KR20170114353A - Multi-rotor drone - Google Patents

Abstract

And a safety device capable of protecting the photographic equipment mounted on the multi-rotor wing drones and the multi-rotor wing drones when the multi-rotor wing drones fall down. Wherein the multi-rotor wing dron comprises a body of an aircraft, a plurality of rotors connected to the body of the aircraft, a drag chute mounted on the body of the aircraft, a shock mounted on at least one of a lower portion of the aircraft body or a side portion of the aircraft body Wherein the drag chute is set to unfold when the crash of the aircraft body is detected by the detection sensor and the shock absorber is set to be inflated, do.

Description

Multi-rotor drone}

The present invention relates to a multi-rotor blade drones, and more particularly, to a multi-rotor blade drones including a safety device capable of protecting a UAV from a collision or the like caused by a fall during a fall of the UAV.

In the case of a general multi-rotor wicket drones, it is easy to carry because of its light weight, and is applied to various fields such as aerial photographing, low-speed reconnaissance search, light cargo transportation, and disaster relief work.

Multi-rotor wing drones can fly in dangerous areas using manned aircraft, or in areas where large manned aircraft are difficult to fly, such as in downtown areas. In addition, since the multi-rotor wing drones can be manufactured in a much smaller size than the manned aircraft, the manufacturing and operation costs are greatly advantageous compared to the manned aircraft. For this reason, unmanned multi - rotor wing drones can be used more often as an imaging system for image data acquisition than manned aircraft.

However, it may happen that a multi-rotor wing drones are defective or fall due to external environmental causes during flight. For example, inefficient operation or inoperability of multi-rotor wing drones may be the reason for multi-rotor wing drones to fall. Alternatively, multiple flywheel drones may be powered down, so that multiple flywheel drones may fall if they are out of control due to electronic errors. And, multi-rotor wing drones may fall due to wind speed or meteorological causes.

The multi-rotor blade drone is manufactured in small size and lightweight, and can be repaired at relatively low cost even if a part of the multi-rotor blade drone is damaged due to the multi-rotor blade dron crashes and collides with the ground. However, since the photographing devices mounted on the multi-rotor blade drones for image photographing are generally high-priced high-priced products and are weak electronic devices, if the photographing device is broken due to the fall of the multi-rotor blade dron, There is a concern.

In addition, even if the multi-rotor blade drones are manufactured in small size and light weight, if multi-rotor blade drones fall in population-densely populated areas, personal injury may occur.

Korean Patent Publication No. 10-2011-0111127

SUMMARY OF THE INVENTION It is an object of the present invention to provide a multi-rotor blade dron including a safety device capable of protecting a photographic equipment mounted on a multi-rotor blade drones and a multi-rotor blade dron when the multi-rotor blade drones fall.

The problems to be solved by the present invention are not limited to the above-mentioned problems, and other matters not mentioned can be clearly understood by those skilled in the art from the following description.

According to an aspect of the present invention, there is provided a multi-rotor rotor drones comprising an aircraft body, a plurality of rotors connected to the aircraft body, a drag chute mounted on the upper portion of the aircraft body, And a detection sensor for detecting a fall of the aircraft body, wherein when a fall of the aircraft body is detected by the detection sensor, the drag chute Is set to be unfolded, and the shock absorbing device is set to be inflated.

The multi-rotor blade drones according to some embodiments of the present invention may further include a landing portion formed at a lower portion of the aircraft body, and the shock-absorbing device is mounted to the landing portion.

In a multi-rotor wick drones according to some embodiments of the present invention, the shock-absorbing device comprises an airbag.

In a multi-rotor blade drones according to some embodiments of the present invention, the sensing sensor includes at least one of an acceleration sensor or a barometric sensor.

In a multi-rotor blade drones according to some embodiments of the present invention, a first battery that supplies power to operate the rotor, and a second battery that supplies power to operate the drag chute and the shock-absorbing device.

In a multi-rotor blade drones according to some embodiments of the present invention, the rotor, the drag chute, and the battery supplying power to operate the shock-absorbing device are included.

The multi-rotor blade drones according to some embodiments of the present invention may further include a control unit for controlling the flight of the aircraft body, wherein the drag chute is set to be unfolded by the signal of the control unit, do.

Other specific details of the invention are included in the detailed description and drawings.

Figure 1 is an exemplary illustration of the appearance of a multiple rotor blade drones in accordance with some embodiments of the present invention.
2 is a block diagram illustrating exemplary components for flight of a multi-rotor wing drones in accordance with some embodiments of the present invention.
FIGS. 3 and 4 show a multi-rotor blade drones according to some embodiments of the present invention.
5 is a view showing a state in which the safety device of Figs. 3 and 4 is developed.
Figure 6 is a view of a multi-rotor blade drones with a safety device in accordance with some embodiments of the present invention.
FIG. 7 is a view showing a state in which the safety device of FIG. 6 is deployed.
Figure 8 is a view of a multi-rotor wing drones according to some embodiments of the present invention.
Fig. 9 is a view showing a state in which the safety device of Fig. 8 is deployed.
10 is a block diagram that illustrates exemplary components for flying a multi-rotor wing drones in accordance with some embodiments of the present invention.

