JP2020037347A - Air vehicle - Google Patents

Abstract

To inhibit temperature rise of an electric component unit properly to achieve long life of an air vehicle.SOLUTION: An air vehicle (a drone) 10 includes: a body part 11; multiple frame parts 12 extending from the body part 11; propulsion drive parts 20, each having rotary vanes (a propeller) 22 provided at a tip of the frame part 12 and a motor 21 for rotating the rotary vanes 22; and an electric component unit for driving the propulsion drive parts 20. The frame part 12 is a hollow member having a space therein, has multiple air supply/discharge ports allowing communication between the space and the outside. The electric component unit is disposed in the space of the frame part 12 and between at least the two air supply/discharge ports.SELECTED DRAWING: Figure 1

Description

  The present invention relates to a flying object having a rotary wing, such as a multicopter.

In recent years, drones (multicopters) and the like have become widespread as small unmanned aerial vehicles capable of unmanned flight. Drones are used in various industries, including surveying, disaster relief, studying the natural environment, broadcasting sports, and spraying pesticides.
Although there are various shapes in the structure of a drone's fuselage, in general, a drone includes a main body, a plurality of frames extending radially from the main body, and a propulsion drive unit provided at a distal end of the frame. Prepare. The propulsion drive unit is a unit that generates lift and thrust for the flight of the airframe, and includes a propeller (rotor) that is a rotating wing and a motor that rotates the propeller.

  For example, Patent Document 1 discloses an unmanned rotary wing machine having four frames extending in an X-shape from a main body portion, and a motor for rotating a propeller (rotor) attached to a tip portion of the frame. ing. Here, the motor is a three-phase brushless DC motor having a U-phase, a V-phase, and a W-phase, and the rotation speed (rotation speed) of the motor is controlled by an electronic speed controller (ESC).

JP 2017-136914 A

At present, the life of a drone is largely due to accidents such as crash damage and missing. The main causes of the crash include loss of communication during flight, running out of battery, motor failure, and inexperienced maneuvers. For this reason, conventionally, with respect to extending the life of the drone, measures and improvements focused on the above points have been mainly performed.
By the way, various electric component units are mounted on the drone, and these electric component units generate heat when driven. Therefore, appropriately suppressing the rise in temperature of the electric component unit is also an important issue in extending the life of the drone. However, little measure has been taken so far in this regard.

  Therefore, an object of the present invention is to appropriately suppress a rise in the temperature of the electric component unit and extend the life of the flying object.

  In order to solve the above-mentioned problem, one aspect of the flying object according to the present invention is provided with a main body, a plurality of frame parts extending from the main body, and a tip part of the frame part, A propulsion drive unit having a motor for rotating the propulsion drive unit, and an electric component unit for driving the propulsion drive unit, wherein the frame unit is a hollow member having a space inside, and the frame A plurality of air supply / exhaust ports communicating between the outside of the unit and the space, and the electric component unit is disposed in the space of the frame unit and between at least two of the air supply / exhaust ports. .

  In this way, by forming the frame portion to have a hollow structure and forming a plurality of air supply / exhaust ports, it is possible to generate an air flow inside the frame portion. The air flowing inside the frame portion acts as a cooling air for cooling the electric component unit disposed inside the frame portion and between the two air supply / exhaust ports. Therefore, the temperature rise of the electric component unit can be appropriately suppressed. As a result, the life of the electric component unit can be extended, and as a result, the life of the flying object on which the electric component unit is mounted can be extended.

In the above-mentioned flying object, the electric component unit may include a speed control unit that controls a rotation speed of the motor.
The speed control unit includes a plurality of switching elements for controlling the rotation speed of the motor, and considerable heat generation is expected. Thus, by arranging the speed control unit that generates a large amount of heat inside the frame portion and cooling it by cooling air flowing inside the frame portion, the temperature rise of the speed control unit can be appropriately suppressed, and the effect can be reduced. It is possible to extend the life of the flying object.

