Aircraft and method for manufacturing aircraft

Abstract

Provided is an aircraft comprising a body, a support body which passes through the body, motors, and propellers respectively rotated by the motors, each of the motors and propellers being provided respectively at each of the plurality of end portions of the support body, wherein the body is integrally formed or the body and the support body as a whole are integrally formed. Provided is a method for manufacturing an aircraft, the method comprising a step of manufacturing a body and a support body and a step of arranging a motor and a propeller rotated by the motor at each of the plurality of end portions of the support body. The body is integrally manufactured by a three-dimensional (3D) printer or the body and the support body as a whole are integrally manufactured by a three-dimensional (3D) printer. This aircraft less likely comes apart than a conventional aircraft.

Description

Aircraft and aircraft manufacturing method

[0001] The disclosed technology relates to aircraft and methods of manufacturing aircraft.

[0002] The drone body disclosed in Publication No. 2019 / 107009 is manufactured by placing a flight controller and other components between an upper plate and a lower plate, inserting the other end of each of a plurality of arms that support rotors at one end, and then connecting the upper plate and the lower plate.

[0003] However, with the conventional drones described above, there is a risk that the drone may come apart if the upper and lower plates come off or the arms come off.

[0004] The disclosed technology aims to provide an aircraft and a method for manufacturing an aircraft that is less likely to be disassembled than conventional techniques.

[0005] In order to achieve the above-mentioned object, the first aspect of the technology disclosed herein is an aircraft comprising a main body, a support having a plurality of ends and penetrating the main body, a motor disposed at each of the plurality of ends of the support, and a propeller rotated by the motor, wherein the main body is integrally formed, or the main body and the support are integrally formed as a whole.

[0006] The aircraft of the second aspect comprises a main body constructed as an integral unit, a plurality of support parts each having one end and the other end, the one end being inserted into the main body, a motor disposed at the other end of each of the plurality of support parts, and a propeller rotated by the motor.

[0007] A third aspect of the method for manufacturing an aircraft includes the steps of manufacturing a main body and a support body having a plurality of ends and penetrating the main body, and arranging a motor and a propeller rotated by the motor at each of the plurality of ends of the support body, wherein the main body is manufactured as a single unit using a three-dimensional (3D) printer, or the main body and the support body as a whole are manufactured as a single unit using a three-dimensional (3D) printer.

[0008] A fourth aspect of the aircraft manufacturing method includes the steps of integrally manufacturing a main body using a three-dimensional (3D) printer, inserting one end of each of a plurality of support parts, each having one end and the other end, into the main body, and arranging a motor and a propeller rotated by the motor at the other end of each of the plurality of support parts.

[0009] An aircraft of a fifth aspect includes a body including a first member and a second member, a support having a plurality of ends and penetrating between the first member and the second member, a motor disposed at each of the plurality of ends of the support, and a propeller rotated by the motor.

[0010] A sixth aspect of the aircraft manufacturing method includes the steps of manufacturing a first member and a second member using a three-dimensional (3D) printer, penetrating a support having both ends between the first member and the second member, connecting the first member and the second member with the support penetrated, and arranging a motor and a propeller rotated by the motor at each of the both ends of the support.

[0011] The techniques of the present disclosure may make aircraft less susceptible to disassembly than prior art.

[0012] FIG. 1 is an overall oblique view of an aircraft 10A according to a first embodiment; FIG. 2 is a partial oblique view of the upper part of an aircraft 10B according to a second embodiment; FIG. 3 is a partial oblique view of the upper part of an aircraft 10C according to a third embodiment; FIG. 4 is a partial oblique view of the upper part of an aircraft 10D according to a fourth embodiment; FIG. 5 is an overall oblique view of an aircraft 10E according to a fifth embodiment; FIG. 6 is an overall oblique view of an aircraft 10F according to a sixth embodiment; FIG. 7 is a partial oblique view of the upper part of an aircraft 10G according to a seventh embodiment; FIG. 8 is a partial oblique view of the upper part of an aircraft 10H according to an eighth embodiment; and FIG. 9 is a partial oblique view of the upper part of an aircraft 10I according to a ninth embodiment.

