JP7557455B2 - Propeller device - Google Patents

Description

The present invention relates to a propeller device equipped with a motor that rotates a propeller of an electric aircraft.

In recent years, there has been active development of electric aircraft. One such aircraft is, for example, an electric vertical take-off and landing aircraft. An electric vertical take-off and landing aircraft is called an eVTOL. An electric aircraft includes multiple propeller devices. The propeller devices include propellers and electric motors. In this specification, the electric motors are also simply referred to as motors. The motors rotate the propellers.

Patent Document 1 shows a technique for cooling the motor of an electric aircraft (multicopter). In this technique, multiple fins are formed on the outer circumferential surface of the motor. In addition, a fan wheel is provided on the outside of the motor. The fan wheel is connected to the rotating shaft of the motor. In this structure, heat from the motor is transferred to each of the fins. As the motor rotates, the fan wheel rotates. Then, cooling air flows between adjacent fins. As a result, each fin is cooled by the cooling air.

US Patent Application Publication No. 2020/0244139

Patent Document 1 shows that an arm is positioned above the machine body. Furthermore, Patent Document 1 shows that a motor is fixed to the arm. However, Patent Document 1 does not specifically show the fixing structure of the motor to the arm. In order to efficiently cool the motor, it is preferable to make the cooling air flowing along the motor as smooth as possible. To achieve this, some ingenuity is required in the fixing structure of the motor.

The present invention aims to solve the above-mentioned problems.

The first aspect of the present invention is a motor mount that fixes a motor that rotates a propeller to an electric aircraft, and includes a mount tube that extends in the axial direction of the motor, surrounds the motor, and guides cooling air around the motor to cool the motor, and a mount support that is located at one end of the mount tube in the axial direction of the motor and supports the motor.

A second aspect of the present invention is a propeller device having a motor that rotates a propeller of an electric aircraft, comprising a motor mount that extends in the axial direction of the motor, surrounds the motor, and fixes the motor to the electric aircraft, and a housing that penetrates in the vertical direction and houses the motor mount and the motor, and the housing and the motor mount guide cooling air that cools the motor around the motor.

The present invention allows the motor to be fixed to the electric aircraft and allows cooling air to flow smoothly around the motor.

FIG. 1 is a perspective view of an electric aircraft. FIG. 2 is a perspective view of the propeller assembly excluding the fairing. FIG. 3 is a cross-sectional view of the propeller device. FIG. 4 is a cross-sectional view of the propeller device shown in FIG. 3 taken along line IV-IV. FIG. 5 is a side view of the drive unit and the propeller. FIG. 6 is a perspective view of the heat sink. FIG. 7 is a block diagram of the cooling system. FIG. 8 is a layout diagram of the motor and the inverter device. FIG. 9 is a block diagram of a modified example of the cooling system. FIG. 10 is a front view of the propeller assembly without the fairing.

[1 Overall configuration of electric aircraft 10]
The overall configuration of the electric aircraft 10 will be described with reference to Fig. 1. Fig. 1 is a perspective view of the electric aircraft 10. The electric aircraft 10 of this embodiment is an eVTOL aircraft. However, the present invention can also be used in a multicopter. In this specification, the electric aircraft 10 is also simply referred to as the aircraft 10.

The aircraft 10 comprises a fuselage 12, a front wing 14, a rear wing 16, two booms 18, a plurality of propeller devices 20 for takeoff and landing, and a plurality of propeller devices 22 for cruising. The fuselage 12 is long in the longitudinal direction. The front wing 14 is disposed forward of the mid-section of the fuselage 12 in the longitudinal direction. The front wing 14 is connected to the upper part of the fuselage 12. The rear wing 16 is disposed rearward of the mid-section of the fuselage 12 in the longitudinal 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 fore-aft direction. The right boom 18R is disposed to the right of the fuselage 12. The right boom 18R curves in an arc toward the right. The right boom 18R is connected to the right wing tip of the front wing 14 and is connected to the right wing of the rear wing 16. The left boom 18L is disposed to the left of the fuselage 12. The left boom 18L curves in an arc toward the left. The left boom 18L is connected to the left wing tip of the front wing 14 and is connected to the left wing of the rear wing 16. Each boom 18 may be straight.