Further, in the above-mentioned flying object, the frame portion may have the supply / exhaust port at an end on the propulsion drive unit side and an end on the body unit side, respectively. In this case, one end to the other end of the frame can be effectively used as a cooling air passage.
In the above-mentioned flying object, the air supply / exhaust port may be formed on an upper surface of an end of the frame portion on the propulsion drive unit side, at a position facing the rotating rotor. In this case, the air supply / exhaust port may be a cooling air inlet through which wind generated by the rotation of the rotating blades can be easily taken into the inside of the frame portion.
Further, in the above flying object, the air supply / exhaust port may be formed on a lower surface of an end portion of the frame portion on the main body portion side. In this case, the air supply / exhaust port can be a cooling air exhaust port that can appropriately exhaust air taken in from the cooling air intake to the outside of the frame portion.

Further, a cooling body for cooling the electric component unit may be attached to the electric component unit. In this case, the temperature rise of the electric component unit can be suppressed more efficiently.
Further, in the above flying object, the cooling body may be made of a carbon fiber reinforced carbon composite material. A carbon fiber reinforced carbon composite material is a material having low density and high thermal conductivity. Therefore, a lightweight cooling body having high cooling efficiency can be provided, and the electric component unit can be efficiently cooled without significantly increasing the weight of the flying body.

  ADVANTAGE OF THE INVENTION According to this invention, since an electric component unit can be forcibly air-cooled, the temperature rise of an electric component unit can be suppressed appropriately, and the life of a flying object can be extended.

It is a figure showing the example of whole composition of the flight object in this embodiment. It is a figure which shows the outline of the system configuration of a flying object. It is a figure showing a flow of wind in the inside of a frame part. It is a figure showing a flow of wind in the inside of a frame part. This is an example in which a cooling body is attached to the speed control unit.

Hereinafter, embodiments of the present invention will be described with reference to the drawings.
FIG. 1 is a diagram illustrating an example of the overall configuration of a flying object 10 according to the present embodiment. In the present embodiment, a case where the flying object 10 is a drone (multicopter) will be described.
The drone 10 includes a main body 11 and a plurality (four in this embodiment) of frame parts 12 extending from the main body 11. Further, the drone 10 includes a propulsion drive unit 20 provided at a tip portion of the frame portion 12 (an end portion that is not on the main body portion 11 side).
The propulsion drive unit 20 is a unit that generates lift and thrust for the body to fly, and includes a motor 21 and rotating wings (also referred to as propellers and rotors) 22 that are rotated by the motor 21. Here, the motor 21 is a three-phase brushless DC motor, and the rotation speed (the number of rotations) is controlled by a controller 32 described later.

Various electric component units are mounted on the main body 11 and the frame 12. Specifically, a receiving unit 31, a controller 32, a sensor unit 33, and a battery unit 34 are mounted on the main body unit 11. The frame unit 12 has a speed control unit 35 mounted thereon.
These electric component units are covered by a casing (including a cover or the like) 13 that forms the main body 11 and the frame 12.

FIG. 2 is a diagram schematically illustrating the system configuration of the drone 10.
The receiving unit 31 receives a signal transmitted from a pilot (not shown) and outputs the received signal to the controller 32. Here, the pilot is an instrument for the pilot to remotely operate the aircraft of the drone 10. The receiving unit 31 includes an antenna for receiving a signal transmitted from a pilot operated by the pilot.
The controller 32 includes a CPU, a ROM, a RAM, and the like, receives a signal received by the receiving unit 31 and a signal detected by the sensor unit 33, and controls flight of the aircraft of the drone 10 based on these signals.

