KR101681602B1

KR101681602B1 - Recovery apparatus for UAV on sea

Info

Publication number: KR101681602B1
Application number: KR1020150155889A
Authority: KR
Inventors: 김동민; 이해창; 김성욱
Original assignee: 한국항공우주연구원
Priority date: 2015-11-06
Filing date: 2015-11-06
Publication date: 2016-12-01

Abstract

SUMMARY OF THE INVENTION It is a technical object of the present invention to provide an unmanned aerial vehicle recovery system capable of recovering an unmanned airplane at sea regardless of the size of a ship. To this end, the unmanned aeronautical maritime recovery apparatus of the present invention comprises: an air cover provided in the unmanned airplane and unfolded by gas injection to surround the unmanned airplane; A gas injector connected to an inlet of the air cover to inject gas into the air cover when an operation signal is received; A tightening string surrounding the periphery of the air cover to tighten the edge of the air cover; And a parachute connected to and extending from the fastening line to pull the fastening line.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a UAV recovery apparatus,

The present invention relates to an unmanned aerial vehicle.

In general, an unmanned aerial vehicle (UAV) is a vehicle that is not driven by a person but is driven by induction of radio waves, and is used not only for land and sea surveillance but also for high-speed shooting or accident detection.

Especially, when the unmanned airplane is used for marine use, there is a need for a technique capable of accurately recovering the unmanned airplane to a ship in a small space floating in the sea.

In accordance with this necessity, the conventional unmanned aerial vehicle recovery apparatus disclosed in U.S. Patent Publication No. US2012 / 0032025 is configured such that, as shown in Fig. 9, the unmanned aircraft To the ship. In addition, in the conventional unmanned aerial vehicle recovery apparatus disclosed in US2007 / 0158498, as shown in Fig. 10, a cord 454 to which a mass is attached is formed with a groove 322 And capture the unmanned airplane as a ship by catching it on a capture plate 312.

However, the conventional unmanned aerial vehicle reclaiming apparatus has a space for installing a capture net or a capture plate, a medium-sized vessel of less than 1,000 tons in which an unmanned airplane can not secure enough space to travel, There is a problem that can not be installed in a small ship.

In addition, in order to construct a capture net or a capture plate on a ship, the design is troublesome, and in order to capture a flying unmanned air vehicle, there is a problem that a high technique is required for operation of the sea recovery device.

SUMMARY OF THE INVENTION It is an object of the present invention to provide an unmanned aerial vehicle recovery system capable of recovering an unmanned airplane in the sea regardless of the size of the vessel.

It is another object of the present invention to provide an unmanned aerial vehicle recovery apparatus capable of recovering an unmanned aerial vehicle at sea without exposure to salt in a simple configuration and a method.

In order to achieve the above object, an unmanned aerial vehicle reconnaissance apparatus according to an exemplary embodiment of the present invention includes an air cover provided in the unmanned airplane and unfolded by gas injection to enclose the unmanned airplane. A gas injector connected to an inlet of the air cover to inject gas into the air cover when an operation signal is received; A tightening string surrounding the periphery of the air cover to tighten the edge of the air cover; And a parachute connected to and extending from the fastening line to pull the fastening line.

The unmanned aerial vehicle reconnaissance apparatus according to an embodiment of the present invention includes the air cover, the gas injector, the sewing line, and the parachute in the unmanned airplane in a manner of being fixed to the unmanned airplane, A housing member having an opening; And a door unit for opening and closing the opening unit.

The door portion may include a first door rotatably provided at a first edge of the opening portion, A second door rotatably provided at a second edge of the opening portion opposite to the first edge to open and close the opening portion together with the first door; And a lock portion for opening the first and second doors when the operation signal is received, and maintaining the closed state during the flight.

For example, the locking portion may include a hook-and-loop structure provided on the first door; And a hook collar hook provided on the second door so as to be attached to and detached from the hook hook. The first and second doors may be maintained in a closed state by the coupling force of the hook hook and the hook hook during the flight When the operating signal is received, the air cover is inflated by the gas injector, and the first and second doors can be opened by the inflating force so that the hook hook and the hook hook are separated from each other.

As another example, the locking portion may include a locking solenoid valve that is provided over the first and second doors, and during the flight, the valve body of the locking solenoid valve is pulled out so that the first and second doors are closed And when the operation signal is received, the valve body of the door solenoid valve is drawn in, and the first and second doors can be opened.

Further, for example, the gas injector may include: a gas cylinder connected to an inlet of the air cover and storing a compressed gas; And a cylinder solenoid valve provided in the gas cylinder to open the gas cylinder so that the gas of the gas cylinder is released when the operation signal is received.

As another example, the gas injector may include: a compression fan connected to the inlet of the air cover; And a driving motor provided in the compression fan to rotate the compression fan when the operation signal is received.

The storage member may be provided at a front portion of the unmanned air vehicle, and the opening portion may be formed at a front portion of the storage member with reference to the unmanned air vehicle.

The unmanned airplane may be a fixed wing type unmanned airplane.

As described above, the unmanned aerial vehicle reclaiming apparatus according to the embodiment of the present invention can have the following effects.

According to the embodiment of the present invention, since the technical constitution including the air cover, the gas injector, the tightening rope and the parachute is provided, it is possible to provide an unmanned air conditioner on the air cover deployed in the sea near the ship in the form of a crepe, The airplane is captured and the tightening string is pulled by the reaction force of the parachute in the direction opposite to the flight direction so that the unmanned airplane captured by the air cover can be entirely wrapped by the air cover, Unmanned aircraft can be recovered. In particular, since the air cover covers the entire unmanned airplane, the unmanned airplane can be prevented from being taken into the sea as well as the unmanned airplane is recovered by a simple configuration and operation as compared with the conventional recovery device combined with the ship.

FIG. 1 is a perspective view schematically showing a state where an unmanned aerial vehicle recovery apparatus according to an embodiment of the present invention is mounted on an unmanned airplane.
FIG. 2 is a schematic view showing a state in which an air cover, a gas injector, a parachute, and the like are accommodated in a receiving member of the unmanned aerial vehicle remover of FIG. 1;
3 is a schematic view showing a state in which an example gas injector is connected to an inlet of an air cover.
4 is a view schematically showing a state in which a gas injector according to another example is connected to an inlet of an air cover.
FIG. 5 is a cross-sectional view schematically showing a state in which an example of the locking part is provided in the first and second doors. FIG.
6 is a cross-sectional view schematically showing a state in which the locking part of another example is provided in the first and second doors.
FIG. 7 is a perspective view schematically showing a state in which an unmanned aircraft is collected in an air cover by the operation of the unmanned aerial vehicle recovery device of FIG. 1, and an air cover is tightened by a parachute and a sewing line.
8 is a view schematically showing a state in which the air cover of FIG. 7 is completely tightened by a parachute and a tightening line;
9 is a view showing a conventional unmanned aerial vehicle recovery apparatus.
FIG. 10 is a view showing another conventional unmanned aerial vehicle salvage system.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings, which will be readily apparent to those skilled in the art to which the present invention pertains. The present invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.

FIG. 1 is a perspective view schematically showing a state in which an unmanned aerial vehicle reconnaissance apparatus according to an embodiment of the present invention is mounted on an unmanned airplane, FIG. 2 is a cross- And a parachute and the like are housed.

FIG. 3 is a schematic view illustrating a state in which an example gas injector is connected to an inlet of an air cover, and FIG. 4 is a view schematically showing a state in which another gas injector is connected to an inlet of an air cover.

FIG. 5 is a cross-sectional view schematically showing a state in which the first and second door locks are provided, and FIG. 6 is a cross-sectional view schematically showing a state in which another example of the lock is provided in the first and second doors.

FIG. 7 is a perspective view schematically showing a state in which an unmanned aircraft is collected in an air cover by the operation of the unmanned aerial vehicle reclaiming apparatus of FIG. 1 and the air cover is tightened by a parachute and a sewing line, FIG. 8 is a cross- And a state in which it is completely tightened by a tightening line.

As shown in FIGS. 1 to 8, an unmanned aerial vehicle reconnaissance apparatus 100 according to an embodiment of the present invention is an unmanned aerial vehicle reconnaissance apparatus for recovering an unmanned air vehicle 10 at sea, an air cover 110, a gas injector 120, a fastening string 130 (FIG. 7), and a parachute 140. Hereinafter, each of the constituent elements will be described in detail with continued reference to Figs. 1 to 8. Fig.

The air cover 110 is a component provided in the UAV 10 (see FIG. 1), expanded by gas injection to surround the UAV 10 (see FIG. 7) As shown in FIG. 7, when the gas is injected, it can be expanded in the form of a crease.

Further, the air cover 110 may be provided with an inlet (111 in FIG. 3) connected to the gas injector 120 and a plurality of air injecting portions (112 in FIG. 7) into which substantially air is injected.

In addition, a wing-wing type unmanned airplane capable of long flight at sea can be used as the unmanned airplane (10). However, the present invention is not limited to this, but may be applicable to a rotor-type aircraft.

2 and 3, the gas injector 120 is connected to the injection port 111 of the air cover 110 and receives an operation signal from the control unit 170 (FIG. 2) .

As an example, the gas injector 120 may include a gas cylinder 121 and a cylinder solenoid valve 122, as shown in FIG. The compressed gas is stored in the gas cylinder 121 and connected to the injection port 111 of the air cover 110. The cylinder solenoid valve 122 is provided in the gas cylinder 121 to be operated from the control unit 170 The gas cylinder 121 is opened so that the gas in the gas cylinder 121 is ejected. Accordingly, when the operation signal is received from the control unit 170, the cylinder solenoid valve 122 is opened, and the compressed gas of the gas cylinder 121 is ejected into the injection port 111 of the air cover 110 to expand the air cover 110 .

As another example, the gas injector 120 may include a compression fan 221 and a drive motor 222, as shown in FIG. The compression fan 221 is connected to the injection port 111 of the air cover 110. The drive motor 222 is provided in the compression fan 221 and receives the operation signal from the control unit 170 ). Accordingly, when the operation signal is received from the controller 170, air is injected into the injection port 111 of the air cover 110 due to driving of the driving motor 222 and rotation of the compression fan 221 so that the air cover 110 is inflated .

The tightening string 130 is a component that surrounds the air cover 110 to tighten the edge of the air cover 110, as shown in Fig. When the gas injector 120 receives an operation signal from the control unit 170 (FIG. 2), the control member 130 is accommodated in the accommodating member 150, Can come out.

The parachute 140 is a component that is connected to the tightening string 130 and pulls the tightening string 130 as it is unfolded, as shown in FIGS. When the gas injector 120 receives an operation signal from the control unit 170 in FIG. 2, the parachute 140 is accommodated in the accommodating member 150, and then, together with the air cover 110, Can come out. Therefore, when the tightening string 130 is pulled by the reaction force of the parachute 140 acting in the direction opposite to the flight direction of the unmanned airplane, the unmanned airplane 10 captured by the air cover 110 is totally It can be wrapped.

In addition, the unmanned aerial vehicle reconnaissance apparatus 100 according to an embodiment of the present invention may further include a receiving member 150 and a door unit 160, as shown in FIG.

The housing member 150 is connected to the unmanned airplane 10 in such a manner as to house the air cover 110, the gas injector 120, the tightening string (130 in FIG. 7) and the parachute 140 as shown in FIG. A gas injector 120, a tightening string 130, and a parachute 140. The airbag 110 is a box-shaped fixing bracket. The storage member 150 includes a storage space 151 capable of accommodating the air cover 110, the gas injector 120, the tightening string 130 and the parachute 140, and a storage space 151 in which the air cover 110 is inflated The air cover 110 may have an opening 152 that provides a path through which the air cover 110 may exit out of the receiving member 150.

1 and 2, the housing member 150 may be provided with a wired shape at the front portion of the UAV 10 to reduce the wind resistance, and the air bag 110 may be unfolded The opening 152 may be formed at the front of the housing member 150 with respect to the UAV 10 so as to enclose the airplane.

The door portion 160 is a constituent element for opening and closing the opening portion 152 as shown in Fig. For example, the door portion 160 may include a first door 161, a second door 162, and a locking portion 163, as shown in FIGS. 2 and 5.

The first door 161 is rotatably provided at a first edge of the opening 152 and the second door 162 is rotatably provided at a second edge of the opening 152 opposed to the first edge. And the opening portion 152 is opened and closed together with the first door 161 and the locking portion 163 is opened when the first and second doors 161 and 162 receive the operation signal and is closed .

As an example, the locking portion 163 may include a hooked male velcro 163a and a female velcro 163b, as shown in FIG. The hooked velcro 163a may be provided on the first door 161 and the hooked looped Velcro 163b may be provided on the second door 162 to be attached to and detached from the hooked Velcro 143a. Accordingly, during the flight, the closed state of the first and second doors 161 and 162 can be maintained by the coupling force of the hook hook 163a and the hook hook hook 163b, The air cover 110 is inflated by the gas injector 120 and the first and second doors 161 and 162 are opened due to the inflating force so that the hook and hook hook 163a and the hook hook hook 163b are separated from each other have.

As another example, the locking portion 363 may include a locking solenoid valve 363a provided over the first and second doors 161 and 162, as shown in Fig. Therefore, during the flight, the valve body 363b of the locking solenoid valve 363a may be drawn out to maintain the closed state of the first and second doors 161 and 162, The valve body 363b of the door solenoid valve 363a is drawn in and the first and second doors 161 and 162 can be opened.

As described above, the UAV recovery apparatus 100 according to the embodiment of the present invention can have the following effects.

According to an embodiment of the present invention, since the air cover 110, the gas injector 120, the tightening string 130, and the parachute 140 are provided, the gas injector 120 The unmanned airplane 10 is captured on the air cover 110 deployed in the sea near the ship in the form of a wrapping cloth and the tightening string 130 is wound by the reaction force of the parachute 140 acting in the direction opposite to the flying direction The unmanned airplane 10 captured by the air cover 110 can be entirely enclosed by the air cover 110 so that the unmanned airplane 10 can be recovered at sea regardless of the size of the vessel. In particular, since the air cover 110 covers the entire space of the UAV 10, it is possible to recover the UAV 10 as well as the UAV 10 in a simple configuration and operation, From getting into the sea.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is to be understood that the invention is not limited to the disclosed exemplary embodiments, Of the right.

10: Unmanned Aircraft 100: Unmanned Aircraft Maritime Recovery Unit
110: air cover 111: inlet of air cover
120, 220: gas injector 121: gas cylinder
122: solenoid valve for cylinder 221: compression fan
222: driving motor 130:
140: Parachute 150: Storage member
151: Storage space 152:
160: door part 161: first door
162: second door 163, 363:
163a: Velcro with hooks 163b: Velcro with hooks
363a: Solenoid valve for locking

Claims

Unmanned aerial vehicle reconnaissance system for recovering unmanned aircraft from offshore,
An air cover provided in the unmanned airplane and unfolded by gas injection to surround the unmanned airplane;
A gas injector connected to an inlet of the air cover to inject gas into the air cover when an operation signal is received;
A tightening string surrounding the periphery of the air cover to tighten the edge of the air cover;
A chute for pulling the fastening string while being connected to the fastening string,
Containing
Unmanned aerial vehicle recovery system.

The method of claim 1,
The unmanned aerial vehicle reconnaissance apparatus according to claim 1,
A housing member having the air cover, the gas injector, the fixing rope, and a parachute mounted on the UAV, the UAV having a storage space and an opening; And
The door portion
Further comprising
Unmanned aerial vehicle recovery system.

3. The method of claim 2,
The door portion
A first door rotatably provided at a first edge of the opening;
A second door rotatably provided at a second edge of the opening portion opposite to the first edge to open and close the opening portion together with the first door; And
And a locking portion for keeping the first and second doors closed during flight
Containing
Unmanned aerial vehicle recovery system.

4. The method of claim 3,
The locking portion
A hook-and-loop fastener provided on the first door; And
And a hook-and-loop fastener provided on the second door to be attached to and detached from the hook-
During the flight, the first and second doors are maintained in a closed state by the coupling force between the hook hook and the hook hook,
When the operating signal is received, the air cover is unfolded by the gas injector, and the inflatable force causes the hook hook and the hook hook to separate from each other to open the first and second doors
Unmanned aerial vehicle recovery system.

4. The method of claim 3,
The locking portion
And a locking solenoid valve provided over the first and second doors,
The valve body of the locking solenoid valve is drawn out to keep the first and second doors closed,
When the actuating signal is received, the valve body of the locking solenoid valve is retracted to open the first and second doors
Unmanned aerial vehicle recovery system.

The method of claim 1,
The gas injector
A gas cylinder connected to an inlet of the air cover and storing a compressed gas; And
A solenoid valve for a cylinder which is provided in the gas cylinder and opens the gas cylinder so as to discharge the gas of the gas cylinder when the operation signal is received,
Containing
Unmanned aerial vehicle recovery system.

The method of claim 1,
The gas injector
A compression fan connected to an inlet of the air cover; And
And a driving motor provided in the compression fan for rotating the compression fan when the operation signal is received,
Containing
Unmanned aerial vehicle recovery system.

3. The method of claim 2,
Wherein the housing member is provided at a front portion of the UAV,
Wherein the opening portion is formed at a front portion of the receiving member on the basis of the unmanned air vehicle
Unmanned aerial vehicle recovery system.

The method of claim 1,
The unmanned airplane is a fixed wing type unmanned airplane
Unmanned aerial vehicle recovery system.