Each boom 18 is equipped with multiple propeller devices 20. In this embodiment, each boom 18 is equipped with four propeller devices 20. Note that each boom 18 may be equipped with two, three, five or more propeller devices 20. In each boom 18, the four propeller devices 20 are arranged in sequence along the extension direction of the boom 18.

The fuselage 12 is equipped with multiple propeller devices 22. In this embodiment, the fuselage 12 is equipped with two propeller devices 22. The fuselage 12 may be equipped with one or three or more propeller devices 22. The two propeller devices 22 are arranged side by side on the left and right at the rear end of the fuselage 12.

[2. Structure of the Propeller Device 20]
A takeoff and landing propeller device 20 provided on the aircraft 10 will be described with reference to Figures 2 to 6. Figure 2 is a perspective view of the propeller device 20 excluding the fairing 40. Figure 3 is a cross-sectional view of the propeller device 20. Figure 3 is a cross-sectional view perpendicular to the extension direction of the boom 18 and including the axis of the motor 44. Figure 4 is a cross-sectional view of the propeller device 20 shown in Figure 3 taken along line IV-IV. Figure 4 is a cross-sectional view of the propeller device 20 disposed at the very front of the left boom 18L. The cross-sectional structures of the other propeller devices 20 are basically the same as the cross-sectional structure shown in Figure 4. Figure 5 is a side view of the drive unit 28 and the propeller 30. Figure 6 is a perspective view of the heat sink 46.

As shown in FIG. 3, the propeller device 20 has a housing 26, a drive unit 28, and a propeller 30. In rotary wing aircraft, a "propeller" is also called a "rotor." However, in this specification, the term "propeller" is used to avoid confusion between the "rotor" and the rotor 66 of the motor 44. The propeller 30 has a hub 32, a propeller shaft 34, and a number of blades 36.

The storage section 26 has a frame 38 and a fairing 40. The frame 38 is the skeleton of the boom 18. The frame 38 is a component that supports the drive unit 28, the inverter device 96 (Figure 7), etc. The frame 38 is connected to the front wing 14 and the rear wing 16. The fairing 40 is a component that covers the frame 38. The fairing 40 forms a hole 42 that penetrates in the vertical direction. The storage section 26 stores the drive unit 28 in the hole 42.

The drive unit 28 has a motor 44, a heat sink 46, a motor mount 48, a gear box 50, a variable pitch mechanism 52, two actuators 54, and a fan 56. The axes of each component overlap with each other. There may be three or more actuators 54.

The motor 44 is an AC motor. As shown in FIG. 3, the motor 44 has a motor housing 58, a motor shaft 60, two bearings 62U and 62L, a stator 64, and a rotor 66. The motor housing 58 is formed by combining a plurality of members. The motor housing 58 accommodates a part of the motor shaft 60, the stator 64, and the rotor 66. The bearing 62U is fixed to the upper end of the motor housing 58. The bearing 62L is fixed to the lower end of the motor housing 58. Each of the two bearings 62U and 62L rotatably supports the motor shaft 60. The motor shaft 60 is fixed to the rotor 66. The stator 64 is located radially outside the rotor 66. Coils (not shown) of each phase are arranged on the stator 64. AC power is supplied to the coils of each phase from a power source via an inverter circuit 104 (FIG. 7).

As shown in FIG. 4, the motor housing 58 has four motor fixing parts 68. Each motor fixing part 68 protrudes radially outward from the outer periphery of the motor housing 58. Each motor fixing part 68 is located relatively at the upper part in the motor housing 58. Each motor fixing part 68 is located at the same height in the up-down direction. Each motor fixing part 68 is arranged at equal intervals in the circumferential direction around the axis of the motor 44. For example, each motor fixing part 68 is located above the stator 64 and the rotor 66. Each motor fixing part 68 is fixed to the first support part 82 of the motor mount 48 by bolts, welding, or the like. The number of motor fixing parts 68 may be two. However, in order to stabilize the motor 44, it is preferable that the number of motor fixing parts 68 is three or more.

