Flying body

Abstract

To improve flight stability against disturbance.SOLUTION: A flying body includes: a plurality of arms of which one ends are connected to the body; fitting parts provided to the other ends of respective arms; and propellers fitted to the fitting part and a motor for turning the propellers. The fitting parts are provided with weight objects.SELECTED DRAWING: Figure 1

Description

[Technical field]

[0001] The technology of the present disclosure relates to flying vehicles. [Background technology]

[0002] JP 2021-145586 A discloses a drone comprising an aircraft body, multiple arms extending from the aircraft body, and propellers and motors arranged at the tips of the arms. Summary of the Invention [Problem to be solved by the invention]

[0003] However, in the above drone, the weight of the main body of the aircraft is large compared to the weight of the multiple arms, so the inertial force around the center of gravity of the main body is small, and flight stability against disturbances such as crosswinds on the main body is poor.

[0004] Therefore, the technology disclosed herein aims to provide an aircraft with improved flight stability against external disturbances. [Means for solving the problem]

[0005] In order to achieve the above-mentioned objective, a first aspect of the technology disclosed herein is an aircraft comprising a plurality of arms having one end connected to a main body, an attachment portion provided at the other end of each of the plurality of arms, a propeller attached to the attachment portion, and a motor for rotating the propeller, and the attachment portion is provided with a heavy object.

[0006] In a second aspect of the flying object, the heavy object is at least one of an electric device other than the propeller and the motor, luggage, and a person.

[0007] In a third aspect of the aircraft, the electrical device is a power source for a motor.

[0008] The fourth aspect of the aircraft is equipped with a movement mechanism that moves the heavy object between the mounting portion and the main body, and the flight of the aircraft is switchable between a stability-emphasis mode that emphasizes flight stability and a maneuverability-emphasis mode that emphasizes flight maneuverability, and the movement mechanism moves the heavy object to the mounting portion when the flight of the aircraft is in the stability-emphasis mode, and moves the heavy object to the main body when the flight of the aircraft is in the maneuverability-emphasis mode. Effect of the Invention

[0009] The first to fourth aspects of the technique of the present disclosure can improve flight stability against external disturbances. The fourth aspect of the technology of the present disclosure can improve flight stability in the stability-emphasis mode, and can improve controllability in the controllability-emphasis mode. [Brief description of the drawings]

[0010] [Figure 1] This is an overall oblique view showing the configuration of an unmanned aerial vehicle. [Diagram 2] FIG. 2 is a block diagram of the electrical configuration of the unmanned aerial vehicle. [Diagram 3] A figure showing the state in which the movement mechanism moves the heavy object to the mounting part when the unmanned aerial vehicle is flying in stability-emphasis mode. [Figure 4] This figure shows the state in which the movement mechanism moves a heavy object to the main body when the unmanned aerial vehicle is flying in maneuverability-emphasized mode. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0011] Hereinafter, embodiments of the technology of the present disclosure will be described with reference to the drawings.

[0012] Fig. 1 shows the configuration of an unmanned aerial vehicle 10. As shown in Fig. 1, the unmanned aerial vehicle 10 has a configuration for flying as an aircraft and a configuration for flying as a multicopter with four propellers. Note that the number of propellers is not limited to four, and may be, for example, three, five, six, seven, eight, etc.

[0013] The unmanned aerial vehicle 10 is configured as an aircraft and comprises a pair of fixed wings 14L, 14R arranged on either side of the main body 12, mounting portions 16L1, 16R1 shaped like rectangular prisms arranged at the tip of each of the pair of fixed wings 14L, 14R, aircraft propellers 28L, 28R arranged at the rear ends of rear support columns 16L3, 16R3 arranged on the rear side of the mounting portions 16L1, 16R1 and generating thrust, and aircraft motors 26L, 26R that rotate the aircraft propellers 28L, 28R.

[0014] The unmanned aerial vehicle 10 is configured as a multicopter and includes multicopter propellers 20L, 20R mounted on the lower (or upper) tip of each of the front support columns 16L2, 16R2 mounted in front of the mounting portions 16L1, 16R1, multicopter propellers 24L, 24R mounted on the tips of extension support columns 16L4, 16R4 extending upward (or downward) from the rear of each of the rear support columns 16L3, 16R3 of the mounting portions 16L1, 16R1, and multicopter motors 18L, 18R, 22L, 22R that rotate these multicopter propellers 20L, 20R, 24L, 24R.

