor 130 may be coupled to the body 110 by a plurality of support frames 141 to 144 so that the rotor 130 including the motor may be positioned in the hollow portion of the body 110.

According to one embodiment, first and second propellers 131 and 132 are installed on the one rotary shaft 135, and the first and second propellers 131 and 132, And may be axially spaced apart from each other in the upward direction of the rotor 130. At least one propeller 131 or 132 rotating around the rotation shaft 135 generates an air flow passing through the hollow portion of the body 110 so that the UAV 100 can be lifted up vertically And can float in the air.

Here, when the moving body 110 is taken off, it is preferable that the propellers 131 and 132 rotate about coaxial axes but rotate in different directions. That is, when the first propeller 131 rotates in the clockwise direction, the second propeller 132 can rotate in the counterclockwise direction. On the contrary, when the first propeller 131 rotates in the counterclockwise direction, 2 propeller 132 can rotate clockwise. As the first and second propellers 131 and 132 rotate in opposite directions to each other, the UAV 100 can generate a larger lift in the vertical direction.

The single rotation shaft 135 and the propellers 131 and 132 are coupled by a gear module composed of a plurality of gears so that the first and second propellers 131 and 132 rotate in opposite directions and / You can have speed.

On the other hand, the first or second propeller 131 or 132 rotating about a single rotation axis includes at least two blades for generating lift, and preferably four blades. Here, the shape of the blades is not particularly limited, but it is preferable that the cross sections of the blades of the first and second propellers 131 and 132 are curved so that a large lift is generated. That is, the propeller blade may have a shape that is twisted at a predetermined angle with respect to the longitudinal direction, and may have a shape in which the width of the blade decreases gradually from the end (farther from the rotation axis). According to one embodiment, the end of the wing may further include a wing piece that is bent and extended in the up or down direction.

The first or second propeller 131 or 132 is coupled to the rotation shaft 135 in a state in which the wing is inclined by a predetermined angle (?) In the gravity direction from the horizontal direction so as to generate a larger lift force by rotation. .

As described above, since the UAV 100 according to the present invention employs the first and second propellers 131 and 132 having a single shaft, it has a wider propeller size than a flying body of the same size, Lt; / RTI >

The supporting frames 141 to 144 are for supporting the rotor 130 on the moving body 110 and the rotor 130 and the supporting frames 141 to 144 are rotated by the rotation of the first and / or second propellers 131 and 132, 144 may be capable of flying.

The support frames 141 to 144 may have a tubular shape in which the inside is hollow and the tubular support frames 141 to 144 may be formed by electric wiring for supplying electric power to the rotor 130, A communication wire for transmitting a control signal or receiving various sensing signals from the rotor 130 may be incorporated.

A plurality of support frames 141 to 144 may be provided along the outer circumference of the rotor 130. The number of the support frames 141 to 144 is not particularly limited, but is preferably four. That is, the UAV 100 is provided with blades on both sides of the longitudinal direction of the support frames 141 to 144 so as to be able to rotate in the longitudinal direction, And may be coupled to the rotor 130 and the body 110.

A detailed description of the flight direction switching according to the rotation of the support frames 141 to 144 will be described later.

The cover 120 is disposed on the upper portion of the body 110 to cover the hollow portion of the body 110 so that the propellers 131 and 132 are not exposed to the outside, And may have an air inlet 101 which is opened.

The shape of the cover 120 may be, for example, a polygonal pyramid or a cone having a bottom opening with an intake port 101 at a vertex, or another hemispherical shape having an intake port 101 at a central portion.

However, according to a preferred embodiment, the shape of the cover 120 is preferably formed as a curved surface of a convex cycloid shape as shown in FIGS. The upper outer surface of the UAV 100 has a curved surface to allow high-speed airflow so that the UAV 100 can fly with low air resistance.

In addition, it is preferable that the annular body 110 has a curved surface of the upper outer circumferential surface, so that the curved surface does not form a curved surface at a portion where the cover 120 and the body 110 face each other Do. That is, it is preferable that the curved surface of the cover 120 is extended to the outer surface of the upper portion of the body 110. The lower outer circumferential surface of the body 110 may also be a curved surface of a cycloid shape.