[0013] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0023] The following describes embodiments of the present disclosure with reference to the accompanying drawings. (First Embodiment) First, the configuration of an aircraft 10A according to a first embodiment will be described. Fig. 1 shows an overall perspective view of the aircraft 10A.

[0014] 1, the aircraft 10A includes a main body 12A that is integrally formed. The main body 12A is a generally rectangular parallelepiped having a top surface, a bottom surface, and four side surfaces. The main body 12A may also be generally spherical, dome-shaped, or the like.

[0015] The aircraft 10A includes a support body having multiple ends and penetrating the main body 12A. The support body includes a first arm 14, a second arm 16, a first holding portion 18, a second holding portion 20, a first support arm 22, and a second support arm 24, which will be described in detail below. In particular, the first arm 14 and the second arm 16 penetrate the main body 12A.

[0016] The aircraft 10A includes a first arm 14 and a second arm 16, each having opposite ends and penetrating the main body 12A via two opposing sides (the left and right sides in FIG. 1 ) of the four sides of the main body 12A. The first arm 14 and the second arm 16 are of approximately the same length and are disposed approximately parallel to each other.

[0017] 1, the aircraft 10A has two arms, a first arm 14 and a second arm 16, but the technology of the present disclosure is not limited to this. For example, the aircraft 10A may have one arm having both ends, or may have more than two arms, each having both ends.

[0018] The first arm 14 and the second arm 16 are an example of the "first arm portion" of the technology of the present disclosure.

[0019] The aircraft 10A includes a first holding portion 18, for example, inserted, located at one end (the right end in FIG. 1 ) of each of the first arm 14 and the second arm 16, and a second holding portion 20, for example, inserted, located at the other end (the left end in FIG. 1 ) of each of the first arm 14 and the second arm 16. Each of the first holding portion 18 and the second holding portion 20 is a substantially rectangular parallelepiped having a top surface, a bottom surface, and four side surfaces. The end of the first arm 14 is inserted into the side of the first holding portion 18 that faces the main body 12A (the left side in FIG. 1 ), and the end of the first arm 14 is inserted into the side of the second holding portion 20 that faces the main body 12A (the right side in FIG. 1 ), among the four side surfaces.

[0020] Here, the end portion refers to a portion that includes the end and is located within a predetermined range from the end. For example, the end portion of the first arm 14 is a portion that includes the tip of the arm 14 and is located within a processing distance from the tip toward the center.

[0021] The aircraft 10A is provided with a first support arm 22 that penetrates the first holding portion 18 through two opposing side surfaces (the rear and front sides in FIG. 1 ) of the four side surfaces of the first holding portion 18. The aircraft 10A is provided with a second support arm 24 that penetrates the second holding portion 20 through two opposing side surfaces (the rear and front sides in FIG. 1 ) of the four side surfaces of the second holding portion 20. The first support arm 22 and the second support arm 24 have approximately the same length and are arranged approximately parallel to each other.

[0022] The first support arm 22 may be divided into two, and each divided arm may be inserted into the first holding portion 18. Similarly, the second holding portion 20 may be divided into two, and each divided arm may be inserted into the second support arm 24.

[0023] Each of the first support arm 22 and the second support arm 24 is an example of the "second arm portion" of the technology of the present disclosure.

[0024] Each of the first arm 14, the second arm 16, the first support arm 22, and the second support arm 24 is a cylinder (i.e., a hollow pipe), and the central axes of each are located on approximately the same plane. Note that each of the first arm 14, the second arm 16, the first support arm 22, and the second support arm 24 may also be a rectangular pillar, a flat plate, or the like.

[0025] The aircraft 10A includes a first motor 30N1 into which one end of the first support arm 22 is inserted, a second motor 30N2 into which the other end of the first support arm 22 is inserted, a third motor 30N3 into which one end of the second support arm 24 is inserted, and a fourth motor 30N4 into which the other end of the second support arm 24 is inserted. The aircraft 10A includes a first propeller 32N1 rotated by the first motor 30N1, a second propeller 32N2 rotated by the second motor 30N2, a third propeller 32N3 rotated by the third motor 30N3, and a fourth propeller 32N4 rotated by the fourth motor 30N4.