BRIEF DESCRIPTION OF THE DRAWINGS The advantages and features of the present invention and the manner of achieving them will become apparent with reference to the embodiments described in detail below with reference to the accompanying drawings. The present invention may, however, be embodied in many different forms and should not be construed as being limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Is provided to fully convey the scope of the invention to those skilled in the art, and the invention is only defined by the scope of the claims. Like reference numerals refer to like elements throughout the specification.

One element is referred to as being "connected to " or" coupled to "another element, either directly connected or coupled to another element, One case. On the other hand, when one element is referred to as being "directly connected to" or "directly coupled to " another element, it does not intervene another element in the middle. Like reference numerals refer to like elements throughout the specification. "And / or" include each and every combination of one or more of the mentioned items.

Although the first, second, etc. are used to describe various elements, components and / or sections, it is needless to say that these elements, components and / or sections are not limited by these terms. These terms are only used to distinguish one element, element or section from another element, element or section. Therefore, it goes without saying that the first element, the first element or the first section mentioned below may be the second element, the second element or the second section within the technical spirit of the present invention.

The terminology used herein is for the purpose of illustrating embodiments and is not intended to be limiting of the present invention. In the present specification, the singular form includes plural forms unless otherwise specified in the specification. It is noted that the terms "comprises" and / or "comprising" used in the specification are intended to be inclusive in a manner similar to the components, steps, operations, and / Or additions.

Unless defined otherwise, all terms (including technical and scientific terms) used herein may be used in a sense commonly understood by one of ordinary skill in the art to which this invention belongs. Also, commonly used predefined terms are not ideally or excessively interpreted unless explicitly defined otherwise.

Figure 1 is an exemplary illustration of the appearance of a multiple rotor blade drones in accordance with some embodiments of the present invention. 2 is a block diagram illustrating exemplary components for flight of a multi-rotor wing drones in accordance with some embodiments of the present invention. FIGS. 3 and 4 show a multi-rotor blade drones according to some embodiments of the present invention. 5 is a view showing a state in which the safety device of Figs. 3 and 4 is developed.

For convenience of explanation, FIG. 1 shows an appearance of the multi-rotor blade drones except for the safety device for protecting the multi-rotor blade drones.

The multi-rotor blade drones according to some embodiments of the present invention are illustrated as including four rotors and four rotor motors, but are for ease of description only, but are not limited thereto.

Unlike what is shown, the multi-rotor blade drones may include three or more rotors and rotor motors.

1 to 5, a multi-rotor blade drones 100 according to some embodiments of the present invention includes an aircraft body 110, a landing unit 130, a control unit 105, a plurality of rotor motors 115 A plurality of rotors 120, a drag chute 150, and an impact damping device 160. [0035]

The aircraft body 110 may be located at the center of the multi-rotor blade drones 100.

In FIG. 1, the aircraft body 110 has been shown to have a shape X, but is not limited thereto.

The plurality of rotor motors 115 may be disposed at an end portion of the aircraft body 110 extending in one direction, respectively.

Although a part of each of the plurality of rotor motors 115 is shown as being inserted in the aircraft body 110, it is for convenience of explanation only, and is not limited thereto.

The plurality of rotors 120 may be rotatably attached to the plurality of rotor motors 115, respectively. Each of the plurality of rotors 120 can rotate about the rotational axis of each of the plurality of rotor motors 115. [

Each of the plurality of rotors 120 may be connected to the aircraft body 110. Each of the plurality of rotors 120 may be connected to the aircraft body 110 via a plurality of rotor motors 115.

The landing portion 130 may be formed at a lower portion of the aircraft body 110. The landing portion 130 may be used for normal takeoff and landing of the multi-rotor blade drones 100, but is not limited thereto.

The photographing apparatus 200 can be disposed at a lower portion of the aircraft body 110. The photographing apparatus 200 may be located at a position where the center of gravity of the aircraft body 110 is located, but is not limited thereto.

For example, the photographing apparatus 200 can be used for identifying the flight path and destination of the multi-rotor drones 100 and the like. Alternatively, the photographing apparatus 200 can be used for photographing an object or the like on the ground as an image or a photograph.

The drag chute 150 may be mounted on the upper portion of the aircraft body 110. The drag chute 150 may be located at a position where the center of gravity of the aircraft body 110 is located, but is not limited thereto.

The drag chute 150 may be mounted on the upper portion of the aircraft body 110 to maintain the balance of the aircraft body 110 when the multi-rotor drones 100 crash. In order to prevent the aircraft body 110 from rotating during the fall of the multi-rotor drones 100 and to maintain the posture of the aircraft body 110, the drag chute 150 is mounted on the upper portion of the aircraft body 110 Can be located.

3, the drag chute 150 is shown attached to the outside of the aircraft body 110, but is not limited thereto. Needless to say, the drag chute 150 can be inserted into the inside of the aircraft body 110.

The shock absorber 160 may be mounted on the lower portion of the aircraft body 110. The shock absorber 160 may, for example, include, but is not limited to, an air bag.

The multi-rotor blade drones 100 may include at least one or more shock absorbing devices 160. That is, at least one shock absorber 160 may be mounted on the lower portion of the aircraft body 110.

In FIG. 4, the shock absorber 160 is shown attached to the outside of the aircraft body 110, but is not limited thereto. It will be appreciated that the shock absorber 160 may be contained within the aircraft body 110.

Further, although the shock absorber 160 is illustrated as being mounted on the rotor arm portion of the aircraft body 110 extending in one direction, it is for convenience of explanation, but is not limited thereto.

In addition, although the shock absorber 160 is illustrated as being mounted in correspondence with each of the plurality of rotor motors 115, it is for convenience of explanation only, and is not limited thereto.

The description of the operation of the drag chute 150 and the shock-absorbing device 160 will be described later with reference to Figs. 2 and 5.

The control unit 105 can control the flight of the multi-rotor drones 100 using a signal input from the user 50. [ The control unit 105 can control the flight of the aircraft body 110.

The control unit 105 can control the plurality of rotor motors 115 using the signals input from the user 50. [ Each of the plurality of rotor motors 115 can be controlled by the control unit 105.

In addition, the control unit 105 can operate the drag chute 150 and the shock-absorbing device 160 using the signal of the sensing sensor 140. [ Further, the control unit 105 can operate the drag chute 150 and the shock-absorbing device 160 using the signal input from the user 50. [

More specifically, by the signal of the control unit 105, the drag chute 150 can be set to unfold. Further, by the signal from the control unit 105, the shock-absorbing device 160 can be set to be expanded.

The control unit 105 may be disposed in the aircraft body 110, but is not limited thereto.

The detection sensor 140 may sense a fall of the multi-rotor blade drones 100. [ For example, the detection sensor 140 may provide a signal to the control unit 105 regarding a fall of the aircraft body 110 when a fall of the aircraft body 110 is detected. Using the signal input from the sensing sensor 140, the control unit 105 can operate the drag chute 150 and the shock absorber 160.

In other words, when a fall of the aircraft body 110 is detected by the sensing sensor 140, the drag chute 150 is set to unfold, and the shock-absorbing device 160 can be set to be inflated.

The sensing sensor 140 may include, for example, at least one of an acceleration sensor or a barometric sensor.

The drag chute 150 is unfolded and the shock absorbing device 160 can be expanded when the acceleration in the gravity direction of the multi-rotor blade drones 100 measured by the acceleration sensor is maintained for a predetermined time or more.

Here, the set acceleration may be less than or equal to the acceleration measured when the multi-rotor blade dron 100 drops freely in the direction of gravity.

Alternatively, when the atmospheric pressure measured by the barometric sensor changes to a value that is set within a set time, the drag chute 150 is unfolded and the shock-absorbing device 160 can be inflated.

The first battery 125 may supply power to the control unit 105, the rotor motor 115, the sensing sensor 140, the drag chute 125, and the shock- The first battery 125 can supply electric power for operating the rotor motor 115, the drag chute 125, and the shock-absorbing device 160.

In FIGS. 2 and 5, the sensing sensor 140 may sense a fall of the aircraft body 110. The sensing sensor 140 sensing the fall of the aircraft body 110 may provide the control unit 110 with a signal for the fall of the multi-rotor blade drones 100.

The control unit 105 receiving a signal for the fall may provide a signal to the drag chute 150 so that the drag chute 150 is unfolded. In addition, the control unit 105 may provide a signal to the shock-absorbing device 160 so that the shock-absorbing device 160 is unfolded.

The deployed drag chute 150 can reduce the fall speed of the multi-rotor blade drones 100. In addition, the deployed drag chute 150 can maintain posture balance of the aircraft body 110 during a crash.

The expanded shock absorbing device 160 may reduce the amount of impact experienced by the multi-rotor blade drones 100 when contacting the ground. When in contact with the ground, the inflated shock absorber 160 can absorb the impact.

The inflated shock absorber 160 may be configured to first contact the ground or impact point of the landing unit 130 or the photographing apparatus 200 so that the inflated shock absorber 160 can effectively absorb the impact .

Meanwhile, during the flight of the multi-rotor blade drones 100, the multi-rotor blade drums 100 may collide with other objects, or the rotor motors 115 may be stopped.

