Aircraft

Abstract

The present invention provides an aircraft that can suppress power consumption and generate a sound that scares birds and animals. The aircraft (1, 1A, 1B, 1C) of the present invention comprises: a rotor (20) that generates an air flow for floating; and a sound generating mechanism (40, 40A, 40B, 40C) having an opening (41, 43, 41A, 41B, 44B, 41C) that generates a sound that scares birds and animals by using the air flow generated by the rotor (20) to make air flow into the opening (41, 43, 41A, 41B, 44B, 41C).

Description

Technical Field

[0001] The present invention relates to an aircraft. Background Art

[0002] Conventionally, there is a known technique for scaring off birds and animals by using an aircraft. As a document describing such a technique, for example, there is Patent Document 1. Patent Document 1 describes a drone that has a speaker mounted on its fuselage and scares off birds and animals by generating sound from the speaker.

[0003] [Background Technology Literature]

[0004] [Patent Document]

[0005] [Patent Document 1] Japanese Patent Application Publication No. 2019-62743 Summary of the invention

[0006] [Problems to be solved by the invention]

[0007] The aircraft of Patent Document 1 must continue to be supplied with electric power at least while the speaker is generating sound. From the viewpoint of suppressing the amount of electric power consumed to generate sound, the prior art has room for improvement.

[0008] The present invention has been made in view of such circumstances, and an object of the present invention is to provide an aircraft that can suppress power consumption and generate a sound that scares off birds and animals.

[0009] [Technical means to solve the problem]

[0010] An aircraft according to one aspect of the present invention comprises: an air flow generating device for generating an air flow for floating; and a sound generating mechanism having an opening and generating sound by causing air to flow into the opening using the air flow.

[0011] [Effects of the Invention]

[0012] According to the present invention, it is possible to provide an aircraft that can suppress power consumption and generate a sound that scares off birds and animals. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a perspective view showing the aircraft according to the first embodiment of the present invention from obliquely below.

[0014] Figure 2 This is a side view of the periphery of the rotor of the aircraft according to the first embodiment of the present invention.

[0015] Figure 3 This is a plan view of the periphery of the rotor of the aircraft according to the first embodiment of the present invention.

[0016] Figure 4This is a bottom view of the periphery of the rotor of the aircraft according to the first embodiment of the present invention.

[0017] Figure 5 It is a cross-sectional view of the periphery of the rotor of the aircraft according to the first embodiment of the present invention.

[0018] Figure 6 This is a block diagram showing an electrical configuration related to the aircraft control device according to the first embodiment of the present invention.

[0019] Figure 7 It is a side view of the periphery of the rotor of the aircraft according to the second embodiment of the present invention.

[0020] Figure 8 It is a plan view of the periphery of the rotor of the aircraft according to the second embodiment of the present invention.

[0021] Fig. 9 It is a bottom view of the periphery of the rotor of the aircraft according to the second embodiment of the present invention.

[0022] Fig.10 It is a cross-sectional view of the periphery of the rotor of the aircraft according to the second embodiment of the present invention.

[0023] Fig.11 It is a side view of the periphery of the rotor of the aircraft according to the third embodiment of the present invention.

[0024] Fig.12 It is a plan view of the periphery of the rotor of the aircraft according to the third embodiment of the present invention.

[0025] Fig.13 It is a bottom view of the periphery of the rotor of the aircraft according to the third embodiment of the present invention.

[0026] Fig.14 It is a cross-sectional view of the periphery of a rotor of an aircraft according to a third embodiment of the present invention.

[0027] Fig.15 This is a side view showing a state in which the sealing mechanism of the aircraft according to the fourth embodiment of the present invention suppresses the generation of sound.

[0028] Fig.16 This is a side view showing a state in which the highest sound is generated by the frequency changing mechanism of the aircraft according to the fourth embodiment of the present invention.

[0029] Fig.17 This is a side view showing a state in which the lowest sound is generated by the frequency changing mechanism of the aircraft according to the fourth embodiment of the present invention.

[0030] Fig.18 This is a block diagram showing an electrical configuration related to an aircraft control device according to a fourth embodiment of the present invention. DETAILED DESCRIPTION

[0031] Hereinafter, non-limiting exemplary embodiments of the present invention will be described with reference to the drawings.

[0032] The aircraft of this embodiment is a drone capable of unmanned flight. In addition, the so-called "capable of unmanned flight" means that the aircraft can be flown without a person on board, and includes not only the case where the aircraft can fly autonomously, but also the case where the aircraft is remotely controlled by a person.

[0033] An aircraft 1 according to a first embodiment of the present invention will be described. Figure 1 This is a perspective view of the aircraft 1 as viewed obliquely from below.

[0034] like Figure 1 As shown, the aircraft 1 comprises: a main body 11; an arm 12 extending from the main body 11; an air flow generating device 19 generating an air flow for making the aircraft 1 fly; a shield 30 protecting the air flow generating device 19; and a sound generating mechanism 40 generating a sound for intimidating birds and animals.

[0035] The main body 11 is located at the center of the aircraft 1 in a plan view. A foot 13 that touches the landing surface is disposed below the main body 11. The main body 11 also includes a control device 100 and a camera 102 that perform various controls on the aircraft 1 as described below.

[0036] The arm portion 12 is a support portion having one end connected to the main body portion 11 and an air flow generating device 19 disposed at the other end (hereinafter referred to as the front end). In the present embodiment, six (plural) arms 12 extend radially (radially) from the main body portion 11 in a plan view. The six arms 12 are spaced at equal intervals in the circumferential direction in a plan view.

[0037] The air flow generating device 19 includes a rotor 20 and a rotor driving unit 21. The rotor driving unit 21 is disposed at the front end of the arm 12 and rotates the rotor 20 with a built-in motor. The air flow generated by the rotation of the rotor 20 generates lift for causing the aircraft 1 to float.

[0038] The shield portion 30 includes a shield extension portion 31 connected to the front end portion of each arm portion 12 , a shield support portion 32 extending upward from the front end of the shield extension portion 31 , and a protection portion 34 supported by the shield support portion 32 .

[0039] The shield extension 31 further extends radially outward in the horizontal direction from the arm portion 12. In addition, the "outside" mentioned here refers to the side away from the main body 11 when the center of gravity or the center of the main body 11 of the aircraft 1 is taken as the starting point when viewed from above, and the starting point can also be set as the center of the sphere to express the radial outside.

