JP2023089988A - cooling system - Google Patents

Abstract

To provide a cooling system for cooling a motor for rotating a propeller of an electric aircraft and an inverter device for controlling an operation of the motor, that cools each inverter while suppressing increase in weight of the electric aircraft as much as possible.SOLUTION: A cooling system 92 comprises: a radiator located radially outside a motor 44, having a plurality of fins; a motor cooling flow channel 74 located between a stator of the motor and the plurality of fins and in which a cooling liquid flows; an inverter cooling flow channel 106 in which the cooling liquid flows to cool an inverter device 96; a first flow channel 108 for making the cooling liquid flow from the motor cooling flow channel 74 to the inverter cooling flow channel 106; a second flow channel 110 for making the cooling liquid flow from the inverter cooling flow channel 106 to the motor cooling flow channel 74; and a pump 112 provided on at least one of the first flow channel 108 and the second flow channel 110.SELECTED DRAWING: Figure 7

Description

The present invention relates to a cooling system that cools a motor that rotates a propeller of an electric aircraft and an inverter device that controls the operation of the motor.

In recent years, the development of electric aircraft is prosperous. Such aircraft include, for example, electric vertical take-off and landing aircraft. An electric vertical take-off and landing vehicle is referred to as an eVTOL. An electric aircraft includes a plurality of propeller devices. The propeller device includes a propeller and an electric motor. In this specification, the electric motor is also simply referred to as a motor. A motor rotates the propeller.

Patent Literature 1 discloses a technique for cooling a motor of an electric aircraft (multicopter). In this technology, a plurality of fins are formed on the outer peripheral surface of the motor. Also, a fan wheel is provided outside the motor. The fan wheel is connected to the rotating shaft of the motor. In this structure, the heat of the motor is transferred to each fin. The fan wheel rotates as the motor rotates. Then, cooling air flows between the fins adjacent to each other. Therefore, each fin is cooled by the cooling air.

U.S. Patent Application Publication No. 2020/0244139

The motor of the electric aircraft is connected to the inverter. As many inverters as there are motors are provided. Like each motor, each inverter generates heat. Therefore, cooling of each inverter is necessary as well as cooling of each motor.

In order to cool the inverter, the electric aircraft may be provided with a cooling device such as a radiator. However, when a radiator is provided in an electric aircraft, the electric aircraft becomes heavy. As a result, the power consumption per unit flight distance of the electric aircraft increases. In other words, the cruising range of the electric aircraft is shortened. Therefore, a technique for cooling each inverter while suppressing an increase in the weight of the electric aircraft as much as possible is desired.

An object of the present invention is to solve the problems described above.

An aspect of the present invention is a cooling system that cools a motor that rotates a propeller of an electric aircraft and an inverter device that controls the operation of the motor, the cooling system being positioned radially outward of the motor and having a plurality of fins. a heat radiator, a motor cooling passage positioned between the stator of the motor and the plurality of fins, through which cooling liquid flows, an inverter cooling passage through which the cooling liquid flows to cool the inverter device; a first flow path for flowing the cooling liquid from the motor cooling flow path to the inverter cooling flow path; a second flow path for flowing the cooling liquid from the inverter cooling flow path to the motor cooling flow path; and a pump provided in either one of the passage and the second passage, wherein the cooling liquid is supplied from the motor cooling passage to the first passage, the inverter cooling passage, and the second passage. A cooling system that flows sequentially back to the motor cooling passage, absorbs heat from each of the motor and the inverter device, and radiates heat to the fins.

ADVANTAGE OF THE INVENTION According to this invention, a motor and an inverter apparatus can be cooled with a simple and lightweight structure.