The thickness of the annular body 110 becomes narrower from the inside to the outside, so that the body 110 to which the cover 120 is coupled can have a substantially UFO shape (see FIG. 7) It is possible to prevent the flight device 100 from receiving a high air resistance when flying in the lateral direction.

According to one embodiment, the cover 120 may be installed on the lower part of the body 110 but not on the upper part of the body 110. In this case, Is preferably smaller than the air inlet 101 of the cover 120 located above the body 110. A detailed description thereof will be omitted from the description of the thrust generation principle described later.

Hereinafter, the principle of generating the thrust by the unmanned aerial vehicle according to an embodiment of the present invention will be described in detail.

7 is a view for explaining a concept of generating thrust in the UAV according to an embodiment of the present invention.

As described above, the cover 120 has the intake port 101 opened at the center for sucking the outside air. The outside air is introduced into the cover 120 through the intake port 101 by the rotation of the propellers 131 and 132. The introduced outside air passes through the propellers 131 and 132 and the support frames 141 through 144, And is discharged to the outside through an exhaust port 102 located at the lower portion of the housing 110. Since the diameter of the intake port 101 is smaller than the diameter of the propellers 131 and 132 or the inner diameter of the body 110 and the diameter of the exhaust port 102 is larger than that of the intake port 101, The moving body 110 may have a shape of entering and outgoing along the moving direction of the outside air around the propellers 131 and 132.

Meanwhile, the impeller 150 is positioned above the rotary shaft 135, and diffuses the outside air sucked through the inlet 101 to the outside of the rotary shaft 135 by rotation. That is, since the outside air introduced through the air intake port 101 having a small diameter is scattered to the edge of the hollow portion of the body 110 and the thrust is generated by using the thus formed air stream, ) Can have a larger thrust than when there is no.

FIG. 7 illustrates the airflow generated by the unmanned aerial vehicle 100 according to an embodiment of the present invention. That is, the airflow formed by the rotation of the propellers 131 and 132 is formed by the outside air being sucked from the upper side of the hollow portion of the moving body 110 and discharged to the lower side of the hollow portion, Will have a flow of broad-leaved exit (入 狹 出 廣). Accordingly, the UAV 100 includes a cover 120 having a suction port having a diameter smaller than the diameter of the propellers 131 and 132 on the upper side of the hollow portion, and the width of the airflow discharged to the lower side of the hollow portion is narrow .

The impeller 150 serves to diffuse the outside air introduced through the inlet 101 as described above. The impeller 150 may include a conical body 151 and a plurality of through holes formed in the outer surface of the body 151 And may include a plurality of spiral rotation blades 152 to 156 (see FIG. 8).

It is preferable that the body 151 of the impeller is conical in order to allow the outside air introduced from the upper side to flow into the cover 120 without resistance and the side of the conical body 151 is provided with a spiral- (152 to 156) may be formed. Here, the rotary vanes 152 to 156 may have a spiral shape in which the height gradually increases from the vertex to the bottom, but the shape is not particularly limited. By rotating the rotary vanes 152 to 156 around the rotary shaft 135, it is possible to diffuse the outside air flowing in from the upper side to the outside and to increase the speed of the air flow.

7, the cover 120 may be formed to have a buoyancy providing space 121 of a predetermined size on the upstream side of the airflow and the upper side of the cover 120. [ The buoyancy providing space 121 may be vacuum or low pressure due to the high speed airflow generated by the rotation of the impeller 150 and the propellers 131 and 132 to provide buoyancy to the UAV 100 .

Accordingly, in the UAV 100 according to an embodiment of the present invention, the buoyancy provided by the buoyancy providing space 121 in which a large thrust by the airflow of the incoming light and the vacuum or the low pressure is formed, It is possible to fly smoothly.

Hereinafter, the principle of switching the flight direction of the UAV according to an embodiment of the present invention will be described in detail.

FIG. 9 is a view for explaining a structure of a rudder and a direction switching method of an unmanned flight control apparatus according to an embodiment of the present invention. Referring to FIG.

As shown in FIG. 9, the UAV according to an embodiment of the present invention includes a blade disposed on both sides of the support frames 141 to 144 that support the rotor 130 without a separate rudder structure, (See Fig. 9 (b)) or in a counterclockwise direction (see Fig. 9 (c)).

