WO2017078227A1 - Dispositif de récupération maritime de véhicule aérien sans pilote - Google Patents

Dispositif de récupération maritime de véhicule aérien sans pilote Download PDF

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Publication number
WO2017078227A1
WO2017078227A1 PCT/KR2016/003256 KR2016003256W WO2017078227A1 WO 2017078227 A1 WO2017078227 A1 WO 2017078227A1 KR 2016003256 W KR2016003256 W KR 2016003256W WO 2017078227 A1 WO2017078227 A1 WO 2017078227A1
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WO
WIPO (PCT)
Prior art keywords
unmanned aerial
aerial vehicle
air
recovery system
gas
Prior art date
Application number
PCT/KR2016/003256
Other languages
English (en)
Korean (ko)
Inventor
김동민
이해창
김성욱
Original Assignee
한국항공우주연구원
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from KR1020150155877A external-priority patent/KR101726654B1/ko
Priority claimed from KR1020150155889A external-priority patent/KR101681602B1/ko
Application filed by 한국항공우주연구원 filed Critical 한국항공우주연구원
Publication of WO2017078227A1 publication Critical patent/WO2017078227A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/30—Launching, take-off or landing arrangements for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • E—FIXED CONSTRUCTIONS
    • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
    • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
    • E05B83/00—Vehicle locks specially adapted for particular types of wing or vehicle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F17C13/04—Arrangement or mounting of valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C7/00—Methods or apparatus for discharging liquefied, solidified, or compressed gases from pressure vessels, not covered by another subclass

Definitions

  • the present invention relates to an unmanned aerial vehicle.
  • unmanned aerial vehicles fly by radio wave guidance without humans, and are used not only for monitoring on land and at sea, but also for aerial photographing or accident prosecution.
  • the conventional unmanned aerial vehicle marine recovery apparatus disclosed in US Patent Publication No. US2012 / 0032025 uses an unmanned aerial vehicle in such a manner that the unmanned aerial vehicle is caught in a capture net 16, as shown in FIG. It proposes a technical configuration for recovering a ship to a ship.
  • a mass cord cord 454 has a groove 322 formed therein. A technical configuration for recovering an unmanned aerial vehicle to a ship in a manner caught by a capture plate 312 is proposed.
  • the conventional unmanned aerial vehicle marine retrieval device is a medium-sized vessel of 1000 tons or less, or 100 tons or less, in which space for installing a capture net or capture plate, and space for an unmanned aerial vehicle can not be secured sufficiently. There is a problem that cannot be installed in a small ship.
  • An object of the present invention is to provide an unmanned aerial vehicle marine recovery apparatus capable of recovering an unmanned aerial vehicle at sea regardless of the size of the vessel.
  • Another technical problem of the present invention is to provide an unmanned aerial vehicle marine recovery apparatus capable of recovering an unmanned aerial vehicle at sea without exposure to salt in a simple configuration and manner.
  • the unmanned aerial vehicle marine recovery apparatus for recovering the unmanned aerial vehicle at sea, is provided with the unmanned aerial vehicle and inflated by gas injection to An air member that floats the unmanned aerial vehicle on water; And a gas injector connected to the inlet of the air member to inject gas into the air member when receiving an operation signal.
  • the air member may be an air bowl which is expanded by gas injection to seat the unmanned aerial vehicle.
  • an unmanned aerial vehicle marine recovery apparatus comprising: an accommodating member including the air bowl and the gas injector in the unmanned aerial vehicle in a fixed and accommodating manner to the unmanned aerial vehicle and having an accommodation space and an opening; And a door part configured to open and close the opening part.
  • the door part may include a first door rotatably provided at a first edge of the opening part; A second door rotatably provided at a second edge of the opening opposite to the first edge to open and close the opening together with the first door; And a lock configured to open the first and second doors upon receiving the operation signal and to maintain the closed state during the flight.
  • the locking unit a hook velcro provided in the first door; And a hook hook velcro provided on the second door to be attached to and detached from the hook velcro, and the first and second doors may be kept closed by the coupling force between the hook velcro and the hook velcro during the flight.
  • the air bowl is inflated by the gas injector, and the first and second doors may be opened by the hook velcro and the hook velcro falling by the expansion force.
  • the locking part may include a locking solenoid valve provided over the first and second doors, and the valve body of the locking solenoid valve is drawn out to close the first and second doors during the flight. May be maintained, and upon receiving the operation signal, the valve body of the solenoid valve for the door may be introduced to open the first and second doors.
  • the gas injector may include: a gas cylinder connected to an inlet of the air bowl and storing compressed gas; And a cylinder solenoid valve provided in the gas cylinder to open the gas cylinder to eject the gas of the gas cylinder when the operation signal is received.
  • the gas injector a compression fan connected to the inlet of the air bowl; And a driving motor provided in the compression fan to rotate the compression fan when receiving the operation signal.
  • the unmanned aerial vehicle marine recovery apparatus in addition to the unmanned aerial vehicle marine recovery apparatus according to an embodiment of the present invention may further include a parachute unit provided in the unmanned aerial vehicle.
  • the parachute unit includes: a parachute provided on an upper portion of the unmanned aerial vehicle; A fixing part fixing the parachute to an upper portion of the unmanned aerial vehicle; And a release part for releasing the fixing part upon receiving the operation signal.
  • the parachute may be connected to the air bowl via a connecting member.
  • the accommodation member may be provided under the unmanned aerial vehicle, and the opening may be formed under the storage member based on the unmanned aerial vehicle.
  • the air member may be an air cover that is expanded by gas injection to surround the unmanned aerial vehicle.
  • the air cover is provided by the unmanned aerial vehicle and unfolded by the gas injection to surround the unmanned aerial vehicle;
  • a gas injector connected to the inlet of the air cover to inject a gas into the air cover when an operation signal is received;
  • the unmanned aerial vehicle marine recovery apparatus is provided with the air cover, the gas injector, the tension line, and the parachute in the unmanned aerial vehicle in a manner of being fixedly stored in the unmanned aerial vehicle.
  • An accommodating member having a space and an opening; And a door part configured to open and close the opening part.
  • the door part may include a first door rotatably provided at a first edge of the opening part; A second door rotatably provided at a second edge of the opening opposite to the first edge to open and close the opening together with the first door; And a lock configured to open the first and second doors upon receiving the operation signal and to maintain the closed state during the flight.
  • the locking unit a hook velcro provided in the first door; And a hook hook velcro provided on the second door to be attached to and detached from the hook velcro, and the first and second doors may be kept closed by the coupling force between the hook velcro and the hook velcro during the flight.
  • the air cover is expanded by the gas injector, and the first and second doors may be opened by falling off the hook velcro and the hook velcro by the expansion force.
  • the locking part may include a locking solenoid valve provided over the first and second doors, and the valve body of the locking solenoid valve is drawn out to close the first and second doors during the flight. May be maintained, and upon receiving the operation signal, the valve body of the solenoid valve for the door may be introduced to open the first and second doors.
  • the gas injector may include: a gas cylinder connected to an inlet of the air cover and storing compressed gas; And a cylinder solenoid valve provided in the gas cylinder to open the gas cylinder to eject the gas of the gas cylinder when the operation signal is received.
  • the gas injector 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 receiving the operation signal.
  • the accommodation member may be provided at the front of the unmanned aerial vehicle, and the opening may be formed at the front of the storage member based on the unmanned aerial vehicle.
  • the unmanned aerial vehicle marine recovery apparatus may have the following effects.
  • the air bowl on the sea near the vessel while inflated in the form of a bowl (bowl) by the gas injector Unmanned aerial vehicles can be seated on the ground, allowing unmanned aerial vehicles to be recovered at sea regardless of the size of the vessel.
  • the air bowl is provided in the unmanned aerial vehicle, the unmanned aerial vehicle is seated on the air bowl while being unfolded, so that the unmanned aerial vehicle is not only recovered from the unmanned aerial vehicle with a simple configuration and operation compared to the technology of the conventional retrieval device which is combined with a ship. Can prevent getting into the sea.
  • the air spread near the ship in the form of a crepe while being expanded by the gas injector The unmanned aerial vehicle is collected on the cover, and the unmanned aerial vehicle captured on the air cover can be entirely wrapped by the air cover while pulling the tension line by the reaction force of the parachute acting in the opposite direction of the flight direction. Regardless, the drone may be recovered at sea.
  • the air cover covers the unmanned aerial vehicle as a whole, it is possible to prevent the unmanned aerial vehicle from getting into the sea as well as the recovery of the unmanned aerial vehicle with a simple configuration and operation compared to the technology of the conventional recovery apparatus combined with the vessel.
  • FIG. 1 is a perspective view schematically showing a state where an unmanned aerial vehicle marine recovery apparatus according to an embodiment of the present invention is mounted on an unmanned aerial vehicle.
  • FIG. 2 is a view schematically illustrating a state in which an air bowl and a gas injector are accommodated in an accommodating member of the unmanned aerial vehicle marine recovery apparatus of FIG. 1.
  • FIG 3 is a view schematically illustrating a state in which an example gas injector is connected to an inlet of an air bowl.
  • FIG. 4 is a view schematically showing a state in which another example of the gas injector is connected to the inlet of the air bowl.
  • FIG. 5 is a cross-sectional view schematically illustrating a state where an example locking unit is provided in the first and second doors.
  • FIG. 6 is a cross-sectional view schematically illustrating a state where the locking unit of the other example is provided in the first and second doors.
  • FIG. 7 is a perspective view illustrating an unmanned aerial vehicle mounted on an air bowl by operating the unmanned aerial vehicle marine recovery apparatus of FIG. 1.
  • FIG. 8 is a perspective view schematically showing a state where an unmanned aerial vehicle marine recovery apparatus according to another embodiment of the present invention is mounted on an unmanned aerial vehicle.
  • FIG. 9 is a perspective view illustrating an unmanned aerial vehicle mounted on an air bowl by operating the unmanned aerial vehicle marine recovery apparatus of FIG. 8.
  • FIG. 10 is a perspective view schematically showing a state where an unmanned aerial vehicle marine recovery apparatus according to another embodiment of the present invention is mounted on an unmanned aerial vehicle.
  • FIG. 11 is a view schematically illustrating a state in which an air cover, a gas injector, a parachute, and the like are accommodated in the accommodating member of the unmanned aerial vehicle marine recovery apparatus of FIG. 10.
  • FIG. 12 is a diagram schematically illustrating a state in which an example gas injector is connected to an inlet of an air cover.
  • FIG. 13 is a view schematically illustrating a state in which another example gas injector is connected to an inlet of an air cover.
  • FIG. 14 is a cross-sectional view schematically illustrating a state where an example locking unit is provided in the first and second doors.
  • 15 is a cross-sectional view schematically illustrating a state where the locking unit of the other example is provided in the first and second doors.
  • FIG. 16 is a perspective view schematically illustrating a state in which an unmanned aerial vehicle is collected in an air cover by operating the unmanned aerial vehicle marine recovery apparatus of FIG. 10 and the air cover is tightened by a parachute and a tension line.
  • FIG. 17 is a view schematically illustrating a state in which the air cover of FIG. 16 is completely tightened by the parachute and the tension line.
  • FIG. 18 is a view showing a conventional unmanned aerial vehicle marine recovery apparatus.
  • 19 is a view showing another conventional unmanned aerial vehicle marine recovery apparatus.
  • FIG. 1 is a perspective view schematically showing a state where an unmanned aerial vehicle marine recovery apparatus according to an embodiment of the present invention is mounted on an unmanned aerial vehicle
  • FIG. 2 is an air bowl and a gas injector in a receiving member of the unmanned aerial vehicle marine recovery apparatus of FIG. 1. Is a view schematically showing a housed state.
  • FIG. 3 is a view schematically illustrating a state in which an example gas injector is connected to an inlet of an air bowl
  • FIG. 4 is a view schematically illustrating a state in which another example gas injector is connected to an inlet of an air bowl.
  • FIG. 5 is a cross-sectional view schematically illustrating a state in which locking parts are provided in the first and second doors as an example
  • FIG. 6 is a cross-sectional view schematically illustrating a state in which the locking parts are provided in the first and second doors as another example.
  • FIG. 7 is a perspective view illustrating an unmanned aerial vehicle mounted on an air bowl by operating the unmanned aerial vehicle marine recovery apparatus of FIG. 1.
  • the unmanned aerial vehicle marine recovery apparatus 100 is an unmanned aerial vehicle marine recovery apparatus for recovering the unmanned aerial vehicle 10 from the sea, as shown in FIGS. 1 to 7.
  • air member (AM) and gas injector 120 are shown in FIGS. 1 to 7.
  • AM air member
  • gas injector 120 gas injector
  • the air member AM is a component provided in the unmanned aerial vehicle 10 (see FIG. 1) and is expanded by gas injection to float the unmanned aerial vehicle 10 on water (see FIG. 7).
  • an air bowl 110 expanded in the form of a bowl may be used as the air member AM.
  • the air bowl 110 as shown in Figures 2 and 3 can be folded in a variety of shapes, such as a rectangular shape in the state in which the gas is missing, bowl (bowl) in the gas injected state as shown in FIG. In the form of a bowl).
  • the air bowl 110 may be provided with an injection hole (111 in FIG. 3) connected to the gas injector 120, and a plurality of air injection portions (112 in FIG. 7) through which air is injected.
  • the unmanned aerial vehicle 10 may be a fixed wing type unmanned aerial vehicle capable of flying for a long time at sea.
  • the present invention may be applied to a rotorcraft type aircraft without being limited thereto.
  • the gas injector 120 is connected to the inlet 111 of the air bowl 110 to receive an operation signal from the control unit 170 of FIG. 2. It is a component to inject.
  • the gas injector 120 may include a gas cylinder 121 and a solenoid valve 122 for a cylinder.
  • the gas cylinder 121 has a compressed gas stored therein and is connected to the inlet 111 of the air bowl 110, and the solenoid valve 122 for the cylinder is provided at the gas cylinder 121 to operate from the controller 170.
  • the gas cylinder 121 is opened to eject the gas from the gas cylinder 121.
  • the solenoid valve 122 for the cylinder is opened and the compressed gas of the gas cylinder 121 is ejected to the inlet 111 of the air bowl 110 to expand the air bowl 110.
  • the gas injector 120 may include a compression fan 221 and a driving motor 222, as shown in FIG. 4.
  • the compression fan 221 is connected to the inlet 111 of the air bowl 110, the drive motor 222 is provided in the compression fan 221 and receives the operation signal from the control unit (170 of FIG. 2) compression fan 221 Rotate). Accordingly, when the operation signal is received from the controller 170, the air bowl 110 is expanded while air is injected into the inlet 111 of the air bowl 110 by the rotation of the driving motor 222 and the compression fan 221. Can be.
  • the unmanned aerial vehicle marine recovery apparatus 100 may further include an accommodation member 130 and a door portion 140 as shown in FIG. 2.
  • the accommodation member 130 includes the air bowl 110 and the gas injector 120 in the unmanned aerial vehicle 10 in a manner of accommodating the air bowl 110 and the gas injector 120.
  • the accommodating member 130 may include an accommodating space 131 capable of accommodating the air bowl 110 and the gas injector 120, and the air bowl 110 may accommodate the accommodating member 130 when the air bowl 110 is inflated. It may have an opening 132 to provide a way out.