The heat sink 46 is located radially outside the motor 44. As shown in FIG. 6, the heat sink 46 has a heat sink tube 70 and a plurality of fins 72. The heat sink tube 70 is attached to the motor housing 58 so as to cover the outer circumferential surface of the motor housing 58. Each fin 72 extends from the heat sink tube 70 radially outward of the heat sink tube 70 and in the axial direction of the heat sink tube 70 (the axial direction of the motor 44). The plurality of fins 72 surround the heat sink tube 70. A space extending in the axial direction of the heat sink tube 70 is formed between two adjacent fins 72. The heat sink 46 and the motor housing 58 may be integral. For example, the motor housing 58 may have a plurality of fins 72.

As shown in FIG. 3, a motor cooling passage 74 is formed between the motor housing 58 and the heat sink tube portion 70. The motor cooling passage 74 is formed along the outer peripheral surface of the motor 44 and the inner peripheral surface of the heat sink 46. The motor cooling passage 74 is divided into multiple parts aligned in the axial direction of the motor 44. However, the passages of each part are connected to each other at multiple points.

The heat sink 46 is formed with an inlet 74i (FIG. 7) and an outlet 74o (FIG. 7) of the motor cooling passage 74. Coolant flows through the motor cooling passage 74. The coolant flows into the motor cooling passage 74 from the inlet 74i, flows through the motor cooling passage 74, and flows out to the outside from the outlet 74o. The motor cooling passage 74 may be formed in the motor housing 58. The motor cooling passage 74 may also be formed in the heat sink tube portion 70. In this way, the motor cooling passage 74 may be disposed between the stator 64 and the multiple fins 72.

The motor mount 48 is positioned around the heat sink 46 while being spaced apart from each of the fins 72. The motor mount 48 surrounds the motor 44 and the heat sink 46. The motor mount 48 is housed in the hole 42 of the fairing 40 together with the motor 44 and the heat sink 46. A mount arrangement portion 76 is formed in a portion of the inner circumferential surface (the inner circumferential surface forming the hole 42) between the upper end and the lower end 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 (Figure 5).

The mount tube portion 78 houses the motor 44 to which the heat sink 46 is attached. The mount tube portion 78 surrounds the housed heat sink 46 and the motor 44. The mount tube portion 78 extends in the axial direction of the motor 44. The inner diameter of the mount tube portion 78 is approximately equal to the inner diameter of the hole 42 of the fairing 40. In addition, the axis of the mount tube portion 78 overlaps with the axis of the hole 42. When the motor mount 48 is placed in the mount placement portion 76, it is preferable that the step and gap at the boundary between the inner surface of the mount tube portion 78 and the inner surface of the fairing 40 are as small as possible.

The inner circumferential surface of the fairing 40 and the inner circumferential surface of the mount tube 78 function as a duct 86 that penetrates in the vertical direction. The motor 44 and the heat sink 46 are located inside the duct 86. As will be described in detail later, cooling air flows through the duct 86 when the fan 56 rotates. By reducing the step and gap at the boundary between the inner circumferential surface of the mount tube 78 and the inner circumferential surface of the fairing 40, the pressure loss of the cooling air flow can be reduced.

The mount fixing part 80 fixes the motor mount 48 to the frame 38. For example, the mount fixing part 80 is a flange extending left and right. The mount fixing part 80 is fixed to the frame 38 of the boom 18 by bolts, welding, etc. Note that the mount fixing part 80 does not have to be a flange. For example, the mount fixing part 80 may be the lower end of the mount tube part 78. In this case, the frame 38 may have a protruding part that protrudes upward, and the mount fixing part 80 (the lower end of the mount tube part 78) may be engaged with the protruding part 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 located at the upper end of the mount tube portion 78. Each of the two second support portions 84 supports an actuator 54. For example, the two second support portions 84 protrude from the outer periphery of the mount tube portion 78. The two second support portions 84 are arranged along the extension direction of the boom 18.

The upper end of the motor mount 48, i.e., the first support portion 82, is located above the upper ends of the fins 72. This allows each first support portion 82 to 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 ends of each fin 72. However, the lower end of the motor mount 48 may be located below the lower ends of each fin 72. The lower end of the motor mount 48 may also be located at the same height as the lower ends of each fin 72.

The motor mount 48 functions as a fixing member that fixes the motor 44 to the 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 adjacent fins 72. The motor mount 48 also functions as a support member that supports the actuator 54. The motor mount 48 may be formed on the frame 38 of the boom 18. In other words, the frame 38 may directly support the motor 44.

The gearbox 50 is located above the motor 44. The gearbox 50 has multiple gears that connect the motor shaft 60 of the motor 44 and the propeller shaft 34 of the propeller 30. The multiple gears reduce the rotational speed of the motor shaft 60 and transmit it to the propeller shaft 34. The gearbox 50 may be integrated with the motor 44. For example, the 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 beam portions 88 are formed on the outside of the gearbox 50. Each beam portion 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 beam portions 88. Each beam portion 88 is disposed at equal intervals in the circumferential direction around the axis of the propeller rotating shaft 34.

The 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 can move up and down along the propeller rotation shaft 34. The moving member 90 is connected to a link mechanism (not shown). The link mechanism changes the pitch of each blade 36 in response to the movement of the moving member 90. As shown in FIG. 5, the moving member 90 extends in two directions radially outward from the propeller rotation shaft 34, centered on the propeller rotation shaft 34. Specifically, the moving member 90 extends along the extension 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 expand 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 portion 84. The upper end of the second actuator 54 is connected to the rear end of the moving member 90. The lower end of the second actuator 54 is connected to the rear second support portion 84. The two actuators 54 operate in unison. The two actuators 54 move the moving member 90 up and down.

The fan 56 is located below the motor 44. The fan 56 is connected to the motor shaft 60. Therefore, when the motor shaft 60 rotates, the fan 56 rotates. Basically, the motor shaft 60 rotates in a fixed direction, so the fan 56 also rotates in a fixed direction. When the fan 56 rotates, a cooling air flow from top to bottom is generated in the duct 86.

[3 Cooling System 92]
7 and 8, a cooling system 92 for cooling the motor 44 and the inverter circuit 104 will be described. Fig. 7 is a block diagram of the cooling system 92. Fig. 8 is a layout diagram of the motor 44 and the inverter device 96.

The motor 44 is supplied with power from a power source via an inverter circuit 104. The motor 44 and the inverter circuit 104 generate heat. The aircraft 10 has a cooling system 92 that cools the motor 44 and the inverter circuit 104. As shown in FIG. 7, the cooling system 92 has a flight controller 94, an inverter device 96, the motor 44, and a cooling circuit 100.

The flight controller 94 has a processor such as a CPU and a memory. The flight controller 94 is disposed in the fuselage 12. The flight controller 94 performs overall control of the aircraft 10. The flight controller 94 determines the control object and the control amount according to the operation performed by the pilot and the state of the aircraft 10, and outputs an instruction signal to the controller of the controlled object. The flight controller 94 also controls the 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 device 96 is disposed near the corresponding motor 44. Specifically, the inverter device 96 is disposed on the boom 18 together with the motor 44.

The inverter controller 102 has a processor such as a CPU and a memory. The inverter controller 102 controls the motor 44 corresponding to the inverter device 96. The inverter controller 102 outputs a control signal to the inverter circuit 104 in response to an instruction signal output from the flight controller 94. The inverter controller 102 also controls the pump 112 of the 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 detected by each temperature sensor. The inverter controller 102 calculates the flow rate of the pump 112 corresponding to each temperature based on a map, an arithmetic expression, etc. stored in the memory. The inverter controller 102 controls the flow rate of the pump 112 so that the calculated rotation speed is obtained.

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 source into multi-phase AC power by the switching operation of a switching element (not shown) and supplies it to the motor 44. The switching element performs an on/off operation in response to a control signal output from the inverter controller 102.

The cooling circuit 100 has a motor cooling passage 74, an inverter cooling passage 106, a first passage 108, a second passage 110, and a pump 112. The cooling circuit 100 is a closed circuit that circulates the coolant.

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

The pump 112 is provided in the first flow path 108. The pump 112 circulates the coolant inside the cooling circuit 100. For example, the coolant flows from the pump 112 through the first flow path 108, the inverter cooling flow path 106, the second flow path 110, the motor cooling flow path 74, and the first flow path 108 in this order, and then returns to the 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. When 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 drawn from the outside to the inside of the duct 86. The outside air becomes cooling air. In FIG. 3, the cooling air is indicated by an arrow W. The cooling air flows downward inside the duct 86. The cooling air passes between two adjacent motor fixing parts 68 (FIG. 4) and flows into the inside of the motor mount 48. The cooling air flows downward inside the motor mount 48 along the heat sink 46. The cooling air cools the heat sink 46. At the lower opening of the duct 86, the cooling air is discharged from the inside of the duct 86 to the outside.

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

In this way, according to this embodiment, the heat sink 46 provided to cool the motor 44 also has the function of cooling the inverter circuit 104.

[5. Modifications of the Cooling System 92]
Fig. 9 is a block diagram of a modified example of the cooling system 92. For example, the distance from the flight controller 94 to the pump 112 may be shorter than the distance from the inverter device 96 (inverter controller 102) to the pump 112. In such a case, as shown in Fig. 9, the flight controller 94 may directly control the pump 112.

[6. Moment acting on the propeller device 20]
Fig. 10 is a front view of the propeller device 20 excluding the fairing 40. When the propeller 30 rotates, a moment is generated at the root of the propeller 30 about an axis parallel to the extension direction of the boom 18. In Fig. 10, the direction of the moment is indicated by arrow A. The moment acts on a plurality of beams 88 formed in the gear box 50. The force acting on the beams 88 is transmitted to the frame 38 via the motor mount 48.

On the other hand, a torsional reaction force is generated in the frame 38. In FIG. 10, the direction of the torsional reaction force is indicated by arrow B. In the frame 38, the force caused by the moment and the torsional reaction force are balanced. Therefore, the force acting on the boom 18 decreases as the propeller 30 rotates.

[7 Invention Obtained from the Embodiments]
The invention that can be understood from the above embodiment will be described below.

The first aspect of the present invention is a motor mount (48) that fixes a motor (44) that rotates a propeller (30) to an electric aircraft (10), and includes a mount tubular portion (78) that extends in the axial direction of the motor, surrounds the motor, and guides cooling air to the periphery of the motor to cool the motor, and a mount support portion (82) that is located at one end of the mount tubular portion in the axial direction of the motor and supports the motor.

The above configuration allows the motor to be fixed to the electric aircraft. Furthermore, the above configuration allows cooling air to flow smoothly around the motor.

In a first aspect, the motor mount may include a mount fixing portion (80) that fixes the mount tubular portion to the electric aircraft.

A second aspect of the present invention is a propeller device (20) equipped with a motor that rotates a propeller of an electric aircraft, comprising a motor mount that extends in the axial direction of the motor, surrounds the motor, and fixes the motor to the electric aircraft, and a housing section (26) that penetrates in the vertical direction and houses the motor mount and the motor, and the housing section and the motor mount guide cooling air that cools the motor around the motor.

The above configuration allows the motor to be fixed to the electric aircraft. Furthermore, the above configuration allows cooling air to flow smoothly around the motor.

In a second aspect, the motor mount may include a mount tube portion that extends in the axial direction of the motor, surrounds the motor, and guides the cooling air around the motor, and a mount support portion that is located at one end of the mount tube portion in the axial direction of the motor and fixes multiple points of the motor.

In a second aspect, a plurality of fins (72) extending in the radial direction of the motor and in the axial direction of the motor are positioned between the motor and the mount cylinder, and the distance from the propeller to the mount support in the axial direction of the motor may be shorter than the distance from the propeller to each of the fins.

With the above configuration, the motor mount can support the motor 44 without contacting each of the fins.

In a second aspect, the electric aircraft may include a variable pitch mechanism (52) capable of changing the pitch of each blade (36) of the propeller, and an actuator (54) for operating the variable pitch mechanism, and the motor mount may support the actuator.

In a second aspect, a support part (50) is provided that is connected to the motor mount and rotatably supports the rotating shaft (34) of the propeller, and a plurality of beam parts (88) extending in the axial direction of the rotating shaft and in the radial direction of the rotating shaft may be formed on the outer peripheral part of the support part centered on the rotating shaft.

The above configuration reduces the force acting on the boom as the propeller rotates.

In a second aspect, the propeller device may include a fan (56) that supplies the cooling air to the housing and the motor mount.

The above configuration allows the motor to be cooled efficiently.

In a second aspect, the fan may be connected to the rotating shaft (60) of the motor.

The above configuration eliminates the need for a separate motor to rotate the fan.

10... Electric aircraft, aircraft 20... Propeller device 26... Housing 30... Propeller 34... Propeller rotating shaft (rotating shaft) 36... Blade 44... Motor 48... Motor mount 50... Gearbox (supporting part) 54... Actuator 56... Fan 60... Motor rotating shaft (rotating shaft)
72: Fin 78: Mount cylinder portion 80: Mount fixing portion 82: First support portion (mount support portion)
88…Beam

Claims (6)

A propeller device including a motor that rotates a propeller of an electric aircraft,
a motor mount extending in an axial direction of the motor, surrounding the motor, and fixing the motor to the electric aircraft;
a housing portion that penetrates in the vertical direction and houses the motor mount and the motor;
Equipped with
The motor mount is
a mount cylinder portion that extends in an axial direction of the motor, surrounds the motor, and guides cooling air to the periphery of the motor;
a mount support portion located at one end of the mount cylinder portion in an axial direction of the motor and configured to fix the motor at a plurality of points;
Equipped with
A propeller device, wherein the accommodation portion and the motor mount guide the cooling air that cools the motor to the periphery of the motor. 2. The propeller device according to claim 1 ,
a plurality of fins are positioned between the motor and the mount cylinder, the fins extending in a radial direction of the motor and in an axial direction of the motor;
A propeller device, wherein in an axial direction of the motor, a distance from the propeller to the mount support is shorter than a distance from the propeller to each of the fins. A propeller device including a motor that rotates a propeller of an electric aircraft,
a motor mount extending in an axial direction of the motor, surrounding the motor, and fixing the motor to the electric aircraft;
a housing portion that penetrates in the vertical direction and houses the motor mount and the motor;
Equipped with
the housing portion and the motor mount guide cooling air that cools the motor to a periphery of the motor,
The electric aircraft comprises:
A variable pitch mechanism capable of changing the pitch of each blade of the propeller;
An actuator that operates the variable pitch mechanism;
Preparation,
The motor mount supports the actuator. A propeller device including a motor that rotates a propeller of an electric aircraft,
a motor mount extending in an axial direction of the motor, surrounding the motor, and fixing the motor to the electric aircraft;
a housing portion that penetrates in the vertical direction and houses the motor mount and the motor;
a support portion connected to the motor mount and configured to rotatably support a rotation shaft of the propeller ;
Equipped with
the housing portion and the motor mount guide cooling air that cools the motor to a periphery of the motor,
A propeller device, wherein a plurality of beam portions extending in the axial direction of the rotating shaft and in the radial direction of the rotating shaft are formed on an outer circumferential portion of the support portion centered on the rotating shaft. A propeller device according to any one of claims 1 to 4 ,
A propeller device comprising: a fan that supplies the cooling air to the housing and the motor mount. 6. A propeller device according to claim 5 ,
A propeller device, wherein the fan is coupled to a rotating shaft of the motor.

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