The sensor unit 33 includes various sensors. For example, the sensor unit 33 includes a gyro sensor 33a, an acceleration sensor 33b, a barometric pressure sensor 33c, a GPS sensor 33d, and the like.
The gyro sensor 33a is, for example, a three-axis gyro, and detects the amount of change in the inclination of each of the roll axis, the pitch axis, and the yaw axis of the drone 10. The acceleration sensor 33b detects the acceleration of the aircraft of the drone 10. The acceleration sensor 33b may be, for example, a three-axis acceleration that detects acceleration in three directions of the XYZ axes. The air pressure sensor 33c detects the air pressure, and detects the altitude of the aircraft of the drone 10 based on the detected air pressure. The GPS sensor 33d detects the flight position of the aircraft of the drone 10.

The controller 32 determines the target rotation speed of each motor 21 based on the signal received by the reception unit 31 and the signal detected by the sensor unit 33, and adjusts the rotation speed of each motor 21 to the target rotation speed. To control the speed control unit 35.
The speed control units 35 are provided corresponding to one motor 21 respectively. In this embodiment, each speed control unit 35 includes an inverter circuit having six switching elements, and a drive circuit (gate driver) for turning on and off the switching elements. Here, the switching element is an FET (field effect transistor), a MOSFET (MOS type field effect transistor), an IGBT (insulated gate type bipolar transistor) or the like.

The controller 32 individually controls the rotation speed (rotation speed) of each motor 21 via the speed control unit 35, so that the drone 10 can control flight, such as takeoff, landing, forward movement, retreat, and roll, pitch, Attitude control such as yawing is performed.
Electric power is supplied from the battery unit 34 shown in FIG. 1 to the electric component units (31, 32, 33, 35) shown in FIG. The battery unit 34 can be, for example, a lithium rechargeable battery. The battery unit 34 is provided at the lower center of the main body 11 in order to stabilize the center of gravity of the body. The supply of electric power from the battery unit 34 to each electric component unit may be performed directly by wiring, or may be performed via a PMU (Power Management Unit).

  By the way, as described above, the speed control unit 35 has six switching elements in order to control the three-phase motor in a wide speed range. The switching element is a heating element that generates heat when a current flows. Since each of the speed control units 35 has six switching elements, considerable heat generation is expected. Therefore, if the cooling is not performed appropriately, for example, the temperature of the junction of the switching element may exceed a certain temperature, and a malfunction may occur in the switching element. Further, when the speed control unit 35 itself is heated to a high temperature, it may cause a malfunction of not only the switching element but also other electric components included in the speed control unit 35.

That is, in order to extend the life of the speed control unit 35, it is important to appropriately cool the switching element and to suppress an excessive rise in temperature of the speed control unit 35.
In this embodiment, in order to suppress the temperature rise of the speed control unit 35, the frame part 12 has a hollow structure, and the speed control unit 35 is disposed inside the hollow frame part 12. The inside of the hollow frame portion 12 is used as a cooling air passage, and the speed control unit 35 is cooled by cooling air passing through the inside of the frame portion 12.

FIG. 3 is a diagram illustrating an example of a cross-sectional structure of the frame unit 12.
The frame portion 12 is a hollow (tubular) member extending in one direction. The cross-sectional shape in a direction orthogonal to the longitudinal direction of the frame portion 12 is not particularly limited, and the frame portion 12 may have a hollow rectangular structure or a hollow hollow structure.
The frame section 12 includes at least one cooling air inlet 15 and at least one cooling air outlet 16. The cooling air inlet 15 and the cooling air exhaust port 16 are supply / exhaust ports formed in the frame portion 12 to communicate the outside of the frame portion 12 with the space inside the frame portion 12.

FIG. 3 shows an example in which a cooling air inlet 15 is formed at an end of the frame section 12 on the propulsion drive section 20 side, and a cooling air exhaust port 16 is formed at an end of the frame section 12 on the body section 11 side. . The speed control unit 35 is disposed inside the frame portion 12 and between the cooling air inlet 15 and the cooling air outlet 16.
Specifically, the cooling air intake 15 is formed on the upper surface of the frame unit 12 on the propulsion drive unit 20 side, at a position facing the rotating blade 22 (immediately below the rotating blade 22). The cooling air inlet 15 is also formed at an end surface of the frame portion 12 on the side of the propulsion drive unit 20 and at a position facing the propulsion drive unit 20. The cooling air inlet 15 is formed such that a part of the wind generated during the flight of the drone 10 enters the hollow inside of the frame portion 12.