As described above, the at least one supporting frame 141 to 144 is rotatable about the longitudinal direction, and the rotatable supporting frames 141 to 144 are disposed at each of the front and rear sides of the rotor 130, Possible support frames 141 to 144 may have blades 1411, 1412, 1421, 1422, 1431, 1432, 1441 and 1442 on both sides along the longitudinal direction. A motor for rotating the support frames 141 to 144 may be provided in the body 110.

When at least one of the plurality of support frames 141 to 144 rotates by a predetermined angle in any direction, an air flow for propelling the body is applied to the rotated blade, A force is generated, and the gas rotates with the rotational force by the transverse force.

For example, as shown in Fig. 10 (a), when the support frames 144 and 142 arranged on the left and right are rotated toward the "front" direction, When the support frames 144 and 142 disposed on the left and right sides are turned toward the "rear" direction as shown in Fig. As shown in Fig. 10 (c), when the support frames 141 and 143 disposed on the front and rear sides are rotated toward the "right" direction, the gas flows to the left, As described above, when the support frames 141 and 143 arranged in the front and rear are rotated toward the "left" As shown in FIG. 10 (e), when the support frames 141 to 144 disposed at the front, rear, left, and right sides are rotated in the counterclockwise direction with respect to the direction viewed from the rotor 130, 10 (f), when the support frames 141 to 144 disposed at the front, rear, left, and right sides are rotated in the clockwise direction with respect to the direction viewed from the rotor 130, (Right yawing) in place. Needless to say, it is possible to fly in various flight directions by driving combinations of the support frames 141 to 144 shown in each of Figs. 10A to 10F (not shown).

At this time, the body 110 may have a thickness below the bottom so that the blades 1411, 1412, 1421, 1422, 1431, 1432, 1441, 1442 formed in the support frames 141 to 144 are not exposed. According to this, the overall height of the UAV 100 can be lowered without the blades protruding out of the casing.

Although the height or the size of the moving body 110 according to the embodiment of the present invention is not particularly limited, the height of the moving body 110 may be determined by the rotor 130, the first and second propellers 131 and 132, Or more. That is, by preventing the propellers 131 and 132 from protruding outside the moving body 110 when the moving body 110 is placed on the ground, it is possible to prevent the propellers 131 and 132 from interfering with external obstacles, It is possible to remarkably reduce the possibility of collision and re-take-off without the hassle of eliminating interference with external obstacles in case of a fall, and it is possible to facilitate the storage and transportation of the unmanned flight device 100.

A blade is disposed only at one side of the support frames 141 to 144 and the direction of the blades is changed by rotation of the support frames 141 to 144, In order to realize such a problem that a blade having a long length may be required and the blade may protrude out of the gas and a blade protruding out of the gas may not be projected out of the gas, There is a problem in that the thickness of the dielectric layer 110 must be increased.

As another example, a method of installing the blades rotatably in a separate rudder structure other than the support frames 141 to 144 can be expected. However, since the rudder structure for installing the blades should be disposed on the downstream side of the air stream, There is a problem that the blades can protrude out of the base. Likewise, there is a problem in that the thickness of the base body 110 must be thickened to implement the blade protruding out of the base so as not to protrude out of the base.

Meanwhile, the UAV 100 according to an embodiment of the present invention may include a landing gear. The landing gear is for supporting the weight of the aircraft when the unmanned flying device 100 is moored on the ground, and the landing gear is located at a lower portion of the unmanned flight device 100 and unfolded at landing And supports the body 110 away from the ground. When the unmanned flight control device 100 is taken off and flying, the landing gear may be folded so as not to interfere with an external obstacle.

6, the landing gear according to an embodiment of the present invention may include a plurality of landing gears along a part of the inner circumferential surface of the lower end of the body 110, And may include a plurality of support legs 161 and 162 formed therein.

For example, when the landing gear is folded, the entire plurality of support legs 161 and 162 may be annular so as to be formed along the inner peripheral surface of the lower end of the body 110. The number of the support legs 161 and 162 is not particularly limited but is preferably two or more to support the base body. In the case where the support legs 161 and 162 are two, the support legs 161 and 162 may be semi- have.