[0026] The aircraft 10A includes a first support column 42 having one end inserted into the bottom surface of the main body 12A, and a second support column 44 having one end inserted into the bottom surface of the main body 12A. The other end of the first support column 42 is inserted into a first connecting portion 46. The other end of the second support column 44 is inserted into a second connecting portion 48. The first support column 42 and the second support column 44 are not parallel to each other, but are arranged so as to be spaced apart from each other from one end to the other.

[0027] A first retaining post 52 penetrates the first connecting portion 46, and a second retaining post 54 penetrates the second connecting portion 48. The first retaining post 52 and the second retaining post 54 are arranged approximately parallel to each other. A third retaining post 56 is inserted between the first connecting portion 46 and the second connecting portion 48 so as to maintain the distance between the first connecting portion 46 and the second connecting portion 48. The third retaining post 56 intersects (e.g., perpendicular to) the first retaining post 52 and the second retaining post 54.

[0028] The first support column 52, the second support column 54, and the third support column 56 are each a cylinder (i.e., a hollow pipe) with their respective central axes positioned on approximately the same plane. The first support column 52, the second support column 54, and the third support column 56 may each be a square column, a flat plate, or the like.

[0029] A first plane on which the central axes of the first arm 14, the second arm 16, the first support arm 22, and the second support arm 24 are located is approximately parallel to a second plane on which the central axes of the first support column 52, the second support column 54, and the third support column 56 are located.

[0030] The first support pillar 42 and the second support pillar 44 are each a cylinder (i.e., a hollow pipe) and their respective central axes are located in approximately the same plane. The first support pillar 42 and the second support pillar 44 may each be a square pillar, a flat plate, or the like. The third plane on which the central axes of the first support pillar 42 and the second support pillar 44 are located intersects (e.g., is perpendicular to) each of the first plane and the second plane.

[0031] Next, a method for manufacturing the aircraft 10A according to the first embodiment will be described.

[0032] In step (a), the main body 12A, the first holding portion 18, the second holding portion 20, the first connecting portion 46, and the second connecting portion 48 are integrally manufactured using a resin containing a carbon component using a three-dimensional printer (hereinafter referred to as a "3D printer"). As a result, the main body 12A, the first holding portion 18, the second holding portion 20, the first connecting portion 46, and the second connecting portion 48 can be configured as a single member (i.e., a block) without being divided into a first member and a second member. The order in which the main body 12A, the first holding portion 18, the second holding portion 20, the first connecting portion 46, and the second connecting portion 48 are manufactured is not limited to this. For example, the order may be reversed, such as first retaining portion 18, second retaining portion 20, first connecting portion 46, second connecting portion 48, and main body 12A, or second retaining portion 20, first connecting portion 46, second connecting portion 48, main body 12A, and first retaining portion 18. Furthermore, main body 12A, first retaining portion 18, second retaining portion 20, first connecting portion 46, and second connecting portion 48 may be manufactured simultaneously.

[0033] When manufacturing the main body 12A using a 3D printer, through-holes through which the first arm 14 and the second arm 16 can pass are formed in the main body 12A. Similarly, grooves into which one ends of the first arm 14 and the second arm 16 can be inserted and a through-hole through which the first support arm 22 can pass are formed in the first holding portion 18. Grooves into which the other ends of the first arm 14 and the second arm 16 can be inserted and a through-hole through which the second support arm 24 can pass are formed in the second holding portion 20. Grooves into which the respective ends of the first support column 42 and the third support column 56 can be inserted and a through-hole through which the first support column 52 can pass are formed in the first connecting portion 46. Grooves into which the respective ends of the second support column 44 and the third support column 56 can be inserted and a through-hole through which the second support column 54 can pass are formed in the second connecting portion 48.

[0034] When manufacturing the main body 12A using a 3D printer, grooves into which the flight controller, electrical wiring, etc. can be inserted are formed in the main body 12A.

[0035] In step (b), a support having a plurality of ends and penetrating the main body 12A is manufactured. Specifically, the support is manufactured as follows.

[0036] In step (b-1), the first arm 14 and the second arm 16, which have been prepared in advance, are passed through the main body 12A.