The cooling air outlet 16 is formed on the lower surface of the frame portion 12 on the main body 11 side. The cooling air exhaust port 16 is formed such that air taken into the inside of the frame portion 12 from the cooling air inlet 15 is exhausted to the outside of the frame portion 12.
With the above-described configuration, as shown in FIG. 3, during the flight of the drone 10, a part 41 of the wind generated by the rotating rotor 22 is transmitted from the cooling air inlet 15 formed on the upper surface of the frame portion 12 to the frame portion. Enter inside 12. A part 42 of the wind generated by the rotating rotor 22 enters the inside of the frame 12 from the cooling air inlet 15 formed on the end face of the frame 12. Further, a part 43 of the wind generated as the body moves, such as moving forward, backward, ascending, and descending, also enters the inside of the frame portion 12 through the cooling air inlet 15 formed in the end face of the frame portion 12.

The wind 44 taken into the inside of the frame 12 flows inside the hollow frame 12 toward the main body 11. This wind 44 acts as a cooling wind for cooling the speed control unit 35 disposed inside the frame portion 12. That is, the speed control unit 35 is appropriately cooled by the wind 44 flowing inside the frame portion 12, and a rise in temperature is suppressed.
The air 45 that has cooled the speed control unit 35 is exhausted from a cooling air exhaust port 16 formed on the main body 11 side of the frame 12.

  In the example shown in FIG. 3, the cooling air intake 15 is formed by the upper surface of the frame portion 12 (the surface facing the rotary wing 22) and the end surface of the frame portion 12 (the surface of the propulsion drive portion 20 facing the motor 21). However, the position where the cooling air inlet 15 is formed is not limited to the position shown in FIG. The cooling air inlet 15 may be formed at a position where air generated during the flight of the drone 10 can be taken into the inside of the frame portion 12. Further, the number of cooling air inlets 15 is not limited to the number (two) shown in FIG.

Further, depending on the flight state of the airframe, as shown in FIG. 4, the wind 51 may flow into the inside of the frame portion 12 from the cooling air exhaust port 16 formed on the lower surface of the frame portion 12. For example, when the body is descending, wind is taken in from a cooling wind exhaust port 16 formed on the lower surface of the frame portion 12. In this case, the wind 52 taken into the inside of the frame part 12 flows toward the propulsion drive part 20 through the inside of the frame part 12, and cools the speed control unit 35 in the process. Then, a part 53 of the air that has cooled the speed control unit 35 is exhausted from the cooling air inlet 15 formed on the upper surface of the frame part 12, and the remaining part 54 is formed on the end face of the frame part 12. Air is exhausted from the cooling air inlet 15.
In other words, the cooling air inlet 15 can be a cooling air outlet and the cooling air outlet 16 can be a cooling air inlet depending on the flight state of the aircraft.

As described above, the drone 10 according to the present embodiment includes a main body 11, a plurality of frames 12 extending from the main body 11, a propulsion driving unit 20 provided at a tip end of the frame 12, and a propulsion driving unit 20. And an electric component unit for driving the motor. Here, the frame portion 12 is a hollow member having a space inside, and has a plurality of air supply / exhaust ports that communicate the outside and the inside space of the frame portion 12. Further, the electric component unit is disposed inside (in the space) of the frame portion 12 and between at least two air supply / exhaust ports.
Specifically, the frame section 12 has a supply / exhaust port at an end on the body section 11 side and an end on the propulsion drive section 20 side, respectively, and the electric component unit has a supply / exhaust port provided on the body section 11 side. It is arranged between the exhaust port and a supply / exhaust port provided on the propulsion drive unit 20 side.

  Thus, by forming the frame portion 12 to have a hollow structure and forming a plurality of air supply / exhaust ports, an air flow is generated inside the frame portion 12. Then, the wind flowing inside the frame portion 12 acts as a cooling wind for cooling the electric component unit disposed inside the frame portion 12 and between the two air supply / exhaust ports. Thereby, the electric component unit can be forcibly air-cooled, and the temperature rise of the electric component unit can be appropriately suppressed. Therefore, the life of the electric component unit can be extended, and as a result, the life of the drone 10 equipped with the electric component unit can be extended.

Further, the electric component unit arranged inside the frame section 12 can be a speed control unit 35 for controlling the rotation speed of the motor 21. The speed control units 35 are provided corresponding to the plurality of motors 21 in order to individually control the rotation speeds of the plurality of motors 21. The motor 21 is a three-phase brushless DC motor, and the speed control unit 35 includes six switching elements in order to control a current flowing through three phases of the motor 21. Therefore, the speed control unit 35 is expected to generate considerable heat.
Therefore, by arranging the speed control unit 35 inside the frame portion 12 and cooling it by cooling air flowing inside the frame portion 12, the temperature rise of the speed control unit 35 having a large amount of heat generation can be appropriately suppressed. Thus, the life of the drone 10 can be effectively extended.

In addition, by disposing the speed control unit 35 inside the frame portion 12, the speed control unit 35 can be separated from other electric component units disposed on the main body portion 11. Thereby, it is possible to suppress the switching noise of the switching element included in the speed control unit 35 from adversely affecting the operation of another electric component unit.
For example, the controller 32 monitors the current flowing through each phase of the motor 21 to determine whether the motor 21 is operating normally. When the speed control unit 35 is disposed near the controller 32, the controller 32 may erroneously determine the operation of the motor 21 due to the influence of the switching noise. By arranging the speed control unit 35 away from the controller 35, the above-described erroneous determination can be suppressed.

Further, the air supply / exhaust port formed at the end of the frame section 12 on the propulsion drive section 20 side can be formed on the upper surface of the frame section 12 at a position facing the rotating rotor 22. Thereby, the air supply / exhaust port can be a cooling air intake port through which wind generated by rotation of the rotary wings 22 can be easily taken into the inside of the frame portion 12.
The air supply / exhaust port formed at the end of the frame portion 12 on the side of the main body 11 can be formed on the lower surface of the frame portion 12. Thereby, the air supply / exhaust port is a cooling air exhaust port that can appropriately exhaust air taken in from a cooling air intake formed at a position facing the rotor 22 to the outside of the frame portion 12. Can be.
As described above, the drone 10 in the present embodiment can reliably flow the air inside the frame portion 12 and appropriately cool the speed control unit 35 disposed inside the frame portion 12.

In addition, in order to cool the speed control unit 35 more efficiently, a cooling body 36 having excellent thermal conductivity may be attached to the heat radiation surface of the speed control unit 35 as shown in FIG. Note that the cooling body 36 may be attached to the switching element itself serving as a heating element included in the speed control unit 35, or may be attached to a substrate on which the switching element is mounted.
Here, as a material of the cooling body 36, for example, a carbon fiber reinforced carbon composite material can be used. The carbon fiber reinforced carbon composite material is a composite material using carbon fiber as a reinforcing material and carbon as a matrix. The carbon fiber reinforced carbon composite material is produced by molding and curing carbon fiber reinforced plastic (CFRP), and then heat-treating the carbon fiber reinforced plastic (CFRP) in an inert atmosphere to carbonize the base plastic. The carbon fiber reinforced carbon composite material includes C / C composite, carbon-carbon, carbon-carbon composite, and reinforced carbon-carbon (RCC). ) Is sometimes called. In the following description, the carbon fiber reinforced carbon composite material is referred to as “C / C composite”.