At this time, both ends of the support legs 161 and 162 are hinged to the inner peripheral surface of the lower end of the body 110, and the landing gear can be folded or unfolded by rotation about the hinge shafts 163 and 164 have. Specifically, the state of folding the landing gear according to an embodiment of the present invention is as shown in FIGS. 5 to 6, and the state where the landing gear is unfolded is as shown in FIG. That is, when the landing gear is folded, the plurality of support legs 161 and 162 are not exposed to the outside, and when the landing gear is unfolded, the plurality of support legs 161 and 162 are raised, .

The landing gear may further include support legs 1611, 1612, 1621, and 1622 extending from one side of the support legs 161 and 162, according to one embodiment. Accordingly, when the landing gear is unfolded, the support feet 1611, 1612, 1621, and 1622 can be placed along the ground to stably support the gas.

At this time, the support feet 1611, 1612, 1621, and 1622 may be bent along the lower outer surface of the body 110 so that the landing gear does not protrude outward from the outer surface of the body 110 when the landing gear is folded, The support feet 1611, 1612, 1621, and 1622 may also be bent upward along the outer surface of the body 110 when the lower outer surface of the body 110 is tapered upward.

Here, the number of the support feet 1611, 1612, 1621, and 1622 formed on one support legs 161 and 162 is not particularly limited, but is preferably two or more.

Meanwhile, the unmanned flight control apparatus 100 according to an embodiment of the present invention can perform an autonomous flight according to a predetermined route, but it is also possible to provide a control command from a remote terminal (or a control device) And a control unit for controlling the operation of at least one component included in the UAV 100 by a control command received through the communication unit.

The UAV 100 may include an obstacle detection sensor for sensing a forward object on a side surface of the body 110 and / or a bottom surface of the body 110. [ The obstacle detection sensor may be an ultrasonic sensor having a module for transmitting an ultrasonic wave and a module for receiving the transmitted ultrasonic wave according to an embodiment. The ultrasonic sensor may be disposed on the bottom surface of the body 110 At least one may be installed, and at least one may be provided along the outer circumferential surface of the side of the body 110 as shown in Figs. Reference numeral 112 shown in Figs. 4 to 6 denotes a vertical ultrasonic sensor installed on the bottom surface of the body 110. The vertical ultrasonic sensor 112 detects a front object on the bottom surface of the body 110, To be measured. Reference numerals 111a to 111d shown in Figs. 4 to 6 denote horizontal ultrasonic sensors provided on the side surface of the moving body 110. The horizontal ultrasonic sensors 111a to 111d sense front objects on the side surface of the moving body 110 So that the distance to the forward object can be measured.

The control unit can control the flight so that the moving body 110 does not collide with the obstacle by using the distances to the adjacent obstacles measured by the ultrasonic sensors 111a to 111d and 112 and the ultrasonic sensors 111a to 111d And 112 to the remote terminal so that the remote terminal can display the distance to the adjacent obstacle.

The unmanned flight control apparatus 100 may further include a mesh covering the intake port 101 formed in the cover 120.

The mesh can prevent external foreign matter from being sucked into the propellers 131 and 132 through the intake port 101 to improve flight stability or prevent damage of the UAV 100. [

Meanwhile, in the UAV 100 according to the embodiment of the present invention, the fluorescent material may be applied to at least a part of the surface exposed to the outside.

At least one of the unmanned flight devices 100 may be provided in order to inform the outside of the position of the unmanned airplane device 100 while the unmanned airplane device 100 is in flight in the dark or to reduce the risk of losing the dropped unmanned airplane device 100 At least a portion of the surface of the structure may be coated with a fluorescent material.

In the meantime, the UAV 100 according to an embodiment of the present invention includes a camera 110, a light emitting means, a receiving means, a communication network constituting means, a speaker, a microphone, a temperature sensor, a wind direction sensor, A positioning module, a solar module, a display means, and an additional battery.