FIG. 1 is a perspective view of an electric aircraft. FIG. 2 is a perspective view of the propeller assembly with the fairing removed. FIG. 3 is a cross-sectional view of the propeller device. FIG. 4 is a sectional view taken along line IV-IV of the propeller device shown in FIG. 3; FIG. 5 is a side view of the drive section and propeller. FIG. 6 is a perspective view of a radiator. FIG. 7 is a block diagram of the cooling system. FIG. 8 is a layout diagram of a motor and an inverter device. FIG. 9 is a block diagram of a modification of the cooling system.

[1 Overall Configuration of Electric Aircraft 10]
The overall configuration of the electric aircraft 10 will be described with reference to FIG. FIG. 1 is a perspective view of an electric aircraft 10. FIG. The electric aircraft 10 of this embodiment is an eVTOL aircraft. However, the present invention can also be used for multicopters. Electric aircraft 10 is also referred to herein simply as aircraft 10 .

The aircraft 10 includes a fuselage 12 , a front wing 14 , a rear wing 16 , two booms 18 , a plurality of takeoff and landing propeller assemblies 20 and a plurality of cruise propeller assemblies 22 . The body 12 is long in the front-rear direction. The front wing 14 is arranged forward of the intermediate portion of the body 12 in the front-rear direction. A front wing 14 is connected to the upper portion of the fuselage 12 . The rear wing 16 is arranged rearward of the middle portion of the fuselage 12 in the front-rear direction. The rear wing 16 is connected to the fuselage 12 via a pylon 24 .

The two booms 18 include a right boom 18R and a left boom 18L. Each boom 18 extends in the front-rear direction. The right boom 18R is arranged on the right side of the fuselage 12. As shown in FIG. The right boom 18R curves rightward in an arc shape. The right boom 18R is connected to the right tip of the front wing 14 and to the right wing of the rear wing 16 . The left boom 18L is arranged on the left side of the fuselage 12 . The left boom 18L curves leftward in an arc shape. The left boom 18L is connected to the left wingtip of the front wing 14 and to the left wing of the rear wing 16 . Note that each boom 18 may be linear.

Each boom 18 has a plurality of propeller devices 20 . In this embodiment each boom 18 comprises four propeller devices 20 . It should be noted that each boom 18 may have two, three or more propeller devices 20 . On each boom 18 , four propeller devices 20 are arranged in sequence along the extension direction of the boom 18 .

Fuselage 12 includes a plurality of propeller devices 22 . In this embodiment the fuselage 12 comprises two propeller devices 22 . Note that the fuselage 12 may include one or more propeller devices 22 . The two propeller devices 22 are arranged side by side at the rear end of the fuselage 12 .

[2 Structure of Propeller Device 20]
A take-off and landing propeller device 20 provided in the aircraft 10 will be described with reference to FIGS. 2 to 6. FIG. FIG. 2 is a perspective view of the propeller device 20 with the fairing 40 removed. FIG. 3 is a cross-sectional view of the propeller device 20. As shown in FIG. FIG. 3 is a sectional view perpendicular to the extending direction of the boom 18 and including the axis of the motor 44. As shown in FIG. FIG. 4 is a sectional view taken along line IV-IV of the propeller device 20 shown in FIG. FIG. 4 is a cross-sectional view of the propeller device 20 arranged foremost on the left boom 18L. The cross-sectional structure of another propeller device 20 is also basically the same as the cross-sectional structure shown in FIG. FIG. 5 is a side view of the drive section 28 and the propeller 30. FIG. 6 is a perspective view of the radiator 46. FIG.

As shown in FIG. 3 , the propeller device 20 has a housing section 26 , a driving section 28 and a propeller 30 . In addition, in a rotary wing aircraft, a "propeller" is also called a "rotor." However, the term "propeller" is used herein to avoid confusion between the "rotor" and the rotor 66 of the motor 44. Propeller 30 has a hub 32 , a propeller shaft 34 and a plurality of blades 36 .

The housing portion 26 has a frame 38 and a fairing 40 . Frame 38 is the skeleton of boom 18 . The frame 38 is a part that supports the driving section 28, the inverter device 96 (FIG. 7), and the like. A frame 38 is connected to the front wing 14 and the rear wing 16 . A fairing 40 is a part that covers the frame 38 . The fairing 40 forms a hole 42 penetrating vertically. The accommodation portion 26 accommodates the driving portion 28 in the hole 42 .

The drive section 28 has a motor 44 , a radiator 46 , a motor mount 48 , a gearbox 50 , a variable pitch mechanism 52 , two actuators 54 and a fan 56 . The axes of each configuration overlap each other. Note that there may be three or more actuators 54 .

Motor 44 is an AC motor. As shown in FIG. 3, the motor 44 has a motor housing 58, a motor rotating shaft 60, two bearings 62U and 62L, a stator 64 and a rotor 66. As shown in FIG. The motor housing 58 is formed by combining a plurality of members. Motor housing 58 accommodates a portion of motor shaft 60 , stator 64 , and rotor 66 . A bearing 62 U is fixed to the upper end of the motor housing 58 . A bearing 62L is fixed to the lower end of the motor housing 58 . Each of the two bearings 62U, 62L supports the motor rotating shaft 60 rotatably. Motor rotating shaft 60 is fixed to rotor 66 . The stator 64 is positioned radially outside the rotor 66 . A coil (not shown) for each phase is arranged on the stator 64 . Alternating current power is supplied to each phase coil from a power supply via an inverter circuit 104 (FIG. 7).

As shown in FIG. 4, motor housing 58 has four motor fixings 68 . Each motor fixing portion 68 protrudes radially outward from the outer circumference of the motor housing 58 . Each motor fixing portion 68 is located relatively high in the motor housing 58 . Each motor fixing portion 68 is positioned at the same height in the vertical direction. Each motor fixing portion 68 is arranged at equal intervals in the circumferential direction around the axis of the motor 44 . For example, each motor fixture 68 is located above the stator 64 and rotor 66 . Each motor fixing portion 68 is fixed to the first support portion 82 of the motor mount 48 by bolts, welding, or the like. Note that the number of motor fixing portions 68 may be two. However, in order to stabilize the motor 44, the number of motor fixing portions 68 is preferably three or more.

The radiator 46 is located radially outside the motor 44 . As shown in FIG. 6 , the heat radiator 46 has a heat radiator cylindrical portion 70 and a plurality of fins 72 . The radiator tubular portion 70 is attached to the motor housing 58 so as to cover the outer peripheral surface of the motor housing 58 . Each fin 72 extends radially outwardly of the radiator tubular portion 70 from the radiator tubular portion 70 and extends in the axial direction of the radiator tubular portion 70 (the axial direction of the motor 44). A plurality of fins 72 surrounds the radiator tubular portion 70 . A space extending in the axial direction of the radiator tubular portion 70 is formed between the two fins 72 adjacent to each other. Note that the radiator 46 and the motor housing 58 may be integrated. For example, motor housing 58 may have multiple fins 72 .

As shown in FIG. 3 , a motor cooling flow path 74 is formed between the motor housing 58 and the radiator tubular portion 70 . The motor cooling flow path 74 is formed along the outer peripheral surface of the motor 44 and the inner peripheral surface of the radiator 46 . The motor cooling flow path 74 is divided into a plurality of portions aligned in the axial direction of the motor 44 . However, the channels of each portion communicate with each other at a plurality of locations.

The radiator 46 is formed with an inlet 74i (FIG. 7) and an outlet 74o (FIG. 7) of the motor cooling flow path 74 . A coolant flows through the motor cooling flow path 74 . The coolant flows into the motor cooling channel 74 from the inlet 74i, flows through the motor cooling channel 74, and flows out from the outlet 74o. Note that the motor cooling flow path 74 may be formed in the motor housing 58 . Also, the motor cooling flow path 74 may be formed in the heat radiator cylindrical portion 70 . Thus, the motor cooling channel 74 may be arranged between the stator 64 and the plurality of fins 72 .