[0015] Figure 2 shows the electrical configuration of the unmanned aerial vehicle 10. As shown in Figure 2, the electrical configuration of the unmanned aerial vehicle 10 includes a flight controller FC provided on the main body 12 of the unmanned aerial vehicle 10, and a battery b that supplies power to the flight controller FC.

[0016] The mounting portion 16L1 provided at the tip of the fixed wing 14L provided on the left side of the traveling direction of the unmanned aerial vehicle 10 is provided with a battery 52L that supplies power to the aircraft motor 26L and the multicopter motors 18L and 22L. That is, the battery 52L is provided, i.e., attached, to the mounting portion 16L1. The battery 52L, the multicopter motors 18L and 22L, and the aircraft motor 26L are connected via power lines 54L1, 54L2, and 54L3.

[0017] The mounting portion 16R1 provided at the tip of the fixed wing 14R provided on the right side of the traveling direction of the unmanned aerial vehicle 10 is provided with a battery 52R that supplies power to the aircraft motor 26R and the multicopter motors 18R and 22R. That is, the battery 52R is provided, i.e., attached, to the mounting portion 16R1. The battery 52R, the multicopter motors 18R and 22R, and the aircraft motor 26R are connected via power lines 54R1, 54R2, and 54R3.

[0018] The batteries 52L and 52R are an example of the "heavy object" of the technology of the present disclosure.

[0019] Thus, in this embodiment, the mounting part 16R1 provided at the tip of the fixed wing 14R provided on the right side of the traveling direction of the unmanned aerial vehicle 10 is provided with a battery 52R that supplies power to the aircraft motor 26R and the multicopter motors 18R and 22R. Also, in this embodiment, the mounting part 16L1 provided at the tip of the fixed wing 14L provided on the left side of the traveling direction of the unmanned aerial vehicle 10 is provided with a battery 52L that supplies power to the aircraft motor 26L and the multicopter motors 18L and 22L. Therefore, in this embodiment, the weight of the arm side is made heavier and the weight of the main body 12 side is made lighter than when the batteries 52R and 52L are provided on the main body 12. Therefore, the inertial force around the center of gravity of the main body 12 can be increased. Therefore, in this embodiment, the stability of flight against disturbances such as crosswinds on the aircraft main body can be improved more than when the batteries 52R and 52L are provided on the main body 12.

[0020] In addition, in this embodiment, the weight of the arm side is made heavier and the weight of the body 12 side is made lighter than when the batteries 52R, 52L are provided in the body 12, so the force with which the arm supports the body 12 side can be reduced and the strength of the arm can be weakened. Thus, the weight of the arm can be reduced. Therefore, the total power consumption of the batteries 52R, 52L can be reduced compared to when the batteries 52R, 52L are provided in the body 12.

[0021] In the embodiment described above, the main body 12 of the unmanned aerial vehicle 10 is provided with the battery b that supplies power to the flight controller FC, but the technology of the present disclosure is not limited to this. For example, the battery b may be omitted, and the flight controller FC may be supplied with power from the battery 52L and the battery 52R.

[0022] In this embodiment, the attachment 16R1 provided at the tip of the indefinite wing 14R is provided with a battery 52R that supplies power to the aircraft motor 26R and the multicopter motors 18R and 22R, and the attachment 16L1 provided at the tip of the fixed wing 14L is provided with a battery 52L that supplies power to the aircraft motor 26L and the multicopter motors 18L and 22L. The technology of the present disclosure is not limited to this. For example, the attachments 16R1 and 16L1 may be provided with at least one of electrical equipment (other than batteries) other than the propeller and motor, luggage, and a person. For example, the luggage may be pesticides, and the electrical equipment may be equipment for spraying pesticides. In addition, when a person is provided on the attachments 16R1 and 16L1, the aircraft is manned, and the attachments 16R1 and 16L1 are provided with a holding part such as a chair for holding the person.

[0023] Electric equipment other than propellers and motors (other than batteries), luggage, and people are examples of the "heavy object" of the technology of this disclosure.

[0024] Furthermore, in the present embodiment, the battery 52R is always provided in the mounting portion 16R1, and the battery 52L is always provided in the mounting portion 16L1, but the technology of the present disclosure is not limited to this.

[0025] Figure 3 shows the movement mechanism moving the heavy object to the mounting portion when the unmanned aerial vehicle's flight is in a stability-emphasis mode, and Figure 4 shows the movement mechanism moving the heavy object to the main body when the unmanned aerial vehicle's flight is in a maneuverability-emphasis mode.