Hereinafter, a method of manufacturing the C / C composite used as the cooling body 36 in the present embodiment will be described.
First, a CFRP is manufactured. CFRP is configured by laminating a plurality of prepregs. The prepreg is a sheet-like member in which carbon fibers are impregnated with a resin while keeping the directionality of the fibers. The resin constituting the prepreg is, for example, a thermosetting epoxy resin. In addition, as a resin constituting the prepreg, for example, a thermosetting resin such as an unsaturated polyester, a vinyl ester, a phenol, a cyanate ester, and a polyimide can also be used.

CFRP is formed by laminating a plurality of prepregs (5 to 10 layers) in a mold in a required number of layers, heating to about 120 ° C. to 130 ° C. under reduced pressure, pressurizing (compression bonding), and curing. You. Here, in the present embodiment, a UD material (UNI-DIRECTION material) in which the fiber direction extends in only one direction is used as the prepreg. In this case, a plurality of UD materials are laminated so that the directions of the fibers match, and a CFRP is produced. In addition, as the prepreg, a cloth material that is overlapped so that the directions of the fibers are different can also be used. However, in this case, the fiber orientation is set so as to have anisotropy.
Next, the CFRP is heat-treated at 2500 ° C. to 3000 ° C. for about two weeks to produce a C / C composite.

The C / C composite is a material having a lower density (that is, lighter) and a higher thermal conductivity than metal materials such as copper and aluminum generally used as a cooling body.
For example, the density is about 8.9 g / cm ^{3 for} copper and about 2.7 g / cm ³ for aluminum, while the density of the C / C composite is about 1.7 g / cm ³ . The thermal conductivity of copper is about 400 W / mK and that of aluminum is about 240 W / mK, while that of C / C composite is 700 W / mK.

Conventionally, as a cooling body for cooling a heating element such as a switching element, aluminum or copper, which is a metal having good heat conductivity, has been widely used. However, considering that the cooling body is made of metal, it is disadvantageous to increase the weight of the fuselage in consideration of being mounted on the drone fuselage. In a drone, the payload is an important factor, and in order to make the payload as large as possible, the weight of the drone itself must be as light as possible.
Even if it is known that the cooling efficiency of the speed control unit 35 can be increased by attaching a cooling body to the speed control unit 35 and the life of the speed control unit 35 and, consequently, the drone 10 can be further extended, the cooling efficiency can be improved. If the body significantly increases the weight of the fuselage, it cannot be mounted.

The present inventor has found that a C / C composite is most suitable as a material for a cooling body that solves the above-mentioned problem. As described above, the C / C composite has high thermal conductivity, and thus can sufficiently exhibit the function as a cooling body. In addition, because of its low density (light weight), even if it is attached to the speed control unit 35, the weight of the body does not increase significantly.
The specific heat conductivity [W · cm ³ / mK · g], which is the value obtained by dividing the heat conductivity by the density, is 44.9 for copper, 74 for aluminum, and 411.8 for the C / C composite. Thus, the C / C composite is a material having higher thermal conductivity and lighter weight than copper and aluminum. Therefore, the C / C composite is extremely excellent as a material capable of efficiently cooling the speed control unit 35 while suppressing an increase in the weight of the fuselage.

  Note that CFRP may be selected as a lightweight coolant having a high thermal conductivity. However, when the coolant is used as a coolant for cooling the speed control unit 35 as in the present embodiment, the strength (rigidity) is reduced. It does not matter. It is desired that a material used as a coolant has higher thermal conductivity than high strength. Therefore, the C / C composite is superior to the CFRP as a material capable of efficiently cooling the speed control unit 35 while suppressing an increase in the weight of the fuselage.

As described above, in the drone 10 according to the present embodiment, the cooling body 36 may be attached to the speed control unit 35. Thereby, the speed control unit 35 can be cooled more efficiently.
In addition, by using a carbon fiber reinforced carbon composite material (C / C composite) as the material of the cooling body 36, not only high-efficiency cooling but also minimizing the weight increase of the airframe due to the attachment of the cooling body 36 is achieved. be able to.