A motor mount 48 is positioned around the heat sink 46 with each fin 72 spaced apart. A motor mount 48 surrounds the motor 44 and the heat sink 46 . Motor mount 48 is received in hole 42 of fairing 40 along with motor 44 and heat sink 46 . A mount placement portion 76 is formed on a part of the inner peripheral surface (the inner peripheral surface forming the hole 42 ) between the upper end portion and the lower end portion of the fairing 40 . The motor mount 48 is arranged in the mount arrangement portion 76 . The motor mount 48 has a mount tube portion 78, a mount fixing portion 80, a first support portion 82, and two second support portions 84 (FIG. 5).

The mount tube portion 78 accommodates the motor 44 to which the radiator 46 is attached. The mount tube portion 78 surrounds the radiator 46 and the motor 44 that are housed therein. The mount tube portion 78 extends in the axial direction of the motor 44 . The inner diameter of the mount tube portion 78 is substantially equal to the inner diameter of the hole 42 of the fairing 40 . Also, the axis of the mount tube portion 78 overlaps with the axis of the hole 42 . When the motor mount 48 is arranged in the mount arrangement portion 76, it is preferable that the steps and gaps at the boundary between the inner peripheral surface of the mount cylinder portion 78 and the inner peripheral surface of the fairing 40 are as small as possible.

The inner peripheral surface of the fairing 40 and the inner peripheral surface of the mount tube portion 78 function as a duct 86 penetrating vertically. The motor 44 and the radiator 46 are located inside the duct 86 . Although the details will be described later, cooling air flows through the duct 86 by rotating the fan 56 . By reducing the steps and gaps at the boundary between the inner peripheral surface of the mount cylinder portion 78 and the inner peripheral surface of the fairing 40, the pressure loss of the flow of the cooling air can be reduced.

A mount fixing portion 80 fixes the motor mount 48 to the frame 38 . For example, the mount fixing portion 80 is a flange extending left and right. The mount fixing portion 80 is fixed to the frame 38 of the boom 18 by bolts, welding, or the like. Note that the mount fixing portion 80 may not be a flange. For example, the mount fixing portion 80 may be the lower end portion of the mount tube portion 78 . In this case, the frame 38 may have a protruding portion that protrudes upward, and the mount fixing portion 80 (lower end portion of the mount tube portion 78) may fit into the protruding portion of the frame 38.

As shown in FIG. 5 , the first support portion 82 supports each motor fixing portion 68 of the motor housing 58 . For example, the first support portion 82 is positioned at the upper end portion of the mount tube portion 78 . Each of the two second supports 84 supports the actuator 54 . For example, the two second support portions 84 protrude from the outer peripheral portion of the mount tube portion 78 . The two second support portions 84 are arranged along the extending direction of the boom 18 .

The upper end of the motor mount 48 , that is, the first support portion 82 is located above the upper end of each fin 72 . Thereby, each first support portion 82 can support the motor 44 without contacting each fin 72 . On the other hand, the lower end of the motor mount 48 is located above the lower end of each fin 72 . However, the lower end of the motor mount 48 may be positioned below the lower end of each fin 72 . Also, the lower end of the motor mount 48 may be positioned at the same height as the lower end of each fin 72 .

Motor mount 48 functions as a fixing member that secures motor 44 to frame 38 . The motor mount 48 also functions as a duct 86 that guides cooling air around the motor 44 . More specifically, the motor mount 48 also functions as a duct 86 that guides cooling air between two fins 72 adjacent to each other. The motor mount 48 also functions as a support member that supports the actuator 54 . Alternatively, the motor mount 48 may be formed on the frame 38 of the boom 18 . That is, frame 38 may directly support motor 44 .

A gearbox 50 is positioned above the motor 44 . Gearbox 50 has a plurality of gears that connect motor rotation shaft 60 of motor 44 and propeller rotation shaft 34 of propeller 30 . A plurality of gears reduce the rotation speed of the motor rotation shaft 60 and transmit it to the propeller rotation shaft 34 . Note that the gearbox 50 may be integrated with the motor 44 . For example, multiple gears may be provided inside the motor housing 58 .