[0040] The shroud support portion 32 extends from the front end of the shroud extension portion 31 substantially parallel to the rotation axis of the rotor 20. The shroud support portion 32 and the rotor 20 are in a positional relationship such that the shroud support portion 32 does not contact the rotor 20 even when the rotor 20 rotates. The shroud support portion 32 is provided with a shroud fixing portion 33 for fixing the protection portion 34.

[0041] The protection part 34 is a ring-shaped belt-shaped member that surrounds the main body 11 as a whole when viewed from above. The protection part 34 is flexible and is installed in a manner that connects the six shield support parts 32. That is, when viewed from above, the six (plural) protection parts 34 form a hexagon (polygon), and all of the plurality of rotors 20 are located inside the hexagon. In addition, in the present embodiment, the height of the protection part 34 is set to a position that is substantially the same height as the rotor 20 in the vertical direction, so as to protect the rotor 20 from other flying objects, buildings, etc.

[0042] The sound generating mechanism 40 generates a sound for intimidating an object. The object may be, for example, a bird or a mammal such as a wild boar or a wild boar that may cause damage to crops on a farm or bird strikes at an airport. In the present embodiment, the sound generating mechanism 40 is formed in each of the six arms 12 and the shield extension 31. That is, a total of 12 sound generating mechanisms 40 are arranged in the aircraft 1.

[0043] The structure of the sound generating mechanism 40 will be described. Figure 2 This is an enlarged side view of the periphery of the rotor 20 of the aircraft 1 . Figure 3 is a top view obtained by enlarging the periphery of the rotor 20 of the aircraft 1. Figure 4 is a bottom view obtained by enlarging the periphery of the rotor 20 of the aircraft 1. Figure 5 yes Figure 3 AA line section view. In addition, Figure 2 to Figure 5 In the figure, the shield fixing portion 33 and the protection portion 34 are omitted.

[0044] The sound generating mechanism 40 disposed on the arm 12 side includes an opening 41 and an outflow port 42 formed in the arm 12. The opening 41 and the outflow port 42 are both formed to be located inside the rotation track when viewed in the rotation axis direction of the rotor 20.

[0045] The arm portion 12 of this embodiment is configured as a tube having a hollow portion 14 inside thereof. The opening 41 is an opening communicating with the hollow portion 14 of the arm portion 12. Figure 2 and Figure 3As shown, an opening 41 is formed at one side of each arm 12. In the present embodiment, the opening 41 is formed into a substantially rectangular shape when viewed from the side, but the shape of the opening 41 is not particularly limited and may be circular, elliptical, or a polygon other than a rectangle. Figure 4 and Figure 5 In the example shown, the lower edge and the upper edge of the opening 41 are located at the same position in a plan view, but the present invention is not limited to this configuration. For example, a configuration may be adopted in which the lower edge of the opening 41 is located further outward than the upper edge in a direction perpendicular to the longitudinal direction of the arm 12 in a plan view. In this way, by making the lower edge of the opening 41 protrude more than the upper edge, more air can flow into the opening 41.

[0046] The outflow port 42 is an opening that communicates with the hollow portion 14 of the arm portion 12. Figure 4 As shown, one outlet 42 is formed at the bottom of each arm 12. In this embodiment, the outlet 42 is formed in a substantially rectangular shape when viewed from below, but the shape of the outlet 42 is not particularly limited and may be circular, elliptical, or polygonal other than rectangular.

[0047] The sound generating mechanism 40 disposed on the shroud extension portion 31 side includes an opening 43 and an outflow port 44 formed in the shroud extension portion 31. The opening 43 and the outflow port 44 of the sound generating mechanism 40 are formed to be located inside the rotation track when viewed in the rotation axis direction of the rotor 20.

[0048] The shield extension portion 31 of the present embodiment is configured as a tube having a hollow portion 15 inside thereof. The opening 43 is an opening communicating with the hollow portion 15 of the shield extension portion 31. Figure 2 and Figure 3 As shown, an opening 43 is formed at one side of each shield extension 31. In the present embodiment, the opening 43 is formed into a substantially rectangular shape when viewed from the side, but the shape of the opening 43 is not particularly limited, and may be circular, elliptical, or a polygon other than a rectangle. Figure 4 and Figure 5 In the example shown, the lower edge and the upper edge of the opening 43 are located at the same position in a plan view, but the present invention is not limited to this configuration. For example, a configuration may be adopted in which the lower edge of the opening 43 is located further outward than the upper edge in a direction perpendicular to the longitudinal direction of the hood extension 31 in a plan view. In this way, by making the lower edge of the opening 43 protrude more than the upper edge, more air can flow into the opening 43.

[0049] The outflow port 44 is an opening that communicates with the hollow portion 15 of the shield extension portion 31. Figure 4As shown, one outlet 44 is formed at the bottom of each shield extension 31. In this embodiment, the outlet 44 is formed in a substantially rectangular shape when viewed from above, but the shape of the outlet 44 is not particularly limited and may be circular, elliptical, or polygonal other than rectangular.

[0050] like Figure 5 As shown by arrow F, the air flow generated by the rotation of rotor 20 flows downward from rotor 20. Thus, air is blown toward arm 12 and shroud extension 31 of shroud 30 from above.

[0051] The generation of sound by the sound generating mechanism 40 disposed in the shroud extension 31 will be described. The sound generating mechanism 40 generates sound by deflecting the air flow. Specifically, the air flow generated by the rotation of the rotor 20 is used to blow air toward the opening 43. The air blown toward the opening 43 collides with the edge of the opening 43 and is divided into air flowing toward the hollow portion 15 of the shroud extension 31 and air flowing toward the outside of the shroud extension 31. The air flow near the edge of the opening 43 is disturbed, and the air in the hollow portion 15 resonates, generating sound of a specified frequency corresponding to the shape of the hollow portion 15 of the shroud extension 31. In addition, the air flowing toward the hollow portion 15 of the shroud extension 31 flows out from the outlet 44 to the outside of the shroud extension 31.

[0052] The principle of sound generation of the sound generating mechanism 40 disposed in the arm 12 is the same as that of the shield extension 31. The air blown to the opening 41 collides with the edge of the opening 41 and is divided into air flowing toward the hollow portion 14 of the arm 12 and air flowing toward the outside of the arm 12. The air flow near the edge of the opening 41 is disturbed, and the air in the hollow portion 14 resonates, generating sound of a predetermined frequency corresponding to the shape of the hollow portion 14 of the arm 12. The air flowing toward the hollow portion 14 of the arm 12 flows out of the arm 12 from the outflow port 42.

[0053] As described above, by utilizing the air flow generated when the aircraft 1 is flying, the sound generating mechanism 40 can generate sound without consuming power, thereby making it possible to intimidate birds and animals with the sound. In addition, in the present embodiment, the arm 12 and the sound generating mechanism 40 are integrally formed, and since the arm 12 has the hollow portion 14, the total weight of the aircraft 1 can also be reduced. Similarly, the shield extension 31 and the sound generating mechanism 40 are integrally formed, and since the shield extension 31 has the hollow portion 15, the weight of the shield 30 can also be reduced.

[0054] The shape of the hollow portion 14 of the arm portion 12 is configured to produce a sound of a frequency that the birds and animals to be intimidated avoid. Similarly, the shape of the hollow portion 15 of the shield extension portion 31 is also configured to produce a sound of a frequency that the birds and animals to be intimidated avoid. The sound generating mechanism 40 arranged on the side of the arm portion 12 and the sound generating mechanism 40 arranged on the side of the shield extension portion 31 can generate sounds of the same frequency or sounds of different frequencies. Furthermore, the frequencies of the sounds generated by the sound generating mechanisms 40 of each arm portion 12 can also be configured to be the same or different from each other. Similarly, the frequencies of the sounds generated by the sound generating mechanisms 40 of each shield extension portion 31 can also be configured to be the same or different from each other.

[0055] When the plurality of sound generating mechanisms 40 are configured so that all sounds have the same frequency, the volume of the frequency can be increased. On the other hand, when the plurality of sound generating mechanisms 40 are configured so that sounds of different frequencies are emitted, the intimidating effect on a plurality of birds and beasts of different frequencies to be avoided can be increased. For example, when the frequencies of sounds generated by 12 sound generating mechanisms 40 are different from each other, 12 kinds of intimidating sounds of different frequencies can be generated, thereby effectively intimidating a greater variety of birds and beasts.

[0056] Next, the control device 100 will be described. Figure 6 1 is a block diagram showing an electrical configuration related to the control device 100 of the aircraft 1 .

[0057] The control device 100 includes, for example, a CPU (Central Processing Unit), a memory, etc., and is a computer that executes a control program, and executes various control processes such as the flight of the aircraft 1. The control device 100 is electrically connected to various electronic devices such as a power supply device such as a battery 101, a detection unit such as a camera 102, a communication device 103 for transmitting and receiving signals with an external device such as an operation controller or a GPS (Global Positioning System), a gyro sensor 104, an acceleration sensor 105, and an altitude sensor 106.

[0058] like Figure 6 As shown, the control device 100 includes a flight control unit 110 for controlling the flight of the aircraft 1. The flight control unit 110 includes a part of a program stored in the control device 100.

[0059] The flight control unit 110 controls the flight of the aircraft 1 based on various information from the camera 102, the communication device 103, the gyro sensor 104, the acceleration sensor 105, the altitude sensor 106, etc. The flight control unit 110 adjusts the rotation speed of the rotor 20 and the like by controlling the driving of the rotor drive unit 21. By increasing the rotation speed of the rotor 20 by the flight control unit 110 to generate a stronger air flow, the volume of the sound generated by the sound generating mechanism 40 can be increased.

[0060] Next, an example of flight control performed by the flight control unit 110 of the control device 100 will be described.

[0061] When the camera 102 of the aircraft 1 detects a predetermined object, the control device 100 may perform control so as to start tracking the bird or animal that is the threatening object.

[0062] The control device 100 compares the image acquired by the camera 102 with the identification information of the object stored in the control device 100, and determines whether the object is detected in the image acquired by the camera 102. When the object is detected based on the image acquired by the camera 102, the flight control unit 110 may start tracking until the object leaves the specified area.

[0063] In addition, the control device 100 may control the flight of the aircraft 1 based not only on the camera 102 but also on the information received by the communication device 103 .

[0064] For example, the control device 100 may also control the flight of the aircraft 1 based on information from a ground system that detects an object that has invaded a specified area in a farm or an airport. Specifically, when a detection signal of an object is received from the ground system via the communication device 103, the aircraft 1 may be controlled so that it patrols the monitoring target area of ​​the ground system. Thus, the aircraft 1 patrols only when the ground system detects an object, and thus the power consumption required for the aircraft 1 to monitor and repel birds and animals can be further suppressed. In addition, since the object can be monitored in cooperation with the ground system, the object that has invaded the specified area can be driven away more reliably by the threatening sound generated by the sound generating mechanism 40.

[0065] In addition, the flight control unit 110 of the control device 100 may also control the flight based on information input to an external operating controller.

[0066] Next, refer to Figure 7 to Figure 10 , while describing an aircraft 1A according to a second embodiment of the present invention. Figure 7 1A is a side view showing an enlarged view of the periphery of the rotor 20 of the aircraft 1A. Figure 81A is a plan view showing an enlarged view of the periphery of the rotor 20 of the aircraft 1A. Fig. 9 This is a bottom view obtained by enlarging the periphery of the aircraft 1A. Fig.10 yes Figure 8 BB line cross-sectional view. In addition, the shroud fixing portion 33 and the protection portion 34 are omitted from illustration. In addition, regarding the same configuration as the aircraft 1 of the first embodiment, the same reference numerals are sometimes assigned and the description thereof is omitted.

[0067] The aircraft 1A comprises: a main body 11; an arm 12A extending from the main body 11; an air flow generating device 19 generating an air flow for making the aircraft 1A fly; a shield 30A protecting the air flow generating device 19; and a sound generating mechanism 40A generating a sound for intimidating birds and animals.

[0068] The arm portion 12A of the aircraft 1A and the shroud extension portion 31A of the shroud portion 30A are different from the aircraft 1 of the first embodiment in that the openings 41 , 43 and the outflow ports 42 , 44 are not formed in each of them.

[0069] like Figures 6 to 9 As shown, the sound generating mechanism 40A is mounted on each side of the arm 12A and the shroud extension 31A via a fixing member 53A. Specifically, the sound generating mechanism 40A is arranged on both sides of the circumferential direction when viewed from above across the arm 12A. In addition, the sound generating mechanism 40A is also arranged on both sides of the circumferential direction when viewed from above across the shroud extension 31A. In this embodiment, the sound generating mechanism 40A is mounted on each of the six arms 12A and the shroud extension 31A. That is, a total of 24 sound generating mechanisms 40A are arranged in the aircraft 1A.

[0070] The sound generating mechanism 40A is an annular member having a hollow portion 52A inside thereof for air circulation. The sound generating mechanism 40A has an opening 41A formed on its upper surface and an outlet 42A formed on its lower surface. The opening 41A and the outlet 42A are both substantially circular in plan view and communicate with the hollow portion 52A. Fig.10 As shown, opening 41A and outflow port 42A are formed at overlapping positions in a plan view. In addition, opening 41A and outflow port 42A are formed so as to be located inside the rotation track of rotor 20 in a plan view.

[0071] like Fig.10As shown, in the sound generating mechanism 40A, the air flowing in from the opening 41A is discharged from the outlet 42A through the hollow portion 52A by the air flow generated by the rotation of the rotor 20. The vortex is continuously generated in the hollow portion 52A by the flow of the air, and the sound is generated by the vibration of the air. In the configuration of this embodiment, the air flow generated when the aircraft 1A is flying is also utilized, so that the sound can be generated while suppressing the consumption of electric power.

[0072] In the second embodiment, the opening 41A of the sound generating mechanism 40A is formed below the rotor 20 and at a position facing the rotor 20, so that a large amount of air can flow into the hollow portion 52A from the opening 41A more easily. This makes it easier to increase the volume of the sound generated by the sound generating mechanism 40A.

[0073] Furthermore, in the second embodiment, the sound generating mechanism 40A is attached to the arm portion 12A and the shield extension portion 31A via the fixing member 53A. Therefore, the sound generating mechanism 40A can be easily replaced with a mechanism having a different frequency.

[0074] Furthermore, the plurality of sound generating mechanisms 40 of the aircraft 1A may generate sounds of the same frequency or sounds of mutually different frequencies.

[0075] Next, refer to Figure 11 to Figure 14 , while explaining an aircraft 1B according to a third embodiment of the present invention. Fig.11 This is a side view obtained by enlarging the periphery of the rotor 20 of the aircraft 1B. Fig.12 1 is a top view obtained by enlarging the periphery of the rotor 20 of the aircraft 1B. Fig.13 This is a bottom view obtained by enlarging the periphery of the aircraft 1B. Fig.14 yes Fig.11 In addition, Figure 11 to Figure 14 In the figure, the shield fixing part 33 and the protection part 34 are omitted. In addition, about the structure similar to the aircraft 1 of 1st Embodiment, the same code|symbol is attached|subjected and the description is abbreviate|omitted in some cases.

[0076] The aircraft 1B comprises: a main body 11; an arm 12B extending from the main body 11; an air flow generating device 19 generating an air flow for making the aircraft 1 fly; a shield 30B protecting the air flow generating device 19; and a sound generating mechanism 40B generating a sound for intimidating birds and animals.

[0077] In the present embodiment, the sound generating mechanism 40B is formed in each of the six arms 12B and the shroud extension 31B. That is, a total of 12 sound generating mechanisms 40B are arranged in the aircraft 1B.

[0078] Sound generating mechanism 40B disposed on arm 12B side includes opening 41B and outflow ports 42B, 43B formed in arm 12B. Opening 41B and outflow ports 42B, 43B are formed to be located inside the rotation track when viewed in the rotation axis direction of rotor 20.

[0079] The arm portion 12B of this embodiment is configured as a tube having a hollow portion 14B inside thereof. In addition, the arm portion 12B is configured as a substantially quadrilateral when viewed in longitudinal section. The opening 41B is an opening that communicates with the hollow portion 14B of the arm portion 12B. Fig.12 As shown, one opening 41B is formed on the upper surface of each arm 12B. In this embodiment, the opening 41B is formed in a substantially rectangular shape in a plan view, but the shape of the opening 41B is not particularly limited and may be circular, elliptical, or a polygon other than a rectangle.

[0080] The outflow port 42B is an opening that communicates with the hollow portion 14B of the arm portion 12B. Fig.11 As shown, one outlet 42B is formed on the side surface of each arm 12B. In this embodiment, the outlet 42B is formed in a substantially rectangular shape when viewed from the side, but the shape of the outlet 42B is not particularly limited and may be circular, elliptical, or a polygon other than a rectangle.

[0081] The outflow port 43B is an opening that communicates with the hollow portion 14B of the arm portion 12B. Fig.13 As shown, one outlet 43B is formed on the bottom surface of each arm 12B. In the present embodiment, the outlet 43B is formed in a substantially rectangular shape when viewed from above, but the shape of the outlet 43B is not particularly limited, and may be circular, elliptical, or polygonal other than rectangular. In addition, the opening area of ​​the outlet 43B is formed to be smaller than the opening area of ​​the opening portion 41B.

[0082] Sound generating mechanism 40B disposed on the shroud extension portion 31B side includes opening 44B and outflow ports 45B, 46B formed in shroud extension portion 31B. Opening 44B and outflow ports 45B, 46B of sound generating mechanism 40B are formed to be located inside the rotation track when viewed in the rotation axis direction of rotor 20.

[0083] The shield extension 31B of this embodiment is configured as a tube having a hollow portion 15B inside. In addition, the shield extension 31B is configured as a substantially quadrilateral when viewed in a longitudinal section. The opening 44B is an opening that communicates with the hollow portion 15B of the shield extension 31B. Fig.12As shown, one opening 44B is formed on the upper surface of each shield extension 31B. In this embodiment, the opening 44B is formed in a substantially rectangular shape in a plan view, but the shape of the opening 44B is not particularly limited and may be circular, elliptical, or polygonal other than rectangular.

[0084] The outflow port 45B is an opening that communicates with the hollow portion 15B of the shield extension portion 31B. Fig.11 As shown, one outlet 45B is formed on the side of each shield extension 31B. In this embodiment, the outlet 45B is formed in a substantially rectangular shape when viewed from the side, but the shape of the outlet 45B is not particularly limited and may be circular, elliptical, or polygonal other than rectangular.