[0037] In step (b-2), one end (the right end in FIG. 1) of each of the first arm 14 and the second arm 16 is inserted into one of the four side surfaces of the first holding part 18, that faces the main body 12A (the left side in FIG. 1). In step (b-3), one of the four side surfaces of the second holding part 20, that faces the main body 12A (the right side in FIG. 1), is inserted into the other end (the left end in FIG. 1) of each of the first arm 14 and the second arm 16. In step (b-4), the first support arm 22, which has been prepared in advance, is passed through two opposing side surfaces (the rear and front sides in FIG. 1) of the four side surfaces of the first holding part 18. In step (b-5), the second support arm 24 prepared in advance is passed through the second holding portion 20 through two opposing sides (the rear and front sides in Figure 1) of the four sides of the second holding portion 20.

[0038] This produces the support.

[0039] The order of steps (b-1) to (b-5) is not limited to this. For example, the order may be step (b-2), step (b-4), step (b-1), step (b-3), and step (b-5), or the order may be step (b-4), step (b-5), step (b-2), step (b-1), and step (b-3).

[0040] In step (c), the motor and propeller are positioned.

[0041] Specifically, in step (c-1), the first motor 30N1 and the first propeller 32N1 are disposed at one end of the first support arm 22. In step (c-2), the second motor 30N2 and the second propeller 32N2 are disposed at the other end of the first support arm 22.

[0042] In step (c-3), the third motor 30N3 and the third propeller 32N3 are disposed at one end of the second support arm 24. In step (c-4), the fourth motor 30N4 and the fourth propeller 32N4 are disposed at the other end of the second support arm 24.

[0043] The order of steps (d-1) to (d-4) is not limited to this. For example, the order may be reversed, or may be steps (d-2), (d-3), (d-4), and (d-1), or steps (d-3), (d-4), (d-1), and (d-2).

[0044] In step (d), the support portion of the main body 12A is manufactured.

[0045] Specifically, in step (d-1), one end of each of the first support column 42 and the second support column 44 is inserted into the bottom surface of the main body 12A. In step (d-2), the first connecting portion 46 and the second connecting portion 48 are inserted into the other end of each of the first support column 42 and the second support column 44.

[0046] In step (d-3), the first retaining post 52 is inserted through the first connecting portion 46, and the second retaining post 54 is inserted through the second connecting portion 48. In step (d-4), the third retaining post 56 is inserted between the first connecting portion 46 and the second connecting portion 48 so as to maintain the distance between the first connecting portion 46 and the second connecting portion 48.

[0047] The order of steps (d-1) to (d-4) is not limited to this. For example, the order may be reversed, or may be steps (d-2), (d-3), (d-4), and (d-1), or steps (d-2), (d-3), (d-4), and (d-1).

[0048] In step (e), the flight controller, electrical wiring, etc. are inserted into the main body 12A. Electrical wiring is arranged between the flight controller and the first motor 30N1 to the fourth motor 30N4. The electrical wiring from the main body 12A is arranged on the surfaces (or inside) of the first arm 14, the second arm 16, the first holding portion 18, the second holding portion 20, the first support arm 22, and the second support arm 24.

[0049] In the manufacturing method of the aircraft 10A according to the first embodiment described above, the main body 12A and the support body are separately manufactured using a 3D printer. However, the technology of the present disclosure is not limited to this. For example, the main body 12A and the support body may be manufactured as a whole as a single unit using a 3D printer. In this case, the first arm 14 and the second arm 16 may be manufactured as a single unit using a 3D printer, with the first arm 14 and the second arm 16 made of different materials from the main body 12A, so that the first arm 14 and the second arm 16 penetrate the main body 12A. The first support arm 22 may be manufactured as a single unit using a 3D printer, with the first support arm 22 made of different materials from the first holding portion 18, so that the first support arm 22 penetrates the first holding portion 18. The second support arm 20 may be manufactured as a single unit using a 3D printer, with the second holding portion 20 made of different materials from the second support arm 24, so that the second holding portion 20 penetrates the second support arm 24. As a result, the main body 12A and the support body are integrally formed as a whole.

