KR101808855B1 - Self-assembly aircraft of flight environment - Google Patents

Abstract

The present invention relates to a prefabricated airframe according to flight management, including: a main wing portion fixed to a fuselage; and an additional wing portion including a first wing portion and a second wing portion detachably coupled to left and right sides of the main wing portion, respectively, and configured to be additionally couplable between the main wing portion and the first wing portion and between the main wing portion and the second wing portion according to a flight environment of a prefabricated airframe.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a self-

The present invention relates to a prefabricated gas according to a flying environment.

Recently, various types of unmanned aerial vehicles have been developed. As interest in small unmanned aerial vehicles has increased, research on application of civilian industry has been increasing. However, due to limited operating environment and limited operating time, utilization in private industry is very low . Combining the advantages of a fixed-wing aircraft that can be operated in extreme environments, maximizing operating radius and time, and the advantages of a rotary-wing aircraft that allows vertical landing and landing in a limited space, And high-intensity, light-weighting technology and control system are required to overcome the constraint of the running time.

An object of the present invention is to provide a prefabricated airframe which can be configured differently according to the purpose of utilization of a prefabricated gas and a flight operating environment by a user.

Further, it is an object of the present invention to provide a prefabricated airframe which can be assembled according to flight operation so as to enable efficient flight even in a limited space.

According to an embodiment of the present invention, the prefabricated airframe includes a main wing portion fixed to the body, a first wing portion and a second wing portion detachably coupled to the left and right sides of the main wing portion, respectively, And an additional wing portion that can be additionally coupled between the main wing portion and the first wing portion and between the main wing portion and the second wing portion according to a flying environment of the gas.

The additional wing according to an embodiment of the present invention includes a fixed wing frame extending a wing length of the prefabricated base.

The additional wing according to an embodiment of the present invention is characterized by including a rotor blade frame including a plurality of vertical flying rotors that generate lifting force for ascending flight including a rotor blade and a motor.

The additional wing according to an embodiment of the present invention further comprises a rotor blade frame coupled to the stator frame and including a plurality of vertical flight rotors including a rotor and a motor to generate lift for ascending flight .

According to an embodiment of the present invention, the prefabricated gas includes a joint spa installed on left and right sides of the main wing, and the rotor blade frame includes a through hole through which the joint spa can pass.

The rotor blade frame according to an embodiment of the present invention includes a power supply unit for supplying power to the plurality of vertical flying rotors, and the main wing unit is characterized by being free from a power line connected to the additional wing unit .

According to an embodiment of the present invention, the plurality of vertical flying rotors include ESC (Electronic Speed Control) for controlling the rotation speed of the motor.

The prefabricated gas according to an embodiment of the present invention includes a propelling frame including a rotor and a motor, and a forward flight rotor for generating propulsive force for forward flight.

The moving body according to an embodiment of the present invention may include a control unit for controlling driving of the forward flight rotor and the plurality of vertical flight rotors in accordance with a flight mode of the prefabricated vehicle including a vertical flight mode and a horizontal flight mode .

The main wing according to an embodiment of the present invention includes a connector transmission terminal connected to the control unit through a communication line to output a control signal for the plurality of vertical flying rotors, And a connector receiving terminal electrically connected to the connector transmitting terminal and receiving the control signal when connected to the main wing.

The moving body according to an embodiment of the present invention may include a wireless communication unit that transmits control signals of the control unit to the plurality of vertical flight rotors to the plurality of vertical flight rotors, And a wireless communication unit for receiving the control signal of the control unit.

The controller may gradually increase the rotational speed of the forward flight rotor to generate a propulsive force for forward flight while gradually decreasing the rotational speed of the plurality of vertical flight rotors And the flywheel of the vertical flight rotor is aligned with the forward direction to switch the flight mode of the prefabricated aircraft from the ascending flight mode to the forward flight mode.

The control unit according to an embodiment of the present invention is characterized in that the rotor blade of the forward flight rotor is aligned in a direction perpendicular to the ground when entering the vertical flight mode.

