Electric airplane charging device

Abstract

The present invention relates to an electric airplane charging device comprising: a receiving part concavely formed in the floor surface of a stand; an openable / closable cover part which is provided on the upper part of the receiving part, and the upper surface of which is at the same height as the floor surface of the stand when the receiving part is closed; a connection part provided on the receiving part to be electrically connected to an external power supply, the connection part being exposed to the upper part of the receiving part when the cover part is opened; and a transfer part configured to be movable while a charging module is mounted and including an input side connector and an output side connector, each electrically connected to the charging module.

Description

Electric airplane charging device

[0001] The present invention relates to an electric aircraft charging device, and more particularly, to an electric aircraft charging device in which a connection part is installed buried in the ground, so as not to affect the movement of the electric aircraft and equipment.

[0002]

[0003] In general, electric vehicles are driven by the rotational power of a motor that uses electric energy, and have the advantage of not producing any harmful exhaust fumes because they use electric energy.

[0004] Recently, the commercialization of electric airplanes that use electricity as a power source has begun, and various types of charging devices are being used to charge the batteries of electric airplanes.

[0005] Conventional electric aircraft charging devices are available in two types: a mobile structure that can be moved to the location of the electric aircraft in a hangar or apron and connected to a power supply unit via a power cable, and a fixed structure that is fixedly installed at a designated charging location.

[0006] However, among the existing electric aircraft charging devices, the mobile charging device has a power cable exposed to the ground, causing interference between the electric aircraft and surrounding equipment, and its use is limited because it can only charge certain models of electric aircraft.

[0007] In addition, fixed charging devices can only charge at a fixed installation location, so the charging space is narrow, and since the charging device is fixed in a state where it is exposed to the ground, there is a risk of interference between the electric aircraft and surrounding equipment, and there is the inconvenience of having to move the electric aircraft over a long distance.

[0008] Prior art documents related to the invention include Korean Patent Publication No. 10-2308909 (September 28, 2021), which discloses a portable charger.

[0009]

[0010] The purpose of the present invention is to provide an electric airplane charging device that does not affect the movement of the electric airplane and equipment because the connecting part is installed in a buried state in the ground.

[0011]

[0012] The electric aircraft charging device according to the present invention is an electric aircraft charging device for charging an electric aircraft equipped with a connection terminal, and includes a receiving portion concavely formed on the floor surface of an apron, a cover portion openably provided on an upper portion of the receiving portion and having an upper surface that is flush with the floor surface of the apron when the receiving portion is closed, a connection portion provided on the receiving portion and electrically connected to an external power supply, and exposed to the upper portion of the receiving portion when the cover portion is opened, and a transfer portion that is movable while a charging module is mounted and has an input-side connector and an output-side connector electrically connected to the charging module, wherein the input-side connector is connected to the connection portion to supply power to the charging module, and the output-side connector is connected to the charging terminal to supply power.

[0013] In addition, the above-mentioned circuit board may further include a power line electrically connecting the connection unit and the power supply unit through the ground.

[0014] In addition, the receiving portion may further include a concavely formed mounting groove along the upper end of the edge side thereof, and the cover portion may further include a body that horizontally covers the upper part of the receiving portion and has an upper surface that is flush with the bottom surface of the cycle when the receiving portion is closed, and a mounting end that protrudes from the edge of the body and is mounted corresponding to the upper surface of the mounting groove.

[0015] In addition, the above-described transport unit may further include a control unit electrically connected to the charging module and having a plurality of charging speeds preset, and when a user inputs the departure time and the required charging amount of the electric airplane, the control unit calculates the remaining charge amount of the electric airplane, the required charge amount, and the remaining time until the departure time to calculate the minimum charging speed, and charges the electric airplane at the minimum charging speed.

[0016] In addition, the transport unit is equipped with a battery that is electrically connected to the charging module, and can use the charging power of the battery as a power source, and the battery is electrically connected to the output-side connector to discharge the charging power, and is electrically connected to the input-side connector to be charged.