The gearbox 50 rotatably supports the propeller rotating shaft 34 . As shown in FIG. 5, a plurality of beams 88 are formed on the outside of gearbox 50 . Each beam 88 extends in the axial direction of the propeller rotating shaft 34 and in the radial direction of the propeller rotating shaft 34 . In this embodiment, the gearbox 50 has four beams 88 . Each beam portion 88 is arranged at regular intervals in the circumferential direction around the axis of the propeller rotating shaft 34 .

A variable pitch mechanism 52 adjusts the pitch of the blades 36 of the propeller 30 . The variable pitch mechanism 52 has a moving member 90 . The moving member 90 is vertically movable along the propeller rotating shaft 34 . The moving member 90 is connected to a link mechanism (not shown). The link mechanism changes the pitch of each blade 36 according to movement of the moving member 90 . As shown in FIG. 5 , the moving member 90 extends in two radially outward directions of the propeller rotation shaft 34 with the propeller rotation shaft 34 as the center. Specifically, the moving member 90 extends along the extending direction of the boom 18 . A first actuator 54 is connected to one end (front end) of the moving member 90 . A second actuator 54 is connected to the other end (rear end) of the moving member 90 .

Each actuator 54 can extend and contract in the vertical direction. Each actuator 54 has, for example, a ball screw. The upper end of the first actuator 54 is connected to the front end of the moving member 90 . The lower end of the first actuator 54 is connected to the front second support 84 . The upper end of the second actuator 54 is connected to the rear end of the moving member 90 . A lower end of the second actuator 54 is connected to a rear second support 84 . The two actuators 54 operate in unison. The two actuators 54 move the moving member 90 up and down.

Fan 56 is positioned below motor 44 . The fan 56 is connected to the motor rotating shaft 60 . Therefore, when the motor rotating shaft 60 rotates, the fan 56 rotates. Basically, since the motor rotating shaft 60 rotates in one direction, the fan 56 also rotates in one direction. When the fan 56 rotates, cooling air is generated in the duct 86 from top to bottom.

[3 Cooling system 92]
A cooling system 92 for cooling the motor 44 and the inverter circuit 104 will be described with reference to FIGS. 7 and 8. FIG. FIG. 7 is a block diagram of cooling system 92 . FIG. 8 is a layout diagram of the motor 44 and the inverter device 96. As shown in FIG.

Electric power is supplied to the motor 44 from the power supply through the inverter circuit 104 . The motor 44 and the inverter circuit 104 generate heat. Aircraft 10 has a cooling system 92 that cools motor 44 and inverter circuit 104 . As shown in FIG. 7 , cooling system 92 includes flight controller 94 , inverter device 96 , motor 44 and cooling circuit 100 .

The flight controller 94 has a processor such as a CPU and memory. A flight controller 94 is located on the fuselage 12 . Flight controller 94 provides overall control of aircraft 10 . The flight controller 94 determines a control target and a control amount according to the operation performed by the pilot, the state of the aircraft 10, etc., and outputs an instruction signal to the controller of the control target. Flight controller 94 also controls two actuators 54 .

The inverter device 96 has an inverter controller 102 and an inverter circuit 104 . One inverter device 96 is provided for one motor 44 . For example, as shown in FIG. 8, the inverter devices 96 are placed near the corresponding motors 44 . Specifically, the inverter device 96 is located on the boom 18 along with the motor 44 .

The inverter controller 102 has a processor such as a CPU and a memory. Inverter controller 102 controls motor 44 corresponding to inverter device 96 . The inverter controller 102 outputs a control signal to the inverter circuit 104 according to the instruction signal output from the flight controller 94 . Inverter controller 102 also controls pump 112 of cooling circuit 100 . The motor 44 is provided with a temperature sensor (not shown). The inverter circuit 104 is provided with a temperature sensor (not shown). For example, the inverter controller 102 acquires the temperature and the like detected by each temperature sensor. The inverter controller 102 calculates the flow rate of the pump 112 corresponding to each temperature based on maps, arithmetic expressions, etc. stored in memory. The inverter controller 102 controls the flow rate of the pump 112 so as to achieve the calculated rotational speed.

The inverter circuit 104 is configured, for example, as a multi-phase full-bridge type. The inverter circuit 104 converts the DC power supplied from the power supply into multi-phase AC power by switching operation of a switching element (not shown), and supplies the multi-phase AC power to the motor 44 . The switching element is turned on and off according to a control signal output from inverter controller 102 .

Cooling circuit 100 includes motor cooling channel 74 , inverter cooling channel 106 , first channel 108 , second channel 110 and pump 112 . The cooling circuit 100 is a closed circuit that circulates coolant.

As described with reference to FIG. 3 , the motor cooling passage 74 is provided around the stator 64 of the motor 44 . An outlet 74 o of the motor cooling channel 74 communicates with the first channel 108 . An inlet 74 i of the motor cooling channel 74 communicates with the second channel 110 . On the other hand, inverter cooling flow path 106 is provided around inverter circuit 104 . An inlet 106 i of the inverter cooling channel 106 communicates with the first channel 108 . An outlet 106 o of the inverter cooling channel 106 communicates with the second channel 110 .

A pump 112 is provided in the first flow path 108 . Pump 112 circulates the coolant within cooling circuit 100 . For example, coolant flows from pump 112 through first flow path 108 , inverter cooling flow path 106 , second flow path 110 , motor cooling flow path 74 , first flow path 108 and back to pump 112 .

[4 Cooling Method for Motor 44 and Inverter Circuit 104]
The inverter controller 102 outputs a control signal to the inverter circuit 104 to rotate the motor 44 . As the motor 44 rotates, the propeller 30 rotates and the fan 56 rotates. Then, at the upper opening of the duct 86, outside air is sucked from the outside of the duct 86 into the inside. The outside air becomes cooling air. In FIG. 3, the cooling air is indicated by an arrow W. As shown in FIG. The cooling air flows downward inside the duct 86 . The cooling air passes between two adjacent motor fixing portions 68 (FIG. 4) and flows into the motor mount 48 . The cooling air flows downward inside the motor mount 48 along the radiator 46 . The cooling air cools the radiator 46 . Cooling air is discharged from the inside of the duct 86 to the outside at the lower opening of the duct 86 .

Inverter controller 102 operates pump 112 . When pump 112 operates, coolant circulates through cooling circuit 100 . The coolant absorbs heat from the motor 44 and the inverter circuit 104 and radiates the heat to the radiator 46 . The radiator 46 is cooled by cooling air. That is, the temperature of the coolant drops in the motor cooling passage 74 .

Thus, according to the present embodiment, the radiator 46 provided for cooling the motor 44 has the function of cooling the inverter circuit 104 .

[5 Modified Example of Cooling System 92]
FIG. 9 is a block diagram of a variation of cooling system 92 . For example, the distance from flight controller 94 to pump 112 may be less than the distance from inverter device 96 (inverter controller 102) to pump 112 . In such cases, the flight controller 94 may directly control the pump 112, as shown in FIG.

[6 Inventions Obtained from Embodiments]
Inventions that can be understood from the above embodiments will be described below.

An aspect of the present invention is a cooling system (92) for cooling a motor (44) that rotates a propeller (30) of an electric aircraft (10) and an inverter device (96) that controls operation of the motor, comprising: a heat radiator (46) having a plurality of fins (72) positioned radially outside the motor, and a motor positioned between a stator (64) of the motor and the plurality of fins to flow cooling liquid. a cooling flow path (74), an inverter cooling flow path (106) for cooling the inverter device by flowing the cooling liquid, and a first flow for flowing the cooling liquid from the motor cooling flow path to the inverter cooling flow path. a passage (108), a second passage (110) through which the cooling liquid flows from the inverter cooling passage to the motor cooling passage, and one of the first passage and the second passage. a pump (112) that flows from the motor cooling flow path through the first flow path, the inverter cooling flow path, the second flow path, and back to the motor cooling flow path; Heat is absorbed from each of the motor and the inverter device and radiated to the fins.

In the above configuration, the radiator that cools the motor also has the function of cooling the inverter device. Therefore, the aircraft does not need to have a device for cooling the inverter device and a device for cooling the motor separately. Therefore, according to the above configuration, the motor and the inverter device can be cooled with a simple and lightweight configuration.

In the aspect of the present invention, the inverter device has an inverter circuit (104) and an inverter controller (102) that controls switching elements of the inverter circuit, and the inverter controller controls the operation of the pump. The flow rate of the cooling liquid may be adjusted by

In an aspect of the present invention, the inverter device has an inverter circuit and an inverter controller that controls switching elements of the inverter circuit, and the electric aircraft has a flight controller (94) that outputs a control signal to the inverter controller. and the flight controller may regulate the flow rate of the coolant by controlling operation of the pump.

In an aspect of the present invention, the distance from the flight controller to the pump may be shorter than the distance from the inverter device to the pump.

According to the above configuration, the length of the signal line for outputting the instruction signal to the pump is shortened.

In an aspect of the present invention, a fan (56) may be provided to supply cooling air between two fins adjacent to each other.

According to the above configuration, the motor can be efficiently cooled.

In an aspect of the present invention, the fan may be connected to the motor shaft (60) of the motor.

According to the above configuration, there is no need for a separate motor for rotating the fan.

DESCRIPTION OF SYMBOLS 10... Electric aircraft, aircraft 30... Propeller 44... Motor 46... Radiator 56... Fan 64... Stator 72... Fin 74... Motor cooling channel 92... Cooling system 94... Flight controller 96... Inverter device 102... Inverter controller 104... Inverter circuit 106 Inverter cooling channel 108 First channel 110 Second channel 112 Pump

Claims (6)

A cooling system for cooling a motor that rotates a propeller of an electric aircraft and an inverter device that controls the operation of the motor,
a radiator positioned radially outward of the motor and having a plurality of fins;
a motor cooling passage located between the stator of the motor and the plurality of fins, through which cooling liquid flows;
an inverter cooling flow path for cooling the inverter device by flowing the cooling liquid;
a first flow path for flowing the coolant from the motor cooling flow path to the inverter cooling flow path;
a second flow path for flowing the coolant from the inverter cooling flow path to the motor cooling flow path;
A pump provided in either one of the first flow path and the second flow path,
The cooling liquid flows from the motor cooling flow path through the first flow path, the inverter cooling flow path, and the second flow path in that order, returns to the motor cooling flow path, and flows from each of the motor and the inverter device. A cooling system that absorbs heat and releases heat to the fins. The cooling system of claim 1, comprising:
The inverter device has an inverter circuit and an inverter controller that controls switching elements of the inverter circuit,
The cooling system, wherein the inverter controller adjusts the flow rate of the coolant by controlling operation of the pump. The cooling system of claim 1, comprising:
The inverter device has an inverter circuit and an inverter controller that controls switching elements of the inverter circuit,
The electric aircraft includes a flight controller that outputs a control signal to the inverter controller,
The cooling system, wherein the flight controller regulates the flow rate of the coolant by controlling operation of the pump. A cooling system according to claim 3, wherein
The cooling system, wherein the distance from the flight controller to the pump is shorter than the distance from the inverter device to the pump. The cooling system of claim 1, comprising:
A cooling system comprising a fan that supplies cooling air between the two fins adjacent to each other. A cooling system according to claim 5, wherein
The cooling system, wherein the fan is connected to a motor shaft of the motor.

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