[0050] Next, the effects of the aircraft 10A according to the first embodiment will be described.

[0051] As described above, each of the main body 12A, the first holding portion 18, the second holding portion 20, the first connecting portion 46, and the second connecting portion 48 is not divided into a first member and a second member, but is composed of a single member (i.e., a block).

[0052] Therefore, firstly, it is possible to prevent the main body 12A from being separated into the first member and the second member, thereby preventing the first arm 14 and the second arm 16 from coming off. Similarly, it is possible to prevent the first support arm 22 from coming off the first holding portion 18, the second support arm 24 from the second holding portion 20, the first holding column 52 and the third holding column 56 from the first connecting portion 46, and the second holding column 54 and the third holding column 56 from the second connecting portion 48. Therefore, this embodiment can make the aircraft 10A more difficult to disassemble than conventional aircraft.

[0053] Second, because the main body 12A, the first holding portion 18, the second holding portion 20, the first connecting portion 46, and the second connecting portion 48 themselves are not separable as described above, the strength of each can be greater than that of conventional aircraft. As described above, the main body 12A, the first holding portion 18, the second holding portion 20, the first connecting portion 46, and the second connecting portion 48 are integrally manufactured using a resin containing a carbon component by a 3D printer, so the strength of each can be greater than that of conventional aircraft. Therefore, this embodiment can make the aircraft 10A less likely to be disassembled than conventional aircraft.

[0054] Third, the number of parts can be reduced by eliminating members connecting the upper and lower plates, etc. Therefore, in this embodiment, the aircraft 10A can be made less likely to be disassembled than conventional aircraft.

[0055] Fourth, since there is no manufacturing process such as connecting upper and lower members for each of the main body 12A, first holding portion 18, second holding portion 20, first connecting portion 46, and second connecting portion 48, it can be manufactured in a shorter time than conventional aircraft.

[0056] Furthermore, in the present embodiment, one end of the first arm 14 and the second arm 16 does not get inserted into the main body 12A but instead penetrates the main body 12A, which prevents the first arm 14 and the second arm 16 from coming off the main body 12A. Similarly, it is possible to prevent the first support arm 22 from coming off the first holding portion 18, the second support arm 24 from the second holding portion 20, the first holding column 52 from the first connecting portion 46, and the second holding column 54 from the second connecting portion 48. Therefore, the present embodiment makes it possible to make the aircraft 10A less susceptible to disassembly than conventional aircraft.

[0057] It is also conceivable to manufacture each of the main body 12A, the first holding portion 18, the second holding portion 20, the first connecting portion 46, and the second connecting portion 48 by injection molding. However, injection molding involves creating a mold with a cavity of the same shape as the product, pouring heated carbon into the mold, cooling it, and then cutting off unnecessary portions of the cooled carbon to manufacture each of the main body 12A, the first holding portion 18, the second holding portion 20, the first connecting portion 46, and the second connecting portion 48. This requires large-scale equipment and a relatively long time. If a manufacturer that already has large-scale equipment were to manufacture the products without preparing large-scale equipment, it would require even longer time for ordering, transportation, etc.

[0058] However, in this embodiment, the main body 12A, the first holding portion 18, the second holding portion 20, the first connecting portion 46, and the second connecting portion 48 are each manufactured using a 3D printer, so that the main body 12A, the first holding portion 18, the second holding portion 20, the first connecting portion 46, and the second connecting portion 48, and thus the drone, can be manufactured using simple equipment and in a short period of time.

[0059] Furthermore, each of the first arm 14, the second arm 16, the first support arm 22, the second support arm 24, the first holding column 52, the second holding column 54, and the third holding column 56 is made of a hollow pipe, which makes it possible to reduce the weight of each of the first arm 14, the second arm 16, the first support arm 22, the second support arm 24, the first holding column 52, the second holding column 54, and the third holding column 56, and ultimately the drone.