[0017]

[0018] The present invention has the effect of allowing easy installation in various charging locations since the connecting part is installed in a buried state in the ground, so there is no interference with electric aircraft and equipment, there is no hassle of having to move the charging equipment to a long distance, and it is easy to secure installation space.

[0019] In addition, since the present invention is easy to secure installation space, it can reduce human costs for securing land and constructing charging facilities, and when installed by a company / individual that operates an electric airplane or a charging company, it can be used universally because various companies and individuals can operate airplanes.

[0020]

[0021] Figure 1 is a plan view showing an electric airplane charging device according to the present invention.

[0022] Figure 2 is a side cross-sectional view showing an electric airplane charging device according to the present invention.

[0023] Figure 3 is a plan view showing a state in which an electric airplane is charged with the cover of the electric airplane charging device according to the present invention open.

[0024] FIG. 4 is a side cross-sectional view showing a state in which an electric airplane is charged with the cover of the electric airplane charging device according to the present invention open.

[0025] FIG. 5 is a plan view showing a state in which the battery of the transport unit and the electric airplane are simultaneously charged with the cover of the electric airplane charging device according to the present invention opened.

[0026] FIG. 6 is a side cross-sectional view showing a state in which the battery of the transport unit and the electric airplane are simultaneously charged with the cover of the electric airplane charging device according to the present invention open.

[0027] Figure 7 is a side cross-sectional view showing a state in which a circuit unit, a communication module, and a lighting unit are applied to an electric airplane charging device according to the present invention.

[0028] Figure 8 is a side cross-sectional view showing a state in which an opening / closing unit and an elevator unit are applied to an electric airplane charging device according to the present invention.

[0029] Figure 9 is a side cross-sectional view showing a state in which the cover portion of the electric airplane charging device according to the present invention is opened by the opening / closing portion.

[0030] Fig. 10 is a side cross-sectional view showing the process of a connection part being raised by an elevation cylinder of an electric airplane charging device according to the present invention.

[0031]

[0032] Hereinafter, a preferred embodiment according to the present invention will be described in detail with reference to the attached drawings.

[0033] The advantages and features of the present invention and the method for achieving them will become clear with reference to the embodiments described in detail below together with the attached drawings.

[0034] However, the present invention is not limited to the embodiments disclosed below, but may be implemented in various different forms, and these embodiments are provided only to make the disclosure of the present invention complete and to fully inform a person having ordinary skill in the art to which the present invention pertains of the scope of the invention, and the present invention is defined only by the scope of the claims.

[0035] In addition, when describing the present invention, if it is determined that related known technologies or the like may obscure the gist of the present invention, a detailed description thereof will be omitted.

[0036] FIG. 1 is a plan view showing an electric airplane charging device according to the present invention, FIG. 2 is a side cross-sectional view showing an electric airplane charging device according to the present invention, FIG. 3 is a plan view showing a state of charging an electric airplane with a cover part of an electric airplane charging device according to the present invention open, FIG. 4 is a side cross-sectional view showing a state of charging an electric airplane with a cover part of an electric airplane charging device according to the present invention open, and FIG. 5 is a plan view showing a state of simultaneously charging a battery of a transport unit and an electric airplane with a cover part of an electric airplane charging device according to the present invention open.

[0037] FIG. 6 is a side cross-sectional view showing a state in which the battery of the transport unit and the electric aircraft are simultaneously charged when the cover part of the electric aircraft charging device according to the present invention is opened, FIG. 7 is a side cross-sectional view showing a state in which a circuit part, a communication module, and a lighting part are applied to the electric aircraft charging device according to the present invention, FIG. 8 is a side cross-sectional view showing a state in which an opening / closing part and an elevation part are applied to the electric aircraft charging device according to the present invention, FIG. 9 is a side cross-sectional view showing a state in which the cover part of the electric aircraft charging device according to the present invention is opened by the opening / closing part, and FIG. 10 is a side cross-sectional view showing a process in which a connection part is raised by an elevation cylinder of the electric aircraft charging device according to the present invention.