  • the door part 140 is a component that opens and closes the opening part 132 as shown in FIG. 2.
  • the door part 140 may include a first door 141, a second door 142, and a locking part 143, as shown in FIGS. 2 and 5.
  • the first door 141 is rotatably provided at the first edge of the opening part 132
  • the second door 142 is rotatably provided at the second edge opposite to the first edge of the opening part 132.
  • the locking unit 143 may include a male velcro 143a and a female velcro 143b.
  • the hook velcro 143a may be provided in the first door 141
  • the hook velcro 143b may be provided in the second door 142 to be attached to and detached from the hook velcro 143a. Therefore, during flight, the first and second doors 141 and 142 may be kept closed by the coupling force between the hook velcro 143a and the hook velcro 143b, and the operation signal from the control unit 170 (FIG. 2).
  • the hook velcro 143a and the hook velcro 143b are separated by the expansion force so that the first and second doors 141 and 142 may be opened. have.
  • the locking part 343 may include a locking solenoid valve 343a provided over the first and second doors 141 and 142, as shown in FIG. 6. Accordingly, during flight, the valve body 343b of the locking solenoid valve 343a may be drawn out so that the first and second doors 141 and 142 may be kept closed, and operated from the control unit 170 of FIG. 2. When the signal is received, the valve body 343b of the solenoid valve 343a for the door may be introduced to open the first and second doors 141 and 142.
  • FIG. 8 is a perspective view schematically showing a state where an unmanned aerial vehicle marine recovery apparatus is mounted on an unmanned aerial vehicle according to another embodiment of the present invention
  • FIG. 9 is an unmanned aerial vehicle mounted on an air bowl by operating the unmanned aerial vehicle marine recovery apparatus of FIG. A perspective view showing a seated state.
  • Unmanned aerial vehicle marine recovery apparatus 400 according to another embodiment of the present invention described above, as shown in Figures 8 and 9, except that further includes a parachute unit 450 of the present invention described above Since substantially the same as the embodiment will be described below with respect to the parachute unit 450.
  • the parachute unit 450 is a component provided in the unmanned aerial vehicle 10 together with the above-mentioned air bowl 110 (or the receiving member 130) as shown in FIG.
  • the parachute unit 450 may include a parachute 451, a fixing part 452, and a release part 453 as illustrated in FIG. 8.
  • the parachute 451 is provided at the upper portion of the unmanned aerial vehicle 10, the fixing portion 452 fixes the parachute 451 at the upper portion of the unmanned aerial vehicle 10, and the release portion 453 is a control unit (see FIG. 2).
  • the fixing part 452 Upon receiving the operation signal from 170, the fixing part 452 is released.
  • the fixing part 452 may be a box-shaped or plate-shaped fixing bracket, and the release part 453 may be used to open and close the opening of the bracket when the fixing part is a box-shaped bracket.
  • a separate door or solenoid valve may be used, and when the fixing part is a plate-shaped bracket, a solenoid valve or the like may be used to enable locking and unlocking of the bracket.
  • the parachute 451 may be connected to the air bowl 110 through a connecting member 460.
  • the air bowl 110 and the parachute 451 are placed in a connected state through the connecting member 460.
  • the housing member 130 is provided under the unmanned aerial vehicle 10
  • the opening 132 is formed under the storage member 130 based on the unmanned aerial vehicle 10
  • the unmanned aerial vehicle 10 Since the parachute 451 placed on the upper portion of the) is relatively above the air bowl 110, when the lowering of the parachute 451 is completed, the parachute 451 covers the upper opening 132 of the air bowl 110.
  • the unmanned aerial vehicle 10 seated on the air bowl 110 may prevent the inflow of the floor to the maximum.
  • FIG. 10 is a perspective view schematically illustrating a state where an unmanned aerial vehicle marine recovery apparatus is mounted on an unmanned aerial vehicle
  • FIG. 11 is an air cover and a gas in a housing member of the unmanned aerial vehicle marine recovery apparatus of FIG. 10. It is a figure which shows schematically the state in which the injector, parachute, etc. were accommodated.
  • FIG. 12 is a view schematically illustrating a state in which an example gas injector is connected to an inlet of an air cover
  • FIG. 13 is a view schematically illustrating a state in which another example gas injector is connected to an inlet of an air cover.
  • FIG. 14 is a cross-sectional view schematically illustrating a state in which the locking parts are provided in the first and second doors as an example
  • FIG. 15 is a cross-sectional view schematically illustrating a state in which the locking parts are provided in the first and second doors as another example.
  • FIG. 16 is a perspective view schematically illustrating a state in which an unmanned aerial vehicle is collected on an air cover and the air cover is fastened by a parachute and a tension line by operating the unmanned aerial vehicle marine recovery apparatus of FIG. 10, and
  • FIG. 17 is a parachute of the air cover of FIG. 16.
  • Figure is a schematic view showing a state that is fully tightened by the tension line.
  • the unmanned aerial vehicle marine recovery apparatus 2100 is an unmanned aerial vehicle marine recovery apparatus for recovering the unmanned aerial vehicle 10 from the sea, as shown in FIGS. 10 to 17.
  • air cover 2110 air cover 2110
  • gas injector 2120 gas injector 2120
  • tension line 2130 of FIG. 16
  • parachute parachute
  • the air cover 2110 is one of the above-described air members AM, which is provided in the unmanned aerial vehicle 10 (see FIG. 10) and is expanded by gas injection to surround the unmanned aerial vehicle 10 (see FIG. 16).
  • the gas may be folded into various shapes such as a square shape, and as shown in FIG. 16, the gas may be expanded into a furoshiki shape as shown in FIG. 16.
  • the air cover 2110 may be provided with an injection hole (2111 of FIG. 12) connected to the gas injector 2120, and a plurality of air injection portions (2112 of FIG. 16) to which air is substantially injected.
  • the unmanned aerial vehicle 10 may be a fixed wing type unmanned aerial vehicle capable of flying for a long time at sea.
  • the present invention may be applied to a rotorcraft type aircraft without being limited thereto.
  • the gas injector 2120 is connected to the inlet 2111 of the air cover 110 to receive an operation signal from the control unit 2170 of FIG. 11. It is a component to inject.
  • the gas injector 2120 may include a gas cylinder 2121 and a solenoid valve 2122 for a cylinder.
  • the gas cylinder 2121 has a compressed gas stored therein and is connected to the inlet 2111 of the air cover 2110, and the solenoid valve 2122 for the cylinder is provided at the gas cylinder 2121 to operate from the controller 2170.
  • the gas cylinder 2121 is opened so that the gas in the gas cylinder 2121 is ejected.
  • the solenoid valve 2122 for the cylinder is opened and the compressed gas of the gas cylinder 2121 is ejected to the inlet 2111 of the air cover 2110, thereby expanding the air cover 2110. Can be.
  • the gas injector 2120 may include a compression fan 2221 and a driving motor 2222, as shown in FIG. 13.
  • the compression fan 2221 is connected to the inlet 2111 of the air cover 2110, and the drive motor 2222 is provided at the compression fan 2221 to receive an operation signal from the control unit 2170 of FIG. 11. Rotate). Accordingly, when the operation signal is received from the controller 2170, the air cover 2110 may be expanded while air is injected into the inlet 2111 of the air cover 2110 by the driving of the driving motor 2222 and the compression fan 2221 rotating. Can be.
  • Tension line 2130 is a component that wraps around the air cover 2110 to tighten the edge of the air cover 2110, as shown in FIG. 16.