[0060] In the first embodiment, as described above, one support is provided. Specifically, the support includes a first arm 14 and a second arm 16 that penetrate the main body 12A via two opposing side surfaces (the left and right side surfaces in FIG. 1 ) of the four side surfaces of the main body 12A and are arranged substantially parallel to each other. Description of other components of the support will be omitted. The technology of the present disclosure is not limited to this. For example, multiple support bodies may be provided. For example, the support may further include a first arm and a second arm that penetrate the main body 12A via two opposing side surfaces (the rear and front side surfaces in FIG. 1 ) of the four side surfaces of the main body 12A and are arranged substantially parallel to each other. Furthermore, the main body 12A may be configured as a polygonal prism with a diameter of more than four (e.g., 6, 8, 10, etc.), and the support may penetrate each opposing side surface.

[0061] Second Embodiment Figure 2 shows a partial perspective view of the upper part of an aircraft 10B according to a second embodiment. The aircraft 10B according to the second embodiment has the same configuration as the main body 12A and the portion below the main body 12A of the aircraft 10A according to the first embodiment, and therefore a description thereof will be omitted. As shown in Figure 2, the aircraft 10B according to the second embodiment includes a first arm 102 and a second arm 104 penetrating the main body 12A, instead of the first arm 14 and the second arm 16, the first holding portion 18 and the second holding portion 20, and the first support arm 22 and the second support arm 24 of the aircraft 10A according to the first embodiment. The first arm 102 and the second arm 104 have approximately the same length and are arranged inside the main body 12A, spaced apart, with their respective longitudinal directions substantially perpendicular to each other.

[0062] Each of the first arm 102 and the second arm 104 has one end and the other end. The first arm 102 has a first motor 30N1 and a first propeller 32N1 rotated by the first motor 30N1 at one end thereof. The second arm 102 has a second motor 30N2 and a second propeller 32N2 rotated by the second motor 30N2 at the other end thereof. The second arm 104 has a third motor 30N3 and a first propeller 32N3 rotated by the third motor 30N3 at one end thereof. The second arm 104 has a fourth motor 30N4 and a fourth propeller 32N4 rotated by the fourth motor 30N4 at the other end thereof.

[0063] The first arm 102 and the second arm 104 are examples of the "support body" and "plurality of arms" of the technology of the present disclosure.

[0064] The difference is that the main body 12A of the aircraft 10A of the first embodiment is a rectangular parallelepiped, whereas the main body 12A of the aircraft 10B of the second embodiment is a cube.

[0065] The main body 12A may be configured as a polygonal prism with more than four sides (six, eight, ten, etc.), with arms having motors and propellers at both ends passing through each opposing side.

[0066] Next, a method for manufacturing the aircraft 10B according to the second embodiment will be described. The method for manufacturing the aircraft 10B according to the second embodiment is substantially the same as the method for manufacturing the aircraft 10A according to the first embodiment, and therefore only differences will be described.

[0067] When manufacturing the main body 12A using a 3D printer, through-holes are formed through which the first arm 102 and the second arm 104 can pass.

[0068] The support (first arm 102 and second arm 104) passes through the main body 12A.

[0069] A first motor 30N1 and a first propeller 32N1 are provided at one end of the first arm 102, a second motor 30N2 and a second propeller 32N2 are provided at the other end of the first arm 102, a third motor 30N3 and a first propeller 32N3 are provided at one end of the second arm 104, and a fourth motor 30N4 and a fourth propeller 32N4 are provided at the other end of the second arm 104. The order in which the motors and propellers are provided is not limited to this.

[0070] 3 shows a partial perspective view of the upper part of an aircraft 10C according to a third embodiment. The aircraft 10C according to the third embodiment has substantially the same configuration as the aircraft 10B according to the second embodiment, and therefore only the differences will be described.

[0071] The aircraft 10C includes a first arm 102 and a second arm 104. The first arm 102 and the second arm 104 have approximately the same length.

[0072] The first arm 102 and the second arm 104 of the aircraft 10B of the second embodiment are cylindrical (see FIG. 2), whereas the first arm 102C and the second arm 104C that penetrate the main body 12A of the aircraft 10C of the third embodiment are bent within the main body 12A. Thus, the first arm 102 and the second arm 104 of the aircraft 10B of the second embodiment penetrate opposite side surfaces of the main body 12A, whereas the first arm 102C and the second arm 104C of the aircraft 10C of the third embodiