KR101731054B1 - Drone - Google Patents

Abstract

The present invention provides a drone having a wing structure enabling a stable flight and a landing unit enabling a photographing device additionally mounted to be efficiently installed in the drone. According to an embodiment of the present invention, the drone includes one or more wing units around a main body, and the main body includes a coupling unit coupled to the wing unit. The wing unit includes: a connection unit for connection with the coupling unit; and the one or more wing units generating propulsion by being connected to the connection unit. The connection unit is coupled to or separated from the coupling unit and has a predetermined angle by using a connection means. The predetermined angle is changed by a user. Therefore, the drone enables the stable flight by being applied with a new wing structure. The drone also can be miniaturized in a transfer process of the drone by having the new wing structure and the landing unit and, therefore, can improve whole use efficiency of the drone.

Description

Drone {Drone}

BACKGROUND OF THE INVENTION Field of the Invention The present invention relates to a drone, which is an unmanned airplane, and more particularly, to a drones having a wing structure for enabling more stable operation and a landing means for efficiently mounting a photographing device, .

The drone, which was started in the recent military industry, refers to a plane or helicopter-shaped airplane flying by induction of radio waves without people burning.

Recently, drones have been widely used for military and commercial purposes.

However, due to the increase in demand for drones, it is expected that the drones will increase the traffic volume over the flights, thereby increasing the possibility of collision and collision during drone flight. In addition, there is a possibility that the drones may fall due to the causes such as unevenness of drones, battery discharge, and failure. In addition, an increase in the risk as described above due to the use of the drones may lead to personal injury or property damage.

In addition, the drones have recently been used in various fields such as logistics delivery, disaster relief, broadcasting and leisure, as well as military, due to various advantages such as simplicity, promptness and economical efficiency.

In addition, although the drones have many advantages, it is also realistic that there is a fear of falling due to changes in the external environment such as the wind and immaturity of the driving operation. And because the drones and their parts are so expensive, the economic damage caused by the drones' damage is inevitable.

Moreover, when a dron crashes, the risk of secondary damage to people and objects as well as the enormous economic damage caused by the breakage of the multi-copter drone itself is also serious.

For this reason, the stability of the drones has been emphasized, and in particular, how to design the structure of the drones' wings and landings is becoming an important issue for this stability.

That is, in designing the structure of the wing portion of the drones, it is necessary to consider both the problem that the drones rise or fall at the time of takeoff and landing and the operational problems that move in a specific direction after takeoff. Technology development is required.

Conventionally, the wing portion of the conventional drones is formed integrally with the main body. In the course of carrying the drones, the integral type always contains the risk of breakage and the development of the structure of the wing portion that can improve such a danger is required something to do.

Also, the landing part of the dron serves to stably maintain the dron body during take-off and landing of the dron. Especially, in the case of the recent drones, various types of photographing apparatuses are provided for aerial photographing. There has been a demand for development of a landing unit structure capable of efficiently mounting a photographing apparatus in a limited drone space.

For example, Korean Patent Laid-Open Publication No. 10-2014-0102584 discloses a multi-rotary wing unmanned aerial vehicle that can control the attitude and direction without adjusting the pitch of the rotor blades of an unmanned aerial vehicle, It is possible to prevent the occurrence of a fatal safety accident and to solve the problems caused by the rising air current around the rotor blades.

However, in the case of the conventional technology, only the structure of a rotor (rotary blade) that allows a stable operation by excluding a main rotor having a large structure is merely suggested, and the overall problem of the unmanned airplane There is still a problem in that it does not provide an alternative solution for solving the compatibility problem with other apparatuses (photographing apparatuses, etc.).

Therefore, development of a drone capable of efficiently solving the overall problem of the dron mentioned above is required.

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and it is an object of the present invention to provide a drones having a wing structure for stable operation and having a landing device for efficiently installing a photographing apparatus, The purpose is to provide.

According to an aspect of the present invention, there is provided a dron according to the present invention, the dron having at least one wing portion around a main body, the main body including a fastening portion to which the wing portion is fastened, And at least one vane unit coupled to the connection unit for generating driving force, wherein the connection unit has a predetermined angle through the connection unit and is fastened to or separated from the connection unit, And the predetermined angle is changed by the user.