When the user 50 observes such a situation or an emergency signal is transmitted to the user 50 by the control unit 105, the user 50 sends the drag chute 150 and the shock damping device Lt; RTI ID = 0.0 > 160 < / RTI >

When the user 50 inputs a signal related to the operation of the drag chute 150 and the shock absorbing device 160, the control unit 105 controls the shock absorbing device 160 such that the shock absorbing device 160 is unfolded Signal.

Figure 6 is a view of a multi-rotor blade drones with a safety device in accordance with some embodiments of the present invention. FIG. 7 is a view showing a state in which the safety device of FIG. 6 is deployed.

For convenience of explanation, the differences from those described with reference to Figs. 1 to 5 will mainly be described.

Referring to FIGS. 6 and 7, in the multi-rotor blade drones 100 according to some embodiments of the present invention, the shock-absorbing device 160 may be mounted to the landing portion 130.

Although the shock absorber 160 is illustrated as being within the landing 130, it is not limited thereto. It goes without saying that the shock absorbing device 160 may be attached to the lowermost portion of the landing portion 130.

2 and 7, when the sensing sensor 140 senses a fall of the aircraft body 110, the inflated shock absorber 160 may first contact the land or impact point of the landing 130 . In this way, the inflated shock absorber 160 can absorb the impact.

Figure 8 is a view of a multi-rotor wing drones according to some embodiments of the present invention. Fig. 9 is a view showing a state in which the safety device of Fig. 8 is deployed.

For convenience of explanation, the differences from those described with reference to Figs. 1 to 5 will mainly be described.

8 and 9, in the multi-rotor blade drones 100 according to some embodiments of the present invention, the shock-absorbing device 160 may be mounted to the side of the aircraft body 110.

When the detection sensor 140 detects a fall of the aircraft body 110, the shock-absorbing device 160 may be inflated.

Even if the shock absorbing device 160 is mounted on the side of the aircraft body 110, the expanded shock absorbing device 160 may be more likely to contact the ground or impact point than the landing part 130 or the photographing device 200 Lt; / RTI >

10 is a block diagram that illustrates exemplary components for flying a multi-rotor wing drones in accordance with some embodiments of the present invention.

For convenience of explanation, the differences from those described with reference to Figs. 1 to 5 will mainly be described.

Referring to FIG. 10, the multi-rotor blade drones 100 according to some embodiments of the present invention may further include a second battery 126.

The first battery 125 can supply power to the control unit 105, the rotor motor 115, and the sensing sensor 140. The first battery 125 can supply electric power for operating the rotor motor 115 to the rotor motor 115. [

Meanwhile, the second battery 126 can supply electric power to the drag chute 125 and the shock-absorbing device 160. [ That is, the second battery 126 can supply the drag chute 125 and the power for operating the shock-absorbing device 160 to the drag chute 125 and the shock-absorbing device 160.

The multi-rotor blade drones 100 may be generated, for example, by depletion of the first battery 125. [ In such a case, the operation of the drag chute 125 and the shock-absorbing device 160 may not be feasible.

In order to prevent such a situation, the multi-rotor blade drones 100 may further include a drag chute 125 and a second battery 126, which is an auxiliary battery for operation of the shock-absorbing device 160.

While the present invention has been described in connection with what is presently considered to be practical exemplary embodiments, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, You will understand. It is therefore to be understood that the above-described embodiments are illustrative in all aspects and not restrictive.

100: multi-rotor wing drones 110: aircraft fuselage
115: rotor motor 120: rotor
150: drag suit 160: shock absorber

Claims (7)

Aircraft fuselage;
A plurality of rotors connected to the aircraft body;
A drag chute mounted on an upper portion of the aircraft body;
A shock absorbing device mounted on at least one of a lower portion of the aircraft body or a side portion of the aircraft body; And
And a detection sensor for detecting a fall of the aircraft body,
Wherein the drag chute is set to unfold when the crash of the aircraft body is detected by the detection sensor, and wherein the shock absorbing device is configured to be inflated. The method according to claim 1,
Further comprising a landing formed at a lower portion of the aircraft body,
Wherein the shock absorbing device is mounted on the landing portion. The method according to claim 1,
Wherein the shock absorbing device comprises an air bag. The method according to claim 1,
Wherein the sensing sensor comprises at least one of an acceleration sensor or a barometric sensor. The method according to claim 1,
A first battery for supplying power to operate the rotor; and a second battery for supplying power to operate the drag chute and the shock absorbing device. The method according to claim 1,
And a battery for supplying power to operate the rotor, the drag chute, and the shock absorbing device. The method according to claim 1,
Further comprising a control unit for controlling the flight of the aircraft body,
The drag chute is set to unfold by the signal of the control unit, and the shock damping device is set to expand.

Images