[0038] Referring to FIGS. 1 to 10, an electric airplane charging device according to the present invention is for charging an electric airplane (10) equipped with a connection terminal (11), and includes a receiving portion (100), a cover portion (200), a connection portion (300), and a transfer portion (400).

[0039] The receiving portion (100) is formed concavely on the bottom surface of the landing pad (S) where the electric airplane (10) that uses electric energy as a power source is located, and the receiving portion (100) can be positioned adjacent to the edge of the landing pad (S).

[0040] A plurality of stands (S) may be arranged adjacently, and a plurality of stands (S) may be arranged at a location adjacent to the runway of the airplane. In this case, the receiving unit (100) may be individually formed in a plurality of stands (S).

[0041] In addition, the receiving portion (100) can be positioned eccentrically on one side of the landing gear (S) to correspond to the position of the connection terminal (11) of the electric airplane (10), and a plurality of receiving portions (100) can be positioned corresponding to both sides of the landing gear (S) to correspond to various types of electric airplanes (10).

[0042] In addition, the depth and width of the receiving portion (100) can be applied in various ways as needed, and a separate blocking wall (metal, plastic, etc.) can be formed on the inner surface and bottom surface of the receiving portion (100), and the inner surface of the receiving portion (100) can be circular, but can be applied in various ways as needed.

[0043] In addition, a mounting groove (110) formed concavely along the upper edge of the receiving portion (100) may be further included. The mounting groove (110) is a portion where the edge of the cover portion (200) described later is mounted, and the depth and width of the mounting groove (110) can be applied in various ways as needed.

[0044] The cover part (200) is for opening and closing the upper part of the receiving part (100), and the edge is seated corresponding to the seating groove (110) of the receiving part (100), and the upper surface of the cover part (200) can be positioned horizontally with the bottom surface of the cycle track (S).

[0045] A cover part (200) according to one embodiment of the present invention may further include a body (210) that horizontally covers the upper part of the receiving part (100) and has an upper surface that is the same height as the bottom surface of the cycle track (S) when the receiving part (100) is closed, and a mounting part (220) that protrudes from the edge of the body (210) and is mounted corresponding to the upper surface of the mounting groove (110).

[0046] The body (210) may be made of a material such as metal, and may have a circular plate shape with an edge that corresponds to the upper portion of the receiving portion (100), but the shape of the body (210) may have a shape corresponding to the receiving portion (100).

[0047] Additionally, a handle structure may be formed on the upper surface of the body (210) so that an administrator can grasp it by hand or connect a work cable. For example, the body (210) may be separated from the upper portion of the receiving portion (100) by the administrator grasping the handle and then lifting it upward.

[0048] When the body (210) is placed on the upper part of the receiving portion (100), the mounting member (220) is placed corresponding to the mounting groove (110). At this time, the lower end of the mounting member (220) can be placed horizontally against the bottom surface of the mounting groove (110), and the edge of the mounting member (220) can be placed vertically against the inner surface of the mounting groove (110).

[0049] In addition, a buffer member (900) made of an elastic material (rubber, etc.) that can be elastically deformed may be further combined on the bottom surface of the mounting groove (110), and the buffer member (900) may have a ring shape with a hollow portion extending upward and downward to correspond to the mounting groove (110), and when the cover part (200) is mounted on the upper part of the receiving part (100), the mounting end (220) may be mounted on the upper surface of the buffer member (900).

[0050] That is, the buffer member (900) can buffer the impact generated when the mounting end (220) is mounted in the mounting groove (110), thereby preventing damage to the cover part (200) due to the impact, and since the contact area between the mounting groove (110) and the mounting end (220) is closely contacted by the buffer member (900), the inflow of foreign substances, etc. can be minimized.