The apparatus may further include a landing unit connected to the main body and supporting the main body from a ground when taking-off and landing, wherein the landing unit is provided in a pair facing each other, A second unit connected to the first unit, and a third unit connected to the second unit and contacting the ground.

The second unit is characterized in that the third unit is directed toward the paper surface direction or the body direction through the folding operation with the first unit.

Further, the first unit is changed to a state of being oriented in the direction of the paper surface according to the folding operation of the second unit or in a state of being parallel to the lower surface of the body.

Further, the main body includes a receiving means for receiving a predetermined device on a lower surface thereof, and the receiving means is coupled with the main body through the connecting means, and a fixing means for fixing the predetermined receiving device is formed .

Each of the one or more vane units includes a propeller and is coupled to the connection unit at a different angle of engagement such that a part of the rotation radius of each propeller overlaps.

In addition, each of the vane units is installed so that the angle of engagement of the vane units facing each other around the main body is the same.

According to the drones according to one aspect of the present invention, a stable operation can be achieved by adopting a new wing structure.

In addition, since the new wing structure and the landing unit are provided, it is possible to reduce the size of the dron during the transportation process, thereby improving the overall utilization efficiency of the drones.

In addition, it is possible to efficiently install additional equipment (photographing apparatus, etc.) mounted on the drone main body in a limited space, thereby improving the usability of the auxiliary equipment.

1 is a perspective view showing an external configuration of a drone according to an embodiment of the present invention.
FIG. 2 is a part of a perspective view illustrating the configuration of the wing portion of the drone and the fastening portion fastened thereto according to the embodiment of the present invention.
FIG. 3 is an exploded perspective view showing a wing structure of a drone and a fastening part to be fastened thereto according to an embodiment of the present invention.
Fig. 4 is a part of a perspective view showing the receiving means of the drone according to the embodiment of the present invention.
5 is a perspective view illustrating a dron with a landing portion according to another embodiment of the present invention.
FIG. 6 is a schematic view illustrating a landing portion provided on a drone according to another embodiment of the present invention.
7 is a perspective view illustrating a folded state of a landing portion of a dron according to another embodiment of the present invention.
8 is a schematic view showing a folded state of a landing portion provided on a drone according to another embodiment of the present invention.
FIG. 9 is a schematic view of a dron unit of a dron according to another embodiment of the present invention. FIG.

The objects, features and advantages of the present invention will become more apparent through the following examples.

The following specific structural or functional descriptions are merely illustrative for purposes of describing an embodiment according to the inventive concept, and it is to be understood that the embodiments according to the inventive concept may be embodied in various forms, It should not be construed as limited to the embodiments.

The embodiments according to the concept of the present invention can make various changes and have various forms, so that specific embodiments are described in detail in the specification or the drawings. It should be understood, however, that the embodiments according to the concept of the present invention are not intended to be limited to any particular mode of disclosure, but include all modifications, equivalents, and alternatives falling within the spirit and scope of the present invention.

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 it is mentioned that an element is "directly connected" or "directly connected" to another element, it should be understood that there are no other elements in between. Other expressions for describing the relationship between components should be interpreted as well.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The singular expressions include plural expressions unless the context clearly dictates otherwise.

It is to be understood that the terms such as " comprises "or" having "in this specification are intended to specify the presence of stated features, integers, But do not preclude the presence or addition of steps, operations, elements, parts, or combinations thereof.

Unless defined otherwise, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Terms such as those defined in commonly used dictionaries are to be interpreted as having a meaning consistent with the meaning of the context in the relevant art and, unless explicitly defined herein, are to be interpreted as ideal or overly formal Do not.

Hereinafter, the present invention will be described in detail with reference to the preferred embodiments of the present invention with reference to the accompanying drawings. Like reference symbols in the drawings denote like elements.

First, the overall construction of a drone according to an embodiment of the present invention will be described in detail below with reference to Fig.

1 is a perspective view showing an external configuration of a drone according to an embodiment of the present invention.

1 is a perspective view seen from the bottom of the drone 1 according to an embodiment of the present invention.

1, a drone 1 according to an embodiment of the present invention includes a main body 100, a wing portion 200, and a receiving means 300. As shown in FIG.

The main body 100 supports the entire drone 1, and the wing part 200 is connected to one side of the main body 100. 1, four wing portions 200 connected to the main body 100 are shown. In the case where the main body 100 has a rectangular parallelepiped shape as shown in FIG. 1, And each wing portion 200 may be provided facing each other. However, the body 100 may have a shape other than the rectangular parallelepiped, and the number of the wings 200 connected to the body 100 may vary.

In addition, various devices necessary for the operation of the drones 1 may be provided in the main body 100. That is, inside the main body 100, communication means for communicating with the steering means of the external driver, control means for controlling the operation of the drones 1, and the like may be provided.

As shown in FIG. 1, the main body 100 may have a fastening part 120 for fastening the wing part 200 stably. Here, the fastening part 120 may be formed perpendicular to one side surface of the main body 100 as a means for stably fastening the main body 100 and the wing part 200.

1, the wing unit 200 may include at least one wing unit 200, and includes a connection unit 210 and a wing unit 230. As shown in FIG. The connecting unit 210 is provided for fastening with the fastening part 120 of the main body 100 and the wing unit 230 is connected to the connecting unit 210 so as to generate a driving force for moving the dron 1 .

Also, the connecting unit 210 may be provided with connecting means, which can be fastened to the fastening part 120, which will be described in detail with reference to FIG. 2 to FIG.

In addition, one or more wing units 230 may be provided in one wing 200. That is, one or a plurality of vane units 230 may be connected to one connection unit 210. The number of such wing units 230 may affect the desired moving speed performance or directional switching performance of the drone 1.

In addition, a propeller 250 for generating a propelling force may be provided at an end of the vane unit 230. The propeller 250 can be formed in various forms in the blade unit 230. Generally the rotation axis is a direction in which the blade unit 230 extends and a direction in which the blade unit 230 is connected to the connection unit 210, As shown in Fig.

The storage means 300 may be coupled to the lower surface of the main body 100. The storage means 300 has a space in which a predetermined apparatus such as a camera, such as a photographing apparatus, is stored. Preferably, the housing means 300 may have the same shape as the main body 100 (in the shape of a rectangular parallelepiped like the main body 100 in FIG. 1) and extend in the downward direction.

Further, the housing means 300 can be coupled to or separated from the main body 100 through the fastening means 350. In addition, the receiving means 300 may be formed with a fixing means inside or outside which the predetermined devices to be additionally accommodated can be fixed. Fixing means (not shown) for stably mounting a photographing device such as a camera in the receiving means 300 may be formed on one side of the interior of the receiving means 300.

Next, the wing portion 200 of the dron 1 according to the embodiment of the present invention and the fastening portion 120 of the main body 100 fastened to the wing portion 200 will be described in detail below with reference to Figs. 2 to 3. Fig.

FIG. 2 is a perspective view illustrating a wing structure of a drone according to an embodiment of the present invention and a fastening unit to be fastened to the drone. FIG. 3 is a perspective view illustrating a structure of a wing of a drone and a fastening unit fastened thereto according to an embodiment of the present invention. FIG.

2, the wing portion 200 of the drone 1 according to the embodiment of the present invention includes the connecting means 205 in addition to the connecting unit 210, the wing unit 230 and the propeller 250 can do.

The connecting means 205 is a means for the wing portion 200 to be fastened to the fastening means 120 of the main body 100 and is formed to protrude from the connecting unit 210 as shown in Figures 2 to 3 . Further, a space into which the protruding connection means 205 can be inserted is formed on the fastening means 120.

That is, the wing portion 200 and the coupling portion 120 may be fastened to each other in such a manner that the coupling means 205 protruding from the coupling unit 210 is inserted into the groove formed in the coupling means 120. The connecting means 205 protruding from the connecting unit 210 and the grooves formed in the connecting means 120 are both male and female so that the connecting unit 210 and the connecting portion 120 can be fastened.