[0026] 3 and 4, the unmanned aerial vehicle 10 includes a moving mechanism 60R that moves the battery 52R between the mounting part 16R1 and the main body 12, and a moving mechanism 60L that moves the battery 52L between the mounting part 16L1 and the main body 12. The moving mechanism may be a moving mechanism that employs a rack and pinion system.

[0027] When a control signal is transmitted from the control signal transmitter to set the flight of the unmanned aerial vehicle to a stability-oriented mode, the flight controller FC controls the moving mechanisms 60L, 60R to move the batteries 52L, 52R to the mounting parts 16L1, 16R1, as shown in Fig. 3. By increasing the inertial force around the center of gravity of the main body 12, the flight stability against disturbances such as crosswinds on the main body can be improved.

[0028] When a control signal for putting the flight of the unmanned aerial vehicle into a maneuverability-oriented mode is transmitted from the control signal transmitter, the flight controller FC controls the moving mechanisms 60L, 60R to move the batteries 52L, 52R to the main body 12, as shown in Fig. 4. By reducing the inertial force around the center of gravity of the main body 12, the maneuverability can be improved.

[0029] Alternatively, for example, when turning the unmanned aerial vehicle 10 to the right, the battery 52R may be moved to the mounting part 16R1 side and the battery 52L may be moved to the main body 12 side, and when turning the unmanned aerial vehicle 10 to the left, the battery 52L may be moved to the mounting part 16L1 side and the battery 52R may be moved to the main body 12 side. This can further improve maneuverability.

[0030] In the embodiment described above, the aircraft propellers 28L, 28R are provided at the rear ends of the support columns 16L3, 16R3 provided at the rear ends of the mounting parts 16L1, 16R1 provided at the tips of the pair of fixed wings 14L, 14R. The technology of the present disclosure is not limited to this. For example, one aircraft propeller 28L, 28R may be provided at the tip of the main body 12 of the flying object 10.

[0031] In the above-described embodiment, an unmanned aerial vehicle has been used as an example, but the technology of the present disclosure is not limited to this and may also be used with a manned aerial vehicle.

[0032] In the embodiment described above, the pair of fixed wings 14L, 14R are provided on the left and right sides of the main body 12, and the mounting portions 16L1, 16R1 are provided at the tip of each of the pair of fixed wings 14L, 14R, each of which has a rectangular prism shape. The technology of the present disclosure is not limited to this. A plurality of cylindrical arms that are not fixed wings may be used. [Explanation of symbols]

[0033] 10 Unmanned Aerial Vehicles 28L, 28R, 20L, 24L, 20R, 24R Propeller 26L, 26R, 18L, 22L, 18R, 22R motor 16L1, 16R1 mounting section 16L2, 16R2, 16L3, 16R3 Support column

Claims

1. A plurality of arms each having one end connected to the body; an attachment portion provided at the other end of each of the plurality of arms; a propeller attached to the mounting portion and a motor for rotating the propeller; An aircraft comprising: The mounting portion is provided with a weight object. Flying vehicle.

2. The flying vehicle according to claim 1 , wherein the heavy object is at least one of an electric device other than the propeller and the motor, luggage, and a person.

3. The flying vehicle according to claim 2 , wherein the electrical device is a power source for a motor.

4. a moving mechanism for moving the heavy object between the attachment portion and the main body, The flight of the aircraft can be switched between a stability-oriented mode that emphasizes flight stability and a maneuverability-oriented mode that emphasizes flight maneuverability, The moving mechanism moves the heavy object to the attachment section when the flight of the aircraft is in a stability-emphasized mode, and moves the heavy object to the main body when the flight of the aircraft is in a maneuverability-emphasized mode. The flying object according to any one of claims 1 to 3.

5. The flying object is A configuration for flying as an aircraft; A configuration for flying as a multicopter with multiple propellers; having The flying vehicle according to claim 1.

6. The configuration of the aircraft is as follows: A pair of fixed wings provided on the left and right sides of the main body; The mounting portion is provided at a tip of each of the pair of fixed wings; an aircraft propeller provided at a rear end of a rear support column provided at a rear side of the mounting portion and configured to generate thrust; an aircraft motor that rotates the aircraft propeller; Equipped with As a configuration of the multicopter, A multicopter propeller provided on the lower or upper end of each of the front support columns provided in front of the mounting portions provided at the tips of each of the pair of fixed wings; A multicopter propeller provided at the tip of an extension support column extending upward or downward from the rear of each of the rear support columns of the mounting portion provided at the tip of each of the pair of fixed wings; a multicopter motor that rotates the multicopter propeller; Equipped with The flying vehicle according to claim 5.

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