[0085] The outflow port 46B is an opening that communicates with the hollow portion 15B of the shield extension portion 31B. Fig.13 As shown, one outlet 46B is formed on the bottom surface of each shield extension 31B. In the present embodiment, the outlet 46B is formed into a substantially rectangular shape when viewed from above, but the shape of the outlet 46B is not particularly limited, and may be circular, elliptical, or polygonal other than rectangular. In addition, the opening area of ​​the outlet 46B is formed to be smaller than the opening area of ​​the opening portion 44B.

[0086] like Fig.14 As shown by arrow F, the air flow generated by the rotation of rotor 20 flows downward from rotor 20. Thus, air is blown from above toward arm 12B and shroud extension 31B of shroud 30B.

[0087] The generation of sound by the sound generating mechanism 40B disposed in the shroud extension 31B is described. Air is blown toward the opening 44B by utilizing the air flow generated by the rotation of the rotor 20. The air blown toward the opening 44B collides with the edge of the opening 44B and flows into the hollow portion 15B in a state where the air flow is turbulent. The air flowing into the hollow portion 15B is divided into the air flowing out from the outlet 45B to the outside and the air flowing out from the outlet 46B to the outside in the hollow portion 15B. The air in the hollow portion 15B resonates due to the flow of this air, and a sound of a specified frequency corresponding to the shape of the hollow portion 15B of the shroud extension 31B is generated.

[0088] The principle of sound generation of the sound generating mechanism 40B disposed in the arm portion 12B is the same as that of the shroud extension portion 31B. Air is blown toward the opening portion 41B by utilizing the air flow generated by the rotation of the rotor 20. The air blown toward the opening portion 41B collides with the edge of the opening portion 41B and flows into the hollow portion 14B in a state where the air flow is turbulent. The air flowing into the hollow portion 14B is divided into air flowing out from the outlet 42B to the outside and air flowing out from the outlet 43B to the outside in the hollow portion 14B. The air in the hollow portion 14B resonates due to the flow of this air, and a sound of a specified frequency corresponding to the shape of the hollow portion 14B of the shroud extension portion 31B is generated. In the configuration of this embodiment, the air flow generated when the aircraft 1B is flying is also utilized, so that the sound can be generated while suppressing the power consumption.

[0089] In addition, in the present embodiment, the arm portion 12B and the sound generating mechanism 40B are integrally formed, and since the arm portion 12B has the hollow portion 14B, the total weight of the aircraft 1B can also be reduced. Similarly, the shroud extension portion 31B and the sound generating mechanism 40B are integrally formed, and since the shroud extension portion 31B has the hollow portion 15B, the weight of the shroud portion 30B can also be reduced.

[0090] In addition, in the present embodiment, the openings 41B and 44B of the sound generating mechanism 40B are formed below the rotor 20 and at a position facing the rotor 20, so that a large amount of air can flow into the hollow portions 14B and 15B from the openings 41B and 44B more easily. Thus, the volume of the sound generated by the sound generating mechanism 40B can be increased more easily.

[0091] Furthermore, the plurality of sound generating mechanisms 40B of the aircraft 1B may generate sounds of the same frequency or sounds of mutually different frequencies.

[0092] Next, refer to Figures 15 to 17 , while explaining the aircraft 1C according to the fourth embodiment of the present invention. Fig.15 1C is a side view showing a state where the frequency changing mechanism 60C which also serves as a sealing mechanism of the aircraft 1C suppresses the generation of sound. Fig.16 1C is a side view showing a state where a high sound is generated by the frequency changing mechanism 60C of the aircraft 1C. Fig.17 It is a side view showing a state where a low sound is generated by the frequency changing mechanism 60C of the aircraft 1C. In addition, about the same structure as the aircraft 1 of the first embodiment, the same code|symbol may be attached|subjected and the description is abbreviate|omitted.

[0093] The aircraft 1C comprises: a main body 11; an arm 12C extending from the main body 11; an air flow generating device 19 for generating an air flow for making the aircraft 1 fly; a shield portion 30C for protecting the air flow generating device 19; a sound generating mechanism 40C for generating a sound for intimidating birds and animals, etc.; and a frequency changing mechanism 60C for changing the frequency of the sound generating mechanism 40C.

[0094] The arm portion 12C is tubular, and is a support portion of which one end is connected to the main body portion 11 and the air flow generating device 19 is arranged at the front end. An opening portion 41C is formed at the upper portion of the arm portion 12C. In the present embodiment, six (plural) arms 12C extend radially (radially) from the main body portion 11 in a plan view. The intervals between the six arms 12C in the circumferential direction in a plan view are equal.

[0095] The shield extension portion 31C further extends in the horizontal direction from the arm portion 12C toward the radially outer side and is formed in a tubular shape. The internal spaces of the arm portion 12C and the shield extension portion 31C are connected to each other. A slit portion 311C extending in the horizontal direction and formed in a substantially elliptical shape is formed on the side of the shield extension portion 31C. The slit portion 311C is an opening that is connected to the internal space of the shield extension portion 31C.

[0096] like Fig.16 As shown, a partition member 61C, an actuator 62C, a shaft 63C, and a cylinder 64C are arranged inside the arm 12C and the shield extension 31C.

[0097] The partition member 61C is a cylindrical member with both ends closed, and its central axis is arranged parallel to the axial direction of the arm portion 12C. The partition member 61C is arranged in a manner that its outer peripheral surface contacts the inner peripheral surface of the arm portion 12C. The partition member 61C is arranged closer to the main body 11 side than the opening portion 41C in the axial direction of the arm portion 12C. The partition member 61C blocks the communication between the space on the main body 11 side inside the arm portion 12C and the space on the shield extension portion 31C side.

[0098] The actuator 62C is a driving device that is disposed between the main body 11 and the partition member 61C and slides the cylinder 64C. The actuator 62C and the cylinder 64C are connected via a rod-shaped shaft 63C.

[0099] The cylinder 64C is a cylindrical member, and its central axis is arranged parallel to the axial direction of the arm portion 12C and the shield extension portion 31C. The cylinder 64C is arranged to be able to slide and move in the axial direction. The end of the cylinder 64C on the shield extension portion side is closed. The cylinder 64C is arranged in a manner that its outer peripheral surface contacts the inner peripheral surface of the arm portion 12C and the shield extension portion 31C. In the internal space of the arm portion 12C and the shield extension portion 31C, the space between the end of the partition member 61C on the shield extension portion 31C side and the closed end of the cylinder 64C is set as a hollow portion 14C.

[0100] Next, refer to Fig.16 , while explaining the structure of the sound generating mechanism 40C. The sound generating mechanism 40C includes an opening 41C formed in the arm 12C and an outlet 42C formed in the cylinder 64C. In this embodiment, the sound generating mechanism 40C is formed in each of the six arms 12C and the cylinder 64C. That is, a total of six sound generating mechanisms 40 are arranged in the aircraft 1C.

[0101] Opening 41C is an opening that communicates with hollow portion 14C. Opening 41C is formed so as to be located inside the rotation track of rotor 20 in a plan view. Fig.16 As shown, one opening 41C is formed at the upper portion of each arm 12C. In this embodiment, the opening 41C is formed in a substantially rectangular shape in a plan view, but the shape of the opening 41C is not particularly limited and may be circular, elliptical, or polygonal other than rectangular.

[0102] The outflow port 42C is an opening that communicates with the hollow portion 14C on the side of the shield extension portion 31C. Fig.16 As shown, the outflow port 42C is formed at one location on the outer peripheral surface of each cylinder 64C. Specifically, the outflow port 42C is formed on the side of the slit portion 311C of the shield extension portion 31C on both sides of the cylinder 64C and is formed at the same position as the slit portion 311C in the vertical direction. Fig.16 In the case of the position shown, the outlet 42C overlaps with the slit portion 311C in a side view, and the hollow portion 14C communicates with the outside through the outlet 42C. In this embodiment, the outlet 42C is formed in a substantially circular shape in a side view, but the shape of the outlet 42C is not particularly limited and may be an ellipse or a polygon.

[0103] like Fig.16 As shown by arrow F, the air flow generated by the rotation of rotor 20 flows downward from the rotor. Thus, the air is blown from the upper side to arm 12C.

[0104] The generation of sound by the sound generating mechanism 40C will be described. Air is blown toward the opening 41C using the air flow generated by the rotation of the rotor 20. The air blown toward the opening 41C collides with the edge of the opening 41C, flows through the hollow portion 14C while vibrating, and flows out from the outflow port 42C, thereby generating sound of a predetermined frequency corresponding to the shape of the hollow portion 14C.

[0105] Next, refer to Figures 15 to 17 , the frequency changing mechanism 60C will be described. The frequency changing mechanism 60C includes a partition member 61C, an actuator 62C, a shaft 63C, and a cylinder 64C.

[0106] The frequency changing mechanism 60C changes the frequency of the sound by changing the shape of the hollow portion 14C. Fig.16 As shown, when the outlet 42C is located at the end of the slit portion 311C on the main body 11 side, the distance L between the end of the partition member 61C on the shield support portion 32 side and the outlet 42C is the shortest. In this case, the sound generating mechanism 40C generates the highest frequency sound.

[0107] When the actuator 62C is driven, the cylinder 64C slides and moves, and the position of the outflow port 42C in the extension direction of the hood extension portion 31C changes. Fig.16 The state causes cylinder 64C to move as Fig.17 As shown, if the outlet 42C is located at the end of the slit portion 311C on the side of the shield support portion 32, the interval L becomes longer, and a sound with a lower frequency is generated by the sound generating mechanism 40C. That is, according to the frequency changing mechanism 60C, by changing the position of the outlet 42C relative to the slit portion 311C and changing the interval L, the frequency of the sound generated by the sound generating mechanism 40C can be changed.

[0108] In addition, the frequency changing mechanism 60C also functions as a closing mechanism capable of closing the outflow port 42C. Fig.16 , 17 As shown in FIG. 1 , when the outlet 42C overlaps the slit portion 311C in a side view, the hollow portion 14C communicates with the outside through the outlet 42C. Fig.15 As shown in FIG. 1 , if the actuator 62C is driven to move the cylinder 64C to a position where the outflow port 42C does not overlap the slit portion 311C, the outflow port 42C is sealed by the inner peripheral surface of the shield extension portion 31C. By sealing the outflow port 42C, the inflow of air from the opening portion 41C into the hollow portion 14C is suppressed, thereby suppressing the generation of sound. Thus, it is possible to switch between a state in which the sound generating mechanism 40C generates sound and a state in which the generation of sound is suppressed, so that a threatening sound to birds and animals can be generated at a desired timing, thereby suppressing the generation of noise.

[0109] Next, the control device 100C will be described. Fig.18 It is a block diagram showing the electrical configuration related to the control device 100C of the aircraft 1C.

[0110] like Fig.18 As shown, the control device 100C is different from the control device 100 of the first embodiment in that it includes a generated sound adjustment unit 120 in addition to the flight control unit 110 for controlling the flight of the aircraft 1C.

[0111] The generated sound adjustment unit 120 controls the driving of the actuator 62C of the frequency change mechanism 60C based on various information from the camera 102, the communication device 103, the height sensor 106, etc. By driving the actuator 62C to change the interval L in the hollow portion 14C, the frequency of the sound generated from the sound generating mechanism 40C can be changed. In addition, the generated sound adjustment unit 120C can also suppress the generation of sound by the frequency change mechanism 60C which also serves as a closing mechanism by driving the actuator 62C to close the outlet 42C.

[0112] Next, an example of control of the frequency of sound etc. by the generated sound adjustment unit 120C of the control device 100C will be described. The flight control unit 110 of the control device 100C may also perform flight control similar to the flight control unit 110 of the control device 100 of the first embodiment.

[0113] When the camera 102 of the aircraft 1C detects a predetermined object, the sound generation adjustment unit 120C of the control device 100C may also use the frequency change mechanism 60C to change the frequency of the sound to a frequency that has an evasive effect on the object. Specifically, the sound generation adjustment unit 120C may also call the information of the frequency set for the object recorded in the control device 100C, and drive the actuator 62C of the frequency change mechanism 60C to change to the frequency. The sound of the frequency set for the object is a sound of a frequency that has an evasive effect on the object. In this way, a sound of a frequency that has an evasive effect on the object can be generated, so that the object can be repelled more reliably.

[0114] In addition, when the camera 102 of the aircraft 1C detects a predetermined object, the sound generation adjustment unit 120C of the control device 100C may also control the generation of sound by the sound generation mechanism 40C. Specifically, when it is determined that the camera 102 detects the object stored in the control device 100C, the sound generation adjustment unit 120 may drive the actuator 62C to open the outflow port 42C closed by the inner peripheral surface of the hood extension 31C to generate sound. In addition, when the interval between the detected object and the aircraft 1C is longer than the predetermined distance, the sound generation adjustment unit 120 may drive the actuator 62C to move the cylinder 64C to the position where the outflow port 42C is closed by the inner peripheral surface of the hood extension 31C. That is, the outflow port 42C is closed to prevent the air from flowing in from the opening 41C, thereby suppressing the generation of sound. Furthermore, when the interval between the detected object and the aircraft 1C is shorter than the predetermined distance, the closed outflow port 42C may be opened to generate sound. Thus, the sound generating mechanism 40C generates a sound only when an object approaches within a predetermined distance, thereby minimizing the generation of noise and preventing birds and animals from coming into contact with the aircraft 1C.

[0115] In addition, the sound generation adjustment unit 120 may also control the generation of sound by the sound generation mechanism 40C based on the flight altitude of the aircraft 1 obtained through the communication device 103 or the altitude sensor 106 that receives the position information from the GPS or the like. Specifically, when the flight altitude is lower than a predetermined altitude, the sound generation adjustment unit 120 may seal the outflow port 42C to suppress the sound generation mechanism 40C from generating sound, and when the flight altitude is higher than the predetermined altitude, the sound generation adjustment unit 120 may open the sealed outflow port 42C. Thus, it is possible to suppress the generation of sound when the aircraft 1 is flying near the ground, thereby preventing noise to the living space of residents and repelling birds and beasts.

[0116] Furthermore, the generated sound adjustment unit 120 of the control device 100C may control the frequency of the sound or the generation of the sound based not only on the camera 102 but also on the information received by the communication device 103 .

[0117] For example, the control device 100C may control the generation of sound based on information from a ground system that detects a monitoring object that has intruded into a predetermined area such as a farm or an airport. Specifically, the generated sound adjustment unit 120 may drive the actuator 62C to open the closed outlet 42C only when the aircraft 1C receives sound generation start information from the ground system while being located in the monitoring target area of ​​the ground system. In this way, the generation of noise can be suppressed and birds and animals can be prevented from contacting the aircraft 1C.

[0118] Furthermore, the generated sound adjustment unit 120 of the control device 100C may control the frequency of the sound or the generation of the sound based on information input to the external operating controller.

[0119] As is clear from the above description, each embodiment of the present invention exhibits advantageous effects through the following configurations.

[0120] The flying machine (1, 1A, 1B, 1C) of the embodiment of the present invention comprises: an air flow generating device (19) generating an air flow for floating; and a sound generating mechanism (40, 40A, 40B, 40C) having an opening (41, 43, 41A, 41B, 44B, 41C) and generating sound by causing air to flow into the opening (41, 43, 41A, 41B, 44B, 41C) under the action of the air flow. Thus, the sound is generated by utilizing the air flow generated when the flying machine (1, 1A, 1B, 1C) flies, so that power consumption can be suppressed and birds and animals can be frightened by utilizing the generated sound.

[0121] In the aircraft (1, 1A, 1B, 1C) according to the embodiment of the present invention, a plurality of rotors (20) are arranged, a plurality of sound generating mechanisms (40, 40A, 40B, 40C) are arranged, and the sound generating mechanisms (40, 40A, 40B, 40C) are arranged at positions corresponding to the rotors (20). Thus, sounds can be generated from the plurality of sound generating mechanisms (40, 40A, 40B, 40C), thereby increasing the volume of the threatening sound to birds and animals.

[0122] In the aircraft (1, 1A, 1B, 1C) of the embodiment of the present invention, at least two sound generating mechanisms (40, 40A, 40B, 40C) generate sounds of different frequencies. Thus, it is possible to generate sounds of two or more frequencies having an evasive effect, thereby increasing the intimidating effect on a plurality of birds and beasts having different frequencies to be evaded.

[0123] The aircraft (1C) of the embodiment of the present invention further comprises a frequency changing mechanism (60C) for changing the frequency of the sound generated by the sound generating mechanism (40C). Thus, the frequency of the generated sound can be changed to a frequency that has an evasive effect on the bird or beast to be intimidated, thereby more effectively repelling the bird or beast.

[0124] In the aircraft (1, 1A, 1B, 1C) according to the embodiment of the present invention, the sound generating mechanism (40, 40A, 40B, 40C) further includes an outflow port (42, 44, 42A, 42B, 43B, 45B, 46B, 42C) through which the air flowing in from the opening (41, 43, 41A, 41B, 44B, 41C) flows out. Thus, the frequency of the sound generated from the sound generating mechanism (40, 40A, 40B, 40C) changes by adjusting the interval between the opening (41, 43, 41A, 41B, 44B, 41C) and the outflow port (42, 44, 42A, 42B, 43B, 45B, 46B, 42C), so that the frequency of the sound can be easily adjusted.

[0125] The aircraft (1C) according to an embodiment of the present invention further comprises a sealing mechanism (60C) capable of sealing at least one of the opening (41C) or the outflow port (42C). Thus, the opening (41C) or the outflow port (42C) is sealed, thereby suppressing the generation of sound from the sound generating mechanism (40C).

[0126] The aircraft (1C) according to an embodiment of the present invention closes at least one of the opening (41C) or the outflow port (42C) by means of a closing mechanism (60C) when the flying altitude is lower than a predetermined altitude. This can suppress the sound generated by the aircraft (1C) when flying near the ground, thereby preventing noise from entering the living space of residents and repelling birds and animals.

[0127] The aircraft (1C) of the embodiment of the present invention further comprises a camera (102) for detecting a predetermined object, and the sealing mechanism (60C) is controlled based on the predetermined object detected by the camera (102) to control the sound generation of the sound generation mechanism (40C). Thus, the sound generation mechanism (40C) can generate sound only when a bird or animal that is a surveillance target is detected.