Depending on the shape of the groove formed in the connecting means 205 or the fastening means 120, the wing portion 200 can be fastened or separated while forming a predetermined angle with the fastening means 120. That is, it is preferable that the shape of the groove formed in the connecting means 205 or the fastening means 120 is such that the angle of engagement can be adjusted. For this purpose, the connecting means 205 may be of a type that can be moved up and down, and the grooves formed in the fastening means 120 may be formed with a plurality of groove spaces.

3, concrete means for connecting one or more wing units 250 (two wing units in FIG. 3) and the connecting means 205 may be provided inside the connecting unit 230 . It should be noted that the internal structure of the connection unit 230 shown in FIG. 3 is an example, and the internal structure is not essential.

Next, the receiving means 350 of the drones 1 according to the embodiment of the present invention will be described in detail with reference to Fig.

Fig. 4 is a part of a perspective view showing the receiving means of the drone according to the embodiment of the present invention.

4, the receiving means 300 may be coupled to the lower surface of the main body 100. As shown in FIG. Specifically, the housing unit 300 may be coupled to the lower surface of the main body 100 through the fastening means 350 with the same area as the lower surface of the main body 100. The fastening means 350 is provided with a fastening means 350 coupled to the main body 100 in such a manner that the fastening means 350 is engaged with or separated from the fastening portion formed at one side of the main body 100 and the fastening portion formed at one side of the housing means 300. [ .

The user of the dron 1 can conveniently mount or separate the storage means 300 to or from the drones 1 through this type of fastening means 350 to effectively compensate for the drawbacks of the difficult to transport drones 1 An effect that can be achieved can be achieved.

Next, a drone 1 having a landing part 400 according to another embodiment of the present invention will be described in detail below with reference to Figs. 5 to 8. Fig.

FIG. 5 is a perspective view of a drone having a landing portion according to another embodiment of the present invention, FIG. 6 is a schematic view illustrating a landing portion provided on a drone according to another embodiment of the present invention, FIG. FIG. 8 is a schematic view showing a folded state of a landing portion provided on a drone according to another embodiment of the present invention. FIG. 8 is a perspective view showing a folded state of a landing portion of a drone according to another embodiment.

As shown in FIG. 5, the drone 1 according to another embodiment of the present invention includes a landing part 400. The landing part 400 may be provided at least one part that stably supports the main body 100 from the ground at the time of taking-off and landing the drones 1, but in particular, Are minimized). The pair of landing parts 400 may be installed facing each other.

5, the landing unit 400 may be connected to one side of the main body 100 and extend to form a predetermined angle in the direction of the ground.

The landing unit 400 includes a first unit 410 connected to the main body 100, a second unit 420 connected to the first unit 410 and connected to the second unit 420, And a third unit 430 in contact with the ground.

In particular, the second unit 420 may be configured such that the third unit 430 is oriented in the direction of the paper surface or the main body 100 through the folding operation with the first unit 410. 6 to 8, the second unit 420 may be in line with the first unit 410 of two frames through the folding operation, or may be part of the first unit 410 of the first unit 410 Lt; / RTI > frames.

Through this folding operation, the second unit 420 can cause the third unit 430, which is in direct contact with the ground, to move to the vicinity of the main body 100 or to carry out the landing operation again toward the ground. In other words, as mentioned above, the dragon 1 usually has a drawback in that it is difficult to carry despite the importance of portability. The folding process of the landing unit 400 as described above can effectively improve the ease of movement and transportation .

Also, the folding operation of the second unit 420 may be performed while the drones are in operation after the take-off. In this case, a driving unit may be further provided on the landing unit 400. In this case, the resistance of the wind can be minimized when the drones 1 are operated, and the possibility of collision with an obstacle during operation can be remarkably reduced.

In addition, like the folding operation of the second unit 420, the first unit 410 can also be folded at the connection portion with the main body 100. That is, since the folding operation of only the second unit 420 can not achieve the optimum folding state of the landing unit 400, the first unit 410 also performs a folding operation at the connecting portion with the main body 100 So that the landing part 400 can be optimally folded as shown in FIG.