  The C / C composite can have anisotropy in thermal conductivity depending on the orientation of the carbon fibers. For example, in the case of a unidirectional C / C composite using a UD material as a prepreg, the thermal conductivity is high in the direction in which the carbon fibers extend (the orientation direction of the carbon fibers). In consideration of this, when the cooling body 36 using the C / C composite is attached to the heat radiation surface of the speed control unit 35, the orientation direction of the carbon fibers of the C / C composite is aligned with the direction in which the cooling air flows. You may make it attach it. Thereby, the speed control unit 35 can be cooled more efficiently.

Further, in the case where the cooling body 36 using the C / C composite is taken into consideration in consideration of the anisotropy of the thermal conductivity of the C / C composite, the longitudinal direction of the cooling body 36 is the orientation of the carbon fibers of the C / C composite. It may be set along the direction. That is, the cooling body 36 may have an elongated shape extending in the direction of high thermal conductivity. Thereby, the cooling efficiency by the cooling body 36 can be improved. Further, even in an elongated space such as the inside of the frame portion 12, the cooling body 36 can be appropriately arranged.
Further, irregularities (fins, blades) may be formed on the surface of the cooling body 36. In this case, the direction in which the irregularities (fins, blades) extend may be formed so as to be along the direction in which the cooling air flows. Also in this case, the speed control unit 35 can be cooled more efficiently.

(Modification)
In the above embodiment, the drone 10 having four rotors 22 has been described, but the number and configuration of the rotors are not particularly limited.
Further, in the above embodiment, the case where the flying object is a drone has been described, but the flying object is not limited to a multicopter as long as it has a rotating wing. Further, the flying object is not limited to the unmanned rotary wing aircraft.
Further, in the above-described embodiment, the case where the speed control unit 35 is disposed inside the frame portion 12 (hollow portion) among the electric component units has been described, but other electric components for driving the propulsion drive unit 20 are described. A structure in which units are arranged to suppress a rise in temperature may be adopted.

  DESCRIPTION OF SYMBOLS 10 ... Flying body (drone), 11 ... Body part, 12 ... Frame part, 15 ... Cooling air inlet (supply / exhaust port), 16 ... Cooling air exhaust port (supply / exhaust port), 20 ... Propulsion drive part, 21 ... Motor, 22 ... rotor, 31 ... receiving unit, 32 ... controller, 33 ... sensor unit, 34 ... battery unit, 35 ... speed control unit, 36 ... cooling body

Claims (7)

A main body part, a plurality of frame parts extending from the main body part, a propulsion drive unit provided at a tip end of the frame part and having a rotor and a motor for rotating the rotor, and a drive unit for driving the propulsion drive unit And an electrical component unit of
The frame portion is a hollow member having a space inside, has a plurality of air supply and exhaust ports that communicate the outside of the frame portion and the space,
The flying object, wherein the electric component unit is disposed in the space of the frame portion and between at least two of the air supply and exhaust ports.   The flying object according to claim 1, wherein the electric component unit includes a speed control unit that controls a rotation speed of the motor. The frame unit,
The flying object according to claim 1, wherein the air supply / exhaust port is provided at each of an end on the propulsion drive unit side and an end on the body unit side.   4. The air supply / exhaust port according to claim 1, wherein the air supply / exhaust port is formed on an upper surface of an end of the frame unit on the propulsion drive unit side, and at a position facing the rotating rotor. A flying object according to claim 1.   The flying object according to claim 4, wherein the air supply / exhaust port is formed on a lower surface of an end portion of the frame portion on the main body portion side.   The flying object according to any one of claims 1 to 5, wherein a cooling body for cooling the electric component unit is attached to the electric component unit.   The said cooling body is comprised by the carbon fiber reinforced carbon composite material, The flying body of Claim 6 characterized by the above-mentioned.

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