[0051] The connection part (300) is configured to supply power, is provided inside the receiving part (100), is electrically connected to an external power supply part (not shown) by a power cable, and is exposed to the upper part of the receiving part (100) when the cover part (200) is opened.

[0052] Here, the connection part (300) can be electrically connected to a power supply part (not shown) through the ground of the main unit (S), and both longitudinal sides of a power line (wire, L) extended through the ground can be connected to the connection part (300) and the power supply part, respectively.

[0053] In addition, the connecting portion (300) may be connected at the bottom to the bottom surface of the receiving portion (100), may have a connecting groove or a connecting protrusion at the top, and may have a connecting terminal exposed at the top of the connecting groove or the connecting protrusion.

[0054] In this case, the connection terminal of the connection part (300) can be electrically connected to one side of the longitudinal direction of a power line (wire, L) extended through the ground so that power can be supplied, and when the input side connector (430) to be described later is connected male and female to the upper end of the connection part (300), the connection terminal of the connection part (300) and the connection terminal of the input side connector (430) can be mutually connected.

[0055] The transfer unit (400) is for charging an electric airplane (10) located on the apron (S), and a movable structure can be selectively used while the charging module (410) is mounted, and the transfer unit (400) is equipped with an input-side connector (420) and an output-side connector (430) that are electrically connected to the charging module (410).

[0056] A transport unit (400) according to one embodiment of the present invention may include a frame (401) in which a driving area is formed in the front and a loading area is formed in the rear, a plurality of wheels (402) rotatably provided on the lower portion of the frame (401), a motor provided on the frame (401) to transmit rotational force to the wheels, and a battery (440) rechargeably provided on the frame (401) to supply power to the motor.

[0057] In addition, the frame (401) may be equipped with a steering device for steering the front wheels (402), the frame (401) may be equipped with a braking device for transmitting braking force to the wheels (402) by the driver's braking operation, and a charging module (410) may be installed in the loading area of ​​the frame (401).

[0058] The input side connector (420) is for electrically connecting the connection part (200) and the charging module (410). The input side connector (420) can be electrically connected to the charging module (410) by a power cable having a length, and can be fixedly mounted on a mounting structure provided on the outside of the transport part (400).

[0059] In this case, the user can open the cover part (200) and then connect the input side connector (420) to the top of the connection part (200) while holding it, and when charging is complete, the user can separate the input side connector (420) from the connection part (200) and then close the receiving part (100) using the cover part (200), and the input side connector (420) can be fixedly placed on a mounting structure provided on the outside of the transport part (400).

[0060] In another form, a connection terminal (450) may be provided on the outside of the transfer unit (400), and an input-side connector (420) may be provided in a pair, and the input-side connector (420) may be electrically connected by a power cable having a length.

[0061] In this case, the user can open the cover (200) and connect a pair of input side connectors (420) to the connection terminals (450) of the transfer unit (400) and the upper part of the connection unit (200), respectively, and when charging is complete, the user can separate the input side connectors (420) from the connection unit (200) and then close the receiving unit (100) using the cover (200).

[0062] In addition, the input side connector (430) can be stored individually after being separated from the connection terminal (450), or the input side connector (430) connected to the connection part (300) can be fixedly mounted on a mounting structure provided on the outside of the transfer part (400).

[0063] The output-side connector (430) is for electrically connecting the charging module (410) and the connection terminal (11) of the electric airplane (10). The output-side connector (430) is electrically connected to the charging module (410) by a power cable having a length, and can be fixedly mounted on a mounting structure provided on the outside of the transport unit (400).

[0064] In this case, the user can open the charging port cover of the electric airplane (10) and connect the output side connector (430) to the connection terminal (11) while holding it, and when charging is complete, the user can disconnect the output side connector (430) from the connection terminal (11) and close the charging port using the charging port cover, and the output side connector (430) can be fixedly mounted on a mounting structure provided on the outside of the transport unit (400).

[0065] In addition, the transfer unit (400) may be equipped with a battery (440) that is electrically connected to the charging module as described above, and the charging power of the battery (440) may be used as a power source. Here, the battery (440) may be electrically connected to the output-side connector (430) to discharge the charging power, and may be electrically connected to the input-side connector (420) through the connection terminal (450) to be charged.

[0066] For example, the power supply of the aforementioned connection part (300) can be applied as 350 kW, the charging speed of the electric airplane (10) can be applied as 200 kW, and since a residual power of 150 kW remains among the power supply of the connection part (300), the battery (440) of the transfer part (400) can be charged using the remaining power of 150 kW. In other words, the transfer part (400) can be charged together in the process of charging the electric airplane (10) located on the apron (S), and when the transfer part (400) is applied as an electric vehicle, the inconvenience caused by frequent charging can be eliminated.

[0067] Meanwhile, the electric airplane charging device according to the present invention may further include a control unit (500) equipped in the transport unit (400) and electrically connected to the charging module (410), and having a plurality of charging speeds preset.

[0068] When a user inputs the departure time and required charge amount of an electric airplane (10), the control unit (500) can calculate the remaining charge amount of the electric airplane (10), the required charge amount, and the remaining time until departure time to calculate the minimum charging speed, and the control unit (500) can charge the electric airplane at the minimum charging speed.

[0069] That is, the electric airplane charging device according to the present invention charges the battery of the electric airplane (10) at the lowest charging speed through the calculation of the charging speed of the control unit (500), thereby extending the battery life of the electric airplane (10) and reducing the possibility of fire occurring during the charging process.

[0070] An electric airplane charging device according to one embodiment of the present invention may further include a communication module (510) that is provided in a transport unit (400) to enable wireless communication as shown in FIG. 7 and is electrically connected to a control unit (500).

[0071] In addition, it may further include a circuit unit (610) provided in the receiving unit (100) and electrically connected to an external power supply unit and a power line (S), a communication module (620) provided in the receiving unit (100) so as to be able to transmit / receive signals in a wireless communication manner with a communication module (510) of the control unit (500) and electrically connected to the circuit unit (610), and one or more lighting units (630) installed in a state inserted into the bottom surface of the main body (S) and electrically connected to the circuit unit (610) and diffusing light (white, red, green, etc.) upward when turned on by the driving control of the circuit unit (610).

[0072] The lighting unit (630) may use a light emitting diode (LED), etc., and a plurality of lighting units (630) may be arranged to surround the perimeter of the cover unit (200), and the position, color, number, etc. of the lighting units (630) may be applied in various ways as needed.

[0073] For example, when a lighting signal is generated using the control unit (500), the lighting signal transmitted from the communication module (510) of the control unit (500) is received by the communication module (620) of the circuit unit (610), and the lighting unit (630) can be turned on by the driving control of the circuit unit (610), and the lighting unit (630) can be turned off by the lighting off signal of the control unit (500). Here, the communication module (620) can selectively use various wireless communication methods.

[0074] That is, when the lighting unit (630) is turned on, the surroundings of the receiving unit (100) are brightly displayed, so that the electric airplane (10) can be easily charged even in an environment where visibility is not good (at night, etc.), and when the transport unit (400) enters the apron (S), the surroundings are brightly illuminated, so that a collision between the electric airplane (10) and the transport unit (400) can be prevented.

[0075] Meanwhile, in an electric airplane charging device according to one embodiment of the present invention, as shown in FIGS. 8 to 10, the cover part (200) may be provided to be rotatable and openable based on a horizontal rotation center on one side, and the cover part (200) may be opened and closed by an opening and closing part (700) electrically connected to a control part (500).

[0076] The opening / closing unit (700) may further include an installation groove (710) formed on one side of the receiving unit (100) and in which one side of the cover unit (200) is exposed to the inside, an opening / closing motor (720) provided in the installation groove (710) and electrically connected to the circuit unit (610) and having a drive shaft protruding to one side, a pair of rotation shafts (730) protruding to both sides of the cover unit (200) and positioned eccentrically on one side of the cover unit (200), coupled to both sides of the installation groove (710) to form a horizontal rotation center, and a power transmission member (740) connecting one of the drive shaft of the opening / closing motor (720) and the rotation shaft (730) and transmitting the rotational force of the drive shaft to the rotation shaft.

[0077] The power transmission member (740) can use a chain, belt, etc., and both sides of the power transmission member (740) can wrap around the radial direction of the rotation shaft (730) and the drive shaft, respectively, and a pulley can be coupled to the drive shaft and the rotation shaft (730) so that the power transmission member (740) wraps around the radial direction.

[0078] For example, when the open operation signal of the control unit (500) is transmitted to the circuit unit (610) through the communication module (620), the drive shaft of the open / close motor (720) rotates in the first direction, and the cover unit (200) rotates backward to open the receiving unit (100). On the other hand, when the close operation signal of the control unit (500) is transmitted to the circuit unit (610) through the communication module (620), the drive shaft of the open / close motor (720) rotates in the second direction, and the cover unit (200) rotates forward to close the receiving unit (100).

[0079] Meanwhile, an electric airplane charging device according to one embodiment of the present invention may further include a connecting portion (300) that is provided to be liftable as shown in FIGS. 8 to 10, and an elevating portion (800) that is electrically connected to an external power supply and is linked with an opening / closing portion (700) to elevate the connecting portion (300) to a connecting position and a standby position.

[0080] The lifting member (800) may further include a guide member (810) that is coupled to the bottom surface of the receiving member (100), has an operating space formed therein, and has a guide hole formed at the top so that the connecting member (300) can be elevated; an elevating cylinder (820) that is coupled to the bottom surface of the operating space, and has an upper end of a rod that protrudes upward vertically coupled to the lower end of the connecting member (300); and a pressure supply member (830) that is provided inside the receiving member (100), is connected to the elevating cylinder (820), and elevates the rod by the driving control of the circuit unit (610).

[0081] The guide hole is vertically penetrated through the upper part of the guide member (810), and the inner surface of the guide hole can support the edge of the connecting part (300) in a close contact state, and when the connecting part (300) is raised and lowered to the upper connecting position and the lower waiting position, the guide hole can support the connecting part (300) so that it does not shake.

[0082] The lifting cylinder (820) can be vertically connected at the bottom to the floor surface of the operating space, and one side of the lifting cylinder (820) and the pressure supply member (830) can be connected by a pipe. That is, the connecting portion (300) can be raised and lowered to the connecting position and the standby position by the raising and lowering of the load, and the connecting portion (300) raised to the connecting position can protrude at the same height as the upper part of the receiving portion (100) or higher than the upper part of the receiving portion (100).

[0083] The pressure supply unit (830) can raise and lower the load of the lifting cylinder (820) by supplying and discharging pneumatic or hydraulic pressure. Here, the pressure supply unit (830) can use a compressor or the like, and can be electrically connected to the circuit unit (610) to control its operation.

[0084] Such an elevator (800) can be linked with an opening / closing unit (700). For example, when an opening operation signal is transmitted from the control unit (500) to the circuit unit (610) via the communication module (620), the cover unit (200) is opened and the load is raised to raise the connection unit (300) to the connection position.

[0085] On the other hand, when a closing operation signal from the control unit (500) is transmitted to the circuit unit (610) through the communication module (620), the connection unit (300) can be lowered to the standby position and then the cover unit (200) can be closed.

[0086] In addition, the manager can selectively control the opening and closing operation of the cover (200) and the raising and lowering operation of the connection part (300) during the process of the transfer part (400) moving to the apron (S) or while the transfer part (400) has entered the apron (S). That is, the cover part (200) can be opened and closed automatically, thereby improving the convenience of use, and the connection part (300) is raised to the ground during charging, so that the input side connector (420) can be easily connected.

[0087] As a result, the present invention is installed with the connection part buried in the ground, so there is no interference with electric aircraft and equipment, etc., there is no hassle of having to move the charging equipment to a long distance, and it is easy to secure installation space, so it can be easily installed in various charging locations.

[0088] In addition, since the present invention is easy to secure installation space, it can reduce human costs for securing land and constructing charging facilities, and if a company / individual that operates an electric airplane or a charging company installs it, it can be used universally because various companies and individuals can operate airplanes.

[0089] Although specific embodiments of the electric airplane charging device according to the present invention have been described so far, it is obvious that various modifications are possible within the scope of the present invention.

[0090] Therefore, the scope of the present invention should not be limited to the described embodiments, but should be defined not only by the claims described below but also by equivalents of the claims.

[0091] That is, it should be understood that the above-described embodiments are exemplary in all respects and not restrictive, and the scope of the present invention is indicated by the claims to be described later rather than the detailed description, and all changes or modified forms derived from the meaning and scope of the claims and their equivalent concepts should be interpreted as being included in the scope of the present invention.

[0092]

[0093] (Explanation of symbols)

[0094] 10: Electric airplane 11: Connection terminal

[0095] 100: Reception area 110: Settling area

[0096] 200: Cover 210: Body

[0097] 220: Settling point 300: Connection point

[0098] 400: Transfer section 401: Frame

[0099] 402: Wheel 410: Charging module

[0100] 420: Input side connector 430: Output side connector

[0101] 440: Battery 450: Connector

[0102] 500: Control unit 510: Communication module

[0103] 610: Circuit section 620: Communication module

[0104] 630: Lighting section 700: Opening section

[0105] 710: Installation groove 720: Opening / closing motor

[0106] 730: Rotating shaft 740: Power transmission member

[0107] 800: Lifting member 810: Guide member

[0108] 820: Lifting cylinder 830: Pressure supply member

[0109] 900: Buffer member L: Power line

[0110] S: Parking lot

Claims

1. An electric airplane charging device for charging an electric airplane equipped with a connection terminal, A receiving area formed concavely on the bottom surface of the pedestal; A cover part which is openably provided on the upper part of the receiving part and has an upper surface that is at the same height as the bottom surface of the pedestal when the receiving part is closed; A connection part provided in the above-mentioned receiving portion and electrically connected to an external power supply, and exposed to the upper portion of the receiving portion when the cover part is opened; and A transport unit that is movable while equipped with a charging module and has an input connector and an output connector electrically connected to the charging module, respectively; An electric airplane charging device characterized in that the input side connector is connected to the connection part to supply power to the charging module, and the output side connector is connected to the connection terminal to supply power.

2. In paragraph 1, An electric airplane charging device further comprising a power line electrically connecting the connection unit and the power supply unit through the ground of the above-mentioned pylon.

3. In paragraph 1, It further includes a seating groove formed concavely along the upper edge side of the above-mentioned receiving portion, The above cover part, A body that covers the upper part of the receiving portion horizontally and has an upper surface that is at the same height as the bottom surface of the receiving portion when the receiving portion is closed, and An electric airplane charging device characterized in that it further includes a mounting end that protrudes from the edge of the body and is mounted corresponding to the upper surface of the mounting groove.

4. In paragraph 1, It further includes a control unit that is provided in the above transport unit and is electrically connected to the charging module, and in which a plurality of charging speeds are preset. The above control unit, An electric airplane charging device characterized in that when a user inputs the departure time and required charge amount of the electric airplane, the remaining charge amount of the electric airplane, the required charge amount, and the time remaining until the departure time are calculated to calculate the minimum charging speed, and the electric airplane is charged at the minimum charging speed.

5. In paragraph 4, The above transport unit, A battery electrically connected to the above charging module is provided, and the charging power of the battery is used as a power source. The above battery, An electric airplane charging device characterized in that it is electrically connected to the output side connector to discharge charging power and is electrically connected to the input side connector to charge.

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