The unmanned flight control apparatus 100 including at least one extension module may acquire and acquire a surrounding image using a camera, inform the outside of the position of the unmanned airplane using light emitting means, It is also possible to carry goods carried by the article receiving means or to establish radio communication between two or more communication nodes by using the communication network constituting means or to output a sound around the wireless flying apparatus by using a speaker, You can collect the sound around the wireless flight device, determine the weather condition of the wireless flight device by using the temperature, the wind direction and the air flow sensor, or use the positioning module to determine the exact position of the wireless flight device or use the solar module Thereby supplying electric power or storing electric power to the configuration included in the wireless flight device, Utilized can be added to ensure the flight time of flight wireless devices by providing an image on a peripheral device or a wireless flight, using an additional battery.

It is needless to say that the extension module is not limited thereto and may be various application devices.

The expansion module according to an embodiment of the present invention may be provided with a predetermined space in the body 110 so that the extension module can be attached to or detached from the body 110. The extension module may include at least one terminal exposed to the outside in order to be electrically connected to the body 110 so that the extension module can be attached to and detached from the body 110, And at least one terminal exposed to the outside in order to be electrically connected to the expansion module.

In order to prevent contaminants such as water and dust from entering the expansion module mounting space when the expansion module is not installed or to reduce resistance with air at the time of flight, And a cover for covering the mounting space.

Meanwhile, the expansion module according to an embodiment of the present invention may be an additional flight device for allowing the UAV 100 to fly.

The additional flight device may be at least one of an additional propeller for securing additional lift, a fixed wing for enabling horizontal flight, or a thrust generating means for generating thrust.

The unmanned flight device 100 equipped with an additional propeller can generate an additional lift when the object is loaded, thereby enabling a smooth flight.

In addition, the fixed wing (which may be a plate-shaped wing) may be mounted on both sides of the body 110, and the UAV 100 equipped with the fixed wing may be unintentionally lowered , It can be slid by a predetermined distance without falling vertically so that it can land safely without impact.

In addition, the unmanned flight control apparatus 100 equipped with thrust generating means such as a jet propulsion device generates a thrust to move at a high speed in the forward, backward, leftward and rightward directions.

Meanwhile, the expansion module according to an embodiment of the present invention may be an air resistance means capable of providing the body 110 with resistance against outside air.

The air resistance means may comprise, for example, an air pocket capable of containing at least one air. The air bag provides resistance to the outside air to the moving body 110 to provide a safe landing or to prevent the moving body that is falling vertically from damaging the external impact so that the impact that may be applied from the ground can not be directly applied to the moving body 110 . The air bladder may be located at any portion of the body 110 (which may be a side portion or a lower portion of the body 110), and is not particularly limited.

According to one embodiment, it is preferable that the air bag is in a state in which no air is injected into the inside of the unmanned flight control apparatus 100 during takeoff or flight, and the air bag is provided with a user input, a battery shortage, a sudden altitude fall, ) State, the control unit preferably injects air into the air bag. In order to inject air into the air bag, the control unit opens the air inlet formed in the air bag to control the air to flow into the air bag, or to open the air inlet to the air bag, For example, a compressor) may be driven to inject air into the air bag.

The preferred embodiments of the present invention have been described in detail with reference to the drawings. It will be understood by those of ordinary skill in the art that various changes in form and details may be made therein without departing from the spirit and scope of the present invention as defined by the appended claims.

Accordingly, the scope of the present invention is defined by the appended claims rather than the foregoing detailed description, and all changes or modifications derived from the meaning, range, and equivalence of the claims are included in the scope of the present invention Should be interpreted.

100: unmanned flight device 101: intake port
102: exhaust port 110:
111a, 111b, 111c, 111d: horizontal ultrasonic sensor 112: vertical ultrasonic sensor
120: cover 121: buoyancy providing space
130: rotor 131: first propeller
132: second propeller 135: rotary shaft
141: first support frame 1411, 1412: first blade
142: second support frame 1421, 1422: second blade
143: third support frame 1431, 1432: third blade
144: fourth support frame 1441, 1442: fourth blade
150: impeller 151: body
152 to 156: rotating blades 161: first landing gear
1611, 1612: first support foot 162: second landing gear
1621, 1622: second support feet 163, 164: hinge shaft

Claims (20)