FIG. 1 is a schematic view illustrating a fixed blade structure of a prefabricated gas according to an embodiment of the present invention.
FIG. 2 is a schematic view of a wing structure of a prefabricated airframe including a fixed-wing frame according to an embodiment of the present invention.
3 is a schematic view of a wing structure of a prefabricated airframe including a rotor blade frame according to an embodiment of the present invention.
FIG. 4 is a schematic view of a wing structure of a prefabricated airframe including a stator frame and a rotor frame according to an embodiment of the present invention. Referring to FIG.
FIG. 5 is a perspective view of a prefabricated airframe including a rotor blades according to an embodiment of the present invention. FIG.
6 is a flowchart illustrating a flight mode of a prefabricated vehicle including a rotor blades frame according to an embodiment of the present invention.
FIG. 7 is a view schematically showing an inner structure of a rotor blades frame, a moving body, and a propelling frame according to an embodiment of the present invention.
8A is a schematic view illustrating a basic wing structure of a prefabricated gas according to an embodiment of the present invention.
8B is a schematic view illustrating a wing structure including a fixed-wing frame according to an embodiment of the present invention.
FIG. 9A is a schematic view illustrating a blade structure including a rotor blade frame according to an embodiment of the present invention.
FIG. 9B is a schematic view illustrating a wing structure including a fixed-wing frame and a rotor-blade frame according to an embodiment of the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings in order to clarify the technical idea of the present invention. In the following description of the present invention, a detailed description of known functions and configurations incorporated herein will be omitted when it may make the subject matter of the present invention rather unclear. BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a block diagram of a computer system according to an embodiment of the present invention; Fig.

1 is a view schematically showing the configuration of a fixed blade 10 of a prefabricated gas according to an embodiment of the present invention. Referring to FIG. 1, a wing 10 fixed to a prefabricated base according to an embodiment of the present invention includes a main wing 100 disposed at the center of a body of the prefabricated base, And a first wing portion 110 and a second wing portion 120 that are respectively disposed on left and right sides of the main wing portion 100 and are coupled to the main wing portion 100. [ The configuration of FIG. 1 may be configured as a cross section as shown in FIG. 8A. The main wing portion 100 may be fixed to the upper portion of the moving body by one frame as shown in FIG. 5, or may extend from the left and right sides of the moving body by a plurality of frames, respectively. The main wing portion 100 and the first and second wing portions 110 and 120 may be coupled using the joint springs 100a and 100b as shown in FIG. It is possible to provide an unmanned airplane in which the wing is constructed in a prefabricated manner, which is easy to carry and which is easy to assemble by a simple coupling method.

According to an embodiment, the prefabricated airframe may be coupled to the body of the prefabricated airframe with the first and second wings 110 and 120 without the main wing 100. In this case, the body may have joint spas on the left and right sides for coupling the first and second wing parts 110 and 120.

In one embodiment, additional wings, such as wings or wings, may additionally be coupled between the main wing 100 and the first and second wings 110, 120. The type and number of additional wings to be combined may depend on the flight environment in which the prefabricated aircraft is operating.

FIG. 2 is a view schematically showing a configuration of a wing 30 of a prefabricated airframe including a fixed-wing frame according to an embodiment of the present invention. The description overlapping with FIG. 1 will be omitted. Referring to FIG. 2, the prefabricated wing includes a fixed wing frame 101, 102 for extending the wing of the prefabricated gas between the main wing 100 and the first and second wing portions 110, 120. The wing frame 101 and 102 also include joint springs 101a and 102a for coupling with the first and second wing parts 110 and 120 like the main wing part 100. [

In addition to the design for stable flight in aircraft design, it is also important to consider the payload or mission weight suitable for the flight mission. Therefore, if the blade length of the prefabricated airframe increases as the wing frames 101 and 102 are coupled, As the area increases and the wing loading of the prefabricated gas increases, the weight at which the prefabricated gas can be lifted increases. The user can engage the fixed-wing frames 101, 102 with the basic prefabricated airframe when performing a task of loading and moving heavy loads. According to the embodiment, when the high-strength and lightweight fixed-wing frames 101 and 102 are combined, the weight of the prefabricated gas itself is reduced at the same anonymous load, so that the flight time is increased and the payload is increased.

FIG. 3 is a schematic view showing a configuration of a wing 20 of a prefabricated airframe including a rotor blades frame according to an embodiment of the present invention. Fig. 5 is a three-dimensional representation of the wing configuration of Fig. 3 and 5, a prefabricated base 20 including a rotor blade frame according to an embodiment of the present invention includes a main rotor 100 and a first rotor blade 110 and a second rotor blade 120, (210, 220). The rotary-wing frames 210 and 220 may be installed in a direction perpendicular to the body as shown in FIG. 5, but are not limited thereto.

As shown in FIG. 9A, the rotor frames 210 and 220 may have four vertical flights. The user can set various numbers of vertical flying rotors of the rotor blades 210 and 220 according to the need and can freely mount any portion of the assembly type airframe other than the main blade 100 according to the user's convenience.

Vertical flight rotors can generate lifting for elevating flights, including ESC (Electronic Speed Control) to control the speed of the rotor, motor, and motor. According to the embodiment, the ESC is not included in the vertical flight rotor of the rotor blades 210 and 220 but may be included in the rotor and drive the motor through wired / wireless communication.

The rotating blade frames 210 and 220 include through holes 210a and 220a through which the joint springs 100a and 100b can penetrate in the center. The joint springs 100a and 100b may pass through the through holes so that the rotor blade frames 210 and 220 can be coupled between the main wing portion 100 and the first and second wing portions 110 and 120. Further, the rotor frame 210, 220 can be coupled between the main wing 100 and the fixed-wick frame 101, which is additionally coupled.

FIG. 4 is a view schematically showing a configuration of a wing 40 of a prefabricated airframe including a fixed-wing frame and a rotor-blade frame according to an embodiment of the present invention. The description overlapping with FIG. 2 will be omitted. Referring to FIG. 4, the wings of the prefabricated body may be provided with the rotor blades 210 and 220 between the main wing 100 and the fixed blade frames 101 and 102. That is, the rotor blade frame can be coupled to the rotor blade frame.

4, the fixed blade frame 101 may be sequentially coupled after the rotor blade frames 210 and 220 are coupled between the main blade unit 100 and the first and second blade units 110 and 120. On the contrary, After the stator frame 101 is coupled, the rotor blades 210 and 220 may be engaged.

According to the embodiment, the prefabricated gas combining both of the flywheel frames 210 and 220 and the fixed-wing frames 101 and 102 may be suitable for taking heavy weight and attempting to take off in a limited space. For example, in the case of a mountainous region or an island where a runway for takeoff and landing is limited and a distance is long, efficient flight can be achieved when both the flywheel frames 210 and 220 and the fixed wing frames 101 and 102 are provided .

As shown in FIG. 5, the prefabricated airframe may include an impulse force frame 140 having one end connected to the fuselage end in a direction perpendicular to the ground. The direction perpendicular to the ground does not necessarily mean that the earth and the frame form 90 degrees, and the other end of the propulsion frame extends in the direction away from the earth. The propulsion frame includes a forward flight rotor that includes an ESC (Electronic Speed Control) that controls the speed of the flywheel, the motor, and the motor at the other end. This creates a propulsive force for forward flight, allowing forward flight of the prefabricated aircraft. According to the embodiment, the ESC is not included in the forward flight rotor of the rotor blades 210 and 220, but may be included in the fuselage to drive the motor through wired / wireless communication.

According to the embodiment, the rotor blades 210 and 220 may include a power supply unit that supplies power to the vertical flight rotor. For example, the power supply is a detachable battery. In this case, the main wing portion may have no power line connected to the additional wing portion. This allows the weight of the prefabricated airframe to be reduced if the rotor frame is not assembled to the prefabricated airframe. As another example, it is also possible to use a power supply line connected to the additional wing portion in the main wing portion so as to use either the battery provided in the rotor blade frame or the power provided in the fuselage as the main power source, Can be used as power source.

According to the embodiment, the control unit 131 of the body 130 controls the driving of the plurality of vertical flying rotors and the forward flight rotor in accordance with the flight board of the assembly type airframe including the vertical flight mode and the horizontal flight mode. This can be achieved by receiving a control signal transmitted from the wireless communication unit 132 of the body 130 by a plurality of vertical flight rotors and a wireless communication unit mounted on the forward flight rotor. When the wireless communication units of the plurality of vertical flight rotors and the forward flight rotor receive the control signal, the ESC controls the speed of the motor to determine the movement of the rotor blades. When the control signal is received by the wireless communication, a separate communication line may not be required between the main wing unit 100 connected to the rotor blades 210 and 220 including a plurality of vertical flying rotors.

According to another embodiment, the main wing section 100 may include a connector transmission terminal for outputting control signals for a plurality of vertical flying rotors. The connector transmitting terminal is connected to the control unit 131 of the body 130 through a communication line. According to the embodiment, the rotating blade frames 210 and 220 are connected to the plurality of vertical flying rotors through a communication line, Terminal to receive the control signal. Since the control signal sent from the control unit 131 of the body 130 can be connected wirelessly or through a single connection line, a user who wishes to use the prefabricated gas can easily make a wing of a prefabricated gas You can.

The rotor blades (210, 220) are provided with a propelling frame (140) including a forward flight rotor for generating a propelling force for forward flight, including a wireless communication unit, so that the prefabricated airframe having fixed blades can be advanced.

According to the embodiment, as shown in FIG. 8B, the removable fixed-frame frames 101 and 102 can be adjusted in weight and length depending on the needs of the user, so that the assembled gas can be loaded.

 Since the fixed-wing frames 101 and 102 are also detachable, the user can determine whether to use the fixed-wing frames 101 and 102 according to the method of using the assembling aircraft.

FIG. 6 is a flowchart illustrating a flight mode of a prefabricated airframe including a rotor blades according to an embodiment of the present invention. FIG. 7 is a view illustrating an internal configuration of a rotor blades, a body, and a propulsion frame according to an embodiment of the present invention. Fig. Referring to FIGS. 5 and 6, a description will be given of a method of operating the assembled base having the rotor blades 210 and 220. FIG.

When a plurality of vertical flying rotors provided in the rotor blade frames 201 and 220 are driven and the rotor blades of the forward flight rotor provided in the propelling frame 140 are aligned in a direction perpendicular to the ground And the prefabricated gas rises vertically.

When the prefabricated gas reaches a certain height, the plurality of vertical flights rotates at a rotation speed of 0 m / s under the control of the control unit 131 and then stops. The forward flight rotor, which is aligned in a direction perpendicular to the earth during stopping flight, gradually increases the number of rotations to generate propulsion for forward flight. When the forward flight rotor reaches a speed range in which propulsion for forward flight is attained, the plurality of vertical flight rotors gradually decrease the rotation speed, and when the prefabricated forward flight, the plurality of vertical flight rotors travel forward Align the rotor blade in a direction parallel to the fuselage to reduce the drag generated by the rotor. Thus, it is said that the flight mode of the prefabricated airplane changes from vertical flight mode to forward flight mode, from forward flight mode to vertical flight mode, and by reducing the drag by aligning the rotor blades, the power consumed by the prefabricated gas can be minimized .

Once the rotor blades of a plurality of vertical flight rotors are aligned in line, the prefabricated airframe automatically ascends to a higher altitude. When the prefabricated gas reaches the desired altitude, the forward flight rotor advances at the speed at which the drag generated during forward flight is minimized to minimize the power consumption of the prefabricated aircraft.

When the prefabricated aircraft arrives at a specific point to perform the mission, the plurality of vertical flight rotors gradually increase the number of revolutions and reach the number of revolutions at which the upward speed is 0 m / s. When a plurality of vertical flight rotors obtain propulsive force for stopping flight, the forward flight rotor is again aligned in a direction perpendicular to the earth. If you take a forward flight with a fixed-wing aircraft, you will not be able to shoot a specific terrain precisely. However, the prefabricated airframe can combine the flywheel frames 210 and 220 to enable efficient flight forwarding and stopping flights.

When the prefabricated aircraft completes its mission, the plurality of vertical flight rotors are again aligned in a direction perpendicular to the fuselage to cruise back to the landing point and the forward flight rotor generates propulsion for forward flight. When the prefabricated gas reaches the landing point after the cruise flight, the forward flight rotor reduces the number of revolutions and the plurality of vertical flight rotors increase the number of revolutions. When a plurality of vertical flight rotors obtain propulsive force for stopping flight, the forward flight rotor is aligned in a direction perpendicular to the ground, and when reaching a precise landing point, a plurality of vertical flight rotors are operated, do.

The present invention has been described in detail with reference to the preferred embodiments shown in the drawings. These embodiments are to be considered as illustrative rather than limiting, and should be considered in an illustrative rather than a restrictive sense. The true scope of protection of the present invention should be determined by the technical idea of the appended claims rather than the above description. Although specific terms are used herein, they are used for the purpose of describing the concept of the present invention only and are not used to limit the scope of the present invention described in the claims or the claims. 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 invention as defined by the appended claims. It is to be understood that the equivalents include all components that are invented to perform the same function irrespective of the currently known equivalents as well as the equivalents to be developed in the future.

Claims (13)

A main wing portion fixed to the body; And
A first wing portion and a second wing portion detachably coupled to left and right side surfaces of the main wing portion,
And an additional wing portion that can be additionally coupled between the main wing portion and the first wing portion and between the main wing portion and the second wing portion according to the flight environment of the prefabricated airframe,
The additional wing
A rotor blade frame including a plurality of vertical flight rotors for generating lifting force for an ascending flight, including a rotor blade and a motor,
The prefabricated airframe comprising a propulsion frame including a forward flight rotor for generating propulsion forces for forward flight, including a rotor blade and a motor,
The vehicle body,
And a controller for controlling the driving of the forward flight rotor and the plurality of vertical flight rotors in accordance with a flight mode of the prefabricated vehicle including a vertical flight mode and a horizontal flight mode,
Wherein the main wing includes a connector transmission terminal connected to the control unit through a communication line to output a control signal for the plurality of vertical flying rotors,
Wherein the rotor frame includes a connector receiving terminal connected to the plurality of vertical flying rotors through a communication line and electrically connected to the connector transmitting terminal when coupled to the main wing and receiving the control signal, Prefabricated airframe according to flight environment. The method according to claim 1,
The additional wing
And a fixed wing frame extending the wing length of the prefabricated gas. delete delete The method according to claim 1,
Wherein the prefabricated gas includes a joint spa installed on left and right sides of the main wing,
Wherein the rotor frame includes a through hole through which the joint spar can pass. ≪ RTI ID = 0.0 > 11. < / RTI > The method according to claim 1,
The rotary-
And a power supply unit for supplying power to the plurality of vertical flight rotors,
Wherein the main wing portion has no power line connected to the additional wing portion. The method according to claim 1,
Wherein the plurality of vertical flight rotors include:
And an ESC (Electronic Speed Control) for controlling the rotation speed of the motor. delete delete delete The method according to claim 1,
Wherein the moving body includes a control unit for controlling driving of the plurality of vertical flight rotors and a wireless communication unit for transmitting a control signal of the control unit to the plurality of vertical flight rotors to the plurality of vertical flight rotors,
Wherein the plurality of vertical flight rotors include a wireless communication unit for receiving a control signal of the control unit,
Wherein the main wing portion has no communication line connected to the additional wing portion. The method according to claim 1,
Wherein,
And gradually increasing the rotational speed of the forward flight rotor to gradually generate the propulsive force for forward flight while gradually reducing the rotational speed of the plurality of vertical flight rotors, , And switches the flight mode of the prefabricated aircraft from the ascending flight mode to the forward flight mode. The method according to claim 1,
Wherein,
Wherein when the vertical flight mode is entered, the rotor blade of the forward flight rotor is aligned in a direction perpendicular to the ground.

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