Further, the folding operation of the first unit 410 may be dependent on the folding operation of the second unit 420. [ That is, the folding operation of the first unit 410 can be performed in proportion to the folding operation (change in the folding angle) of the second unit 420, and the optimum folding state can be achieved through this operation.

Finally, the wing portion 200 of the drone 1 according to still another embodiment of the present invention will be described in detail below with reference to Fig.

FIG. 9 is a schematic view of a dron unit of a dron according to another embodiment of the present invention. FIG.

9, the wing of the drone 1 according to another embodiment of the present invention includes a propeller 250 provided at an end of one or more vane units 230-1, 230-2, and 230-3, -1, 250-2, and 250-3 may be partially overlapped with each other.

That is, the plurality of propellers 250-1, 250-2, and 250-3 provided in the plurality of vane units 230-1, 230-2, and 230-3 formed in one vane portion have rotation radii A plurality of propellers can be provided in a limited space while overlapping each other, so that more powerful propulsive force can be generated.

In other words, only by adjusting the coupling angle of the plurality of wing units 230-1, 230-2 and 230-3 with respect to the connection unit 210, the maximum number of propellers 250-1, 250-2, 250- 3). As a result, it is possible to achieve an effect of improving the vertical or lateral thrust force of the drone 1 as a whole.

However, in order to provide a plurality of propellers 250-1, 250-2, and 250-3, the coupling angle of the plurality of vane units 230-1, 230-2, and 230-3 to the coupling unit 210 is And can be adjusted according to the characteristics of the drone 1. In other words, although the propellers 250-1, 250-2 and 250-3 may be provided according to the adjustment of the coupling angle, the optimum wing units 230-1 and 230-2 may be provided in accordance with the forward, -2, and 230-3 may be determined.

That is, according to the provision of the plurality of vane units 230-1, 230-2, and 230-3, the overlapping of the turning radii of the propellers 250-1, 250-2, and 250-3 occurs, It will be possible to design within the extent that there will be no interference with the drone (1) operation.

Also, it is preferable that the number of the plurality of vane units 230-1, 230-2, and 230-3 provided in one vane unit 200 is an odd number as shown in FIG. 9, the position of the wing unit 230-2 located at the center among the three wing units 230-1, 230-2, and 230-3 (the angle of engagement with the connecting unit 210) It is preferable to make the blade units different from the blade units located on both sides.

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, It will be understood. The embodiments described above are therefore to be considered in all respects as illustrative and not restrictive.

1: Drone 100: Body
120: fastening part 200: wing part
210: connecting unit
230, 230-1, 230-2, 230-3: wing unit
250, 250-2, 250-2, 250-3: Propeller
300: storage means
350: fastening means 400:
410: first unit 420: second unit
430: the third unit

Claims (7)

In a dron with at least one wing portion centered on the body,
Wherein the main body includes a fastening portion to which the wing portion is fastened,
Wherein the wing portion includes a connecting unit for fastening with the fastening portion and at least one wing unit coupled to the connecting unit to generate a propulsive force,
Wherein the connecting unit is engaged or disconnected with the connecting portion at a predetermined angle through the connecting means, the predetermined angle is changed by the user,
The main body includes a receiving means for receiving a predetermined device on a lower surface thereof,
The storage means is formed with fixing means to be coupled to the main body through the fastening means and to fix the predetermined device to be stored therein,
Wherein each of said one or more vane units includes a propeller and is coupled to said connection unit at a different angle of engagement such that a portion of the turning radius of each propeller overlaps to alter forward and backward propulsion or up-
Wherein each of the vane units is installed so that the angle of engagement of the vane units facing each other around the main body is the same . The method according to claim 1,
And a landing unit connected to the main body and supporting the main body from the ground during take-off and landing,
The landing unit includes a first unit connected to the main body, a second unit connected to the first unit, and a third unit connected to the second unit, the third unit being in contact with the ground, The drones being characterized in that: 3. The method of claim 2,
Wherein the second unit directs the third unit toward the paper surface direction or the body direction through a folding operation with the first unit.
The method of claim 3,
Wherein the first unit is changed to a state of being oriented in the direction of the paper surface according to a folding operation of the second unit or parallel to a lower surface of the body. delete delete delete

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