A rotor for rotating at least one propeller about a rotational axis;
A body having a hollow portion in which the rotation axis is disposed; And
A support frame for supporting the rotor on the body;
Wherein the unmanned flight device comprises:
A cover covering the hollow portion, the cover having an inlet port opened to suck ambient air at a central portion thereof; And
An impeller positioned above the rotating shaft for diffusing the outside air sucked through the inlet port toward the outside of the rotating shaft by rotation;
And an unmanned flight device. The method according to claim 1,
The cover is positioned on the body so that the propeller is not exposed above the top surface of the cover,
Wherein the cover is formed in a convexly curved surface of a convex shape to facilitate high-speed airflow movement. The method according to claim 1,
Wherein the body is annular and the thickness is narrower from the inside to the outside. The method according to claim 1,
Wherein a diameter of a suction port through which the outside air is sucked is smaller than a diameter of the propeller. 5. The method of claim 4,
Wherein the outside air sucked through the intake port is diffused by the impeller, and the propeller generates a thrust by using the air flow formed by the impeller. The method according to claim 1,
Wherein the propeller comprises:
Wherein the propeller includes first and second propellers disposed above and below the rotary shaft, wherein the first and second propellers rotate in opposite directions to generate thrust,
Wherein the cover
And has a shape of an incident light along the moving direction of the outside air around the propeller. The method according to claim 1,
The impeller
Wherein the body has a conical body and a plurality of spiral-shaped rotating blades formed on an outer surface of the body. The method according to claim 1,
Wherein the cover has a buoyancy providing space between an air flow generated by rotation of the impeller and the propeller and an upper inside of the cover,
Wherein the buoyancy providing space is vacuum or low pressure by the air flow to provide buoyancy to the unmanned flight device. The method according to claim 1,
The unmanned flight device according to claim 1,
Wherein the at least one support frame is tubular and is provided with electrical or communication wiring in the rotor. 10. The method of claim 9,
Wherein at least one of the support frames is rotatable about an axis in the longitudinal direction,
Wherein the rotatable support frame includes at least one blade disposed along the longitudinal direction of the rotatable support frame, the rotatable support frame being disposed at each of the front, rear, left, and right sides of the rotor. 11. The method of claim 10,
Wherein each of the rotatable support frames includes a blade on both sides,
Wherein the flight direction of the unmanned flight device changes according to the rotation of the rotatable support frame. 11. The method of claim 10,
Wherein the body has a thickness such that the blade is not exposed under the bottom surface. The method according to claim 1,
The unmanned flight device (1)
And a landing gear including a plurality of support legs formed along a part of an inner circumferential surface at a lower end of the body. 14. The method of claim 13,
Wherein the support legs are hinged to the inner circumferential surface of the lower end of the moving body at both ends, and the landing gear is folded or unfolded by rotating the support leg about the hinge axis. 14. The method of claim 13,
Characterized in that the body is annular and the lower outer circumferential surface of the body has a tapered shape upward,
Wherein the landing gear further includes a support leg extending from one side of the support leg, wherein the support foot is bent upward along the outer surface of the lower portion of the body when the landing gear is folded. A rotor including a propeller rotating about a rotational axis;
A body having a hollow portion in which the rotation axis is disposed; And
A support frame for supporting the rotor on the body;
Wherein the unmanned flight device comprises:
Wherein the air flow formed by the rotation of the propeller is formed by sucking air from the upper side of the hollow portion and discharging to the lower side of the hollow portion, the upper portion of the hollow portion being sucked out by the propeller And a cover having an intake port having a diameter smaller than the diameter of the cover. 17. The method of claim 16,
And the downstream of the airflow formed below the hollow portion does not narrow the width of the exhaust. 17. The method of claim 16,
An empeller located at an upper portion of the rotary shaft for diffusing the outside air sucked through the inlet port toward the outside of the rotary shaft by rotation;
Further comprising:
Wherein the propeller generates a thrust by using the sucked outdoor air diffused by the empeller. 17. The method of claim 16,
The unmanned flight device according to claim 1, wherein the unmanned flight device includes a plurality of support frames, each of the plurality of support frames is disposed on each of front, rear, left and right sides of the rotor,
Wherein each of the plurality of support frames includes blades on both sides along the longitudinal direction to convert the flight direction of the unmanned flight device according to the rotation of the support frame. 20. The method of claim 19,
The vehicle body,
And has a thickness below the bottom so that the blade is not exposed.

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