[0128] The aircraft (1C) of the embodiment of the present invention closes at least one of the opening (41C) or the outflow (42C) by means of a closing mechanism (60C) when the distance between the object detected by the camera (102) and the aircraft (1C) is longer than a predetermined distance, and opens the closed opening (41C) and outflow (42C) when the distance is shorter than the predetermined distance. Thus, the sound generating mechanism (40C) generates a sound only when a bird or animal to be monitored approaches, thereby minimizing the generation of noise and preventing the bird or animal from contacting the aircraft (1C).

[0129] The aircraft (1C) of the embodiment of the present invention further comprises a camera (102) for detecting a predetermined object, and controls a frequency changing mechanism (60C) based on the predetermined object detected by the camera (102) to generate a sound of a frequency set for the predetermined object. Thus, the frequency can be changed to a frequency that has an evasive effect on the bird or beast detected by the camera (102), thereby more effectively repelling the bird or beast.

[0130] In the aircraft (1, 1A, 1B, 1C) of the embodiment of the present invention, the air flow generating device (19) has a rotor (20), and the air flow is generated by rotating the rotor (20), thereby generating a threatening sound to birds and animals with a simpler structure.

[0131] The aircraft (1, 1B, 1C) of an embodiment of the present invention further comprises: a main body (11); a plurality of arms (12, 12B, 12C) extending from the main body (11) and supporting an air flow generating device (19); and an extension (31, 31B, 31C) extending from a front end of the arm (12, 12B, 12C) in a direction away from the main body (11) when viewed from above; and a sound generating mechanism (40, 40B, 40C) formed in at least one of the arm (12, 12B, 12C) or the extension (31, 31B, 31C). Thus, the opening portion (41, 43, 41B, 44B, 41C) of the sound generating mechanism (40, 40B, 40C) is formed on the arm portion (12, 12B, 12C) or the extension portion (31, 31B, 31C), thereby reducing the total weight of the aircraft (1, 1B, 1C), thereby further reducing the power consumption when intimidating birds and beasts.

[0132] As mentioned above, although embodiment of this invention was described, this invention is not limited to this embodiment, and the change, improvement, etc. which can achieve the objective of this invention are included in this invention.

[0133] In the first, second and third embodiments, all the sound generating mechanisms 40, 40A and 40B may generate sounds of different frequencies, or at least two of the sound generating mechanisms 40, 40A and 40B may generate sounds of different frequencies. There is no particular limitation on the number of sound generating mechanisms 40, 40A and 40B that generate different frequencies.

[0134] In the fourth embodiment, the sound adjustment unit 120C controls the frequency changing mechanism 60C to change the frequency of the sound, but before flying the aircraft 1C, the frequency changing mechanism 60C may be operated to change the frequency of the sound generated by the sound generating mechanism 40C to a frequency that has an evasive effect on a specific object.

[0135] The sound generating mechanism 40, 40A, 40B, 40C of the above-described embodiment generates sound through the openings 41, 43, 41A, 41B, 44B, 41C and the outflow ports 42, 44, 42A, 42B, 43B, 45B, 46B, 42C, but may also be configured such that the outflow ports 42, 44, 42A, 42B, 43B, 45B, 46B, 42C are not provided and sound is generated by air flowing into the openings 41, 43, 41A, 41B, 44B, 41C.

[0136] In the fourth embodiment, the sound generation is suppressed by sealing the outflow port 42C, but the sound generation may be suppressed by sealing the opening 41C, or by sealing both the opening 41C and the outflow port 42C.

[0137] In the aircraft 1 and 1B of the first and third embodiments, the openings 41, 43, 41B, 44B and the outflow ports 42, 44, 42B, 43B, 45B, 46B are formed in both the arm portions 12 and 12B and the shroud extension portions 31 and 31B, but the openings 41, 43, 41B, 44B and the outflow ports 42, 44, 42B, 43B, 45B, 46B may be formed only in the arm portions 12 and 12B or only in the shroud extension portions 31 and 31B.

[0138] In the aircraft 1A of the second embodiment, the opening 41A and the outflow port 42A are mounted on both the arm 12A and the shroud extension 31A. However, the opening 41A and the outflow port 42A may be mounted only on the arm 12A or only on the shroud extension 31A.

[0139] In addition, in each embodiment, an unmanned aerial vehicle is described as an example of an aircraft, but the invention is not limited to an unmanned aerial vehicle. For example, the invention can also be applied to an aircraft that transfers a person to a destination without a pilot.

[0140] [Explanation of Symbols]

[0141] 1.1A, 1B, 1C Aircraft

[0142] 19 Air flow generating device

[0143] 40, 40A, 40B, 40C Sound generating mechanism

[0144] 41, 43, 41A, 41B, 44B, 41C opening

Claims

1. An aircraft having: An air flow generating device for generating an air flow for floating; a sound generating mechanism having an opening formed below the air flow generating device and an outlet for the air flowing in from the opening to flow out, and generating sound by causing the air to flow into the opening using the air flow; a sealing mechanism capable of sealing at least one of the opening or the outflow port; and a frequency changing mechanism for changing the frequency of the sound generated by the sound generating mechanism; and The sound generating mechanism has a hollow portion, the hollow portion is communicated with the opening portion, and a vortex is generated by the air flow flowing in from the opening portion; The frequency changing mechanism changes the frequency of the sound by changing the shape of the hollow portion; When the flight altitude is lower than a predetermined altitude, at least one of the opening or the outflow port is closed by the closing mechanism.

2. The aircraft according to claim 1, wherein The air flow generating device is provided in plurality; and The sound generating mechanism is disposed in plurality, and is disposed at a position corresponding to the air flow generating device.

3. The aircraft according to claim 2, wherein At least two of the sound generating mechanisms generate sounds having frequencies different from each other.

4. The aircraft according to claim 1, further comprising a detection unit for detecting a predetermined object. The sealing mechanism is controlled based on the predetermined object detected by the detection unit to control the generation of sound by the sound generating mechanism.

5. The aircraft according to claim 4, wherein when the interval between the object detected by the detection unit and the aircraft is longer than a specified distance, at least one of the opening or the outflow port is closed by the closing mechanism, and when the interval is shorter than the specified distance, the closed opening and the outflow port are opened.

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