  • the tension line 2130 is in a state of being accommodated in the accommodating member 2150, and when the gas injector 2120 receives an operation signal from the control unit (2170 of FIG. 11), the tension cord 2130 is out of the accommodating member 2150 together with the air cover 2110. Can come out.
  • the parachute 2140 is a component that is connected to the tension string 2130 and pulls the tension string 2130 while being unfolded.
  • the parachute 2140 is stored in the housing member 2150, and when the gas injector 2120 receives an operation signal from the controller 2170 of FIG. 11, the parachute 2140 is moved out of the housing member 2150 together with the air cover 2110. Can come out. Accordingly, the unmanned aerial vehicle 210 captured by the air cover 2110 is pulled by the air cover 2110 while the tension string 2130 is pulled by the reaction force of the parachute 2140 acting in the direction opposite to the flight direction of the drone. It can be wrapped.
  • the unmanned aerial vehicle marine recovery apparatus 2100 may further include an accommodating member 2150 and a door part 2160 as shown in FIG. 11.
  • the accommodating member 2150 includes the air cover 2110, the gas injector 2120, the tension line 2130 of FIG. 16, and the parachute 2140 in the unmanned aerial vehicle 10.
  • An air cover 2110, a gas injector 2120, a tension line 2130, and a parachute 2140 are provided as a component, which is a kind of fixed bracket having a box shape.
  • the accommodating member 2150 may include an accommodating space 2511 for accommodating the air cover 2110, the gas injector 2120, the tension line 2130, and the parachute 2140, and the air cover 2110 may be expanded.
  • the air cover 2110 may have an opening 2152 that provides a way out of the receiving member 2150.
  • the accommodation member 2150 may have a streamlined shape in front of the unmanned aerial vehicle 10 to reduce wind resistance, and the air cover 2110 is unmanned as the air cover 2110 is unfolded.
  • the opening portion 2152 may be formed at the front of the accommodation member 2150 based on the unmanned aerial vehicle 10 to surround the aircraft 10.
  • the door part 2160 is a component which opens and closes the opening part 2152 as shown in FIG. 11.
  • the door part 2160 may include a first door 2161, a second door 2162, and a locking part 2163 as illustrated in FIGS. 11 and 14.
  • the first door 2161 is rotatably provided at the first edge of the opening portion 2152
  • the second door 2162 is rotatably provided at the second edge of the opening portion 2152 facing the first edge.
  • the locking unit 2163 may include a male velcro 2163a and a female velcro 2163b.
  • the hook velcro 2163a may be provided at the first door 2161
  • the hook velcro 2163b may be provided at the second door 2162 to be attached to and detached from the hook velcro 2143a. Therefore, during flight, the first and second doors 2161 and 2162 may be kept closed by the coupling force between the hook velcro 2163a and the hook velcro 2163b, and the operation signal from the control unit 2170 of FIG.
  • the air cover 2110 is inflated by the gas injector 2120, the hook Velcro 2163a and the hook Velcro 2163b are separated by the expansion force, and thus the first and second doors 2161 and 2162 may be opened. have.
  • the locking unit 2363 may include a locking solenoid valve 2363a provided over the first and second doors 2161 and 2162 as shown in FIG. 15. Accordingly, during flight, the valve body 2363b of the locking solenoid valve 2363a may be drawn out so that the first and second doors 2161 and 2162 may be kept closed, and operated from the control unit 2170 of FIG. 11. When the signal is received, the valve body 2363b of the solenoid valve 2363a for the door may be introduced to open the first and second doors 2161 and 2162.
  • the unmanned aerial vehicle marine recovery apparatus 100, 400, 2100 may have the following effects.
  • the gas injector 120 is expanded in the form of a bowl.
  • the unmanned aerial vehicle 10 may be seated on the air bowl 110 deployed at sea near the ship, so that the unmanned aerial vehicle 10 may be recovered at sea regardless of the size of the ship.
  • the air bowl 110 is provided in the unmanned aerial vehicle 10 and is unfolded to seat the unmanned aerial vehicle 10 on the air bowl 110, it is simpler than the technology of the conventional retrieval apparatus combined with a ship.
  • the configuration and operation can prevent not only the recovery of the unmanned aerial vehicle 10 but also the unmanned aerial vehicle 10 from getting into the sea.
  • the gas injector 2120 since the technical configuration including the air cover 2110, the gas injector 2120, the tension line 2130, and the parachute 2140 is provided, the gas injector 2120
  • the unmanned aerial vehicle 10 is collected on an air cover 2110 deployed in the sea near the ship in the form of a crepe while being expanded by), and together with the tension line by the reaction force of the parachute 2140 acting in the opposite direction of the flight direction.
  • the unmanned aerial vehicle 10 captured in the air cover 2110 may be entirely surrounded by the air cover 2110, so that the unmanned aerial vehicle 10 may be recovered at sea regardless of the size of the vessel. .
  • the air cover 2110 surrounds the unmanned aerial vehicle 10 as a whole, the unmanned aerial vehicle 10 as well as the recovery of the unmanned aerial vehicle 10 with a simple configuration and operation compared to the technology of the conventional recovery device that is combined with the vessel. Can prevent getting into the sea.
  • the present invention relates to an unmanned aerial vehicle marine recovery apparatus can be applied to recover the unmanned aerial vehicle at sea, there is industrial applicability.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Forklifts And Lifting Vehicles (AREA)

Abstract

La présente invention vise à fournir un dispositif de récupération maritime d'un véhicule aérien sans pilote, le dispositif de récupération maritime permettant à un véhicule aérien sans pilote d'être récupéré en mer indépendamment de la taille d'un navire. À cet effet, le dispositif de récupération maritime d'un véhicule aérien sans pilote, selon la présente invention, est conçu pour récupérer un véhicule aérien sans pilote en mer et comprend : un élément pneumatique fourni au véhicule aérien sans pilote, et gonflé par injection de gaz de façon à faire flotter le véhicule aérien sans pilote sur l'eau ; et un injecteur de gaz relié à l'entrée de l'élément pneumatique de façon à injecter un gaz dans l'élément pneumatique lorsqu'un signal de fonctionnement est reçu.
PCT/KR2016/003256 2015-11-06 2016-03-30 Dispositif de récupération maritime de véhicule aérien sans pilote WO2017078227A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
KR10-2015-0155877 2015-11-06
KR10-2015-0155889 2015-11-06
KR1020150155877A KR101726654B1 (ko) 2015-11-06 2015-11-06 무인항공기 해상 회수 장치
KR1020150155889A KR101681602B1 (ko) 2015-11-06 2015-11-06 무인항공기 해상 회수 장치

Publications (1)

Publication Number Publication Date
WO2017078227A1 true WO2017078227A1 (fr) 2017-05-11

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CN107985599A (zh) * 2017-12-27 2018-05-04 天机智汇科技（深圳）有限公司 自动载货装置、无人机及载货舱
CN113581482A (zh) * 2020-04-30 2021-11-02 山东交通学院 一种固定翼无人机回收装置

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JP2009208674A (ja) * 2008-03-05 2009-09-17 Mitsubishi Electric Corp 搭載型無人飛行機回収装置及び搭載型無人飛行機回収装置を備えた無人飛行機
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JP2009208674A (ja) * 2008-03-05 2009-09-17 Mitsubishi Electric Corp 搭載型無人飛行機回収装置及び搭載型無人飛行機回収装置を備えた無人飛行機
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KR20110111127A (ko) * 2010-04-02 2011-10-10 한국항공우주산업 주식회사 무인항공기용 완충착륙장치
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107985599A (zh) * 2017-12-27 2018-05-04 天机智汇科技（深圳）有限公司 自动载货装置、无人机及载货舱
CN113581482A (zh) * 2020-04-30 2021-11-02 山东交通学院 一种固定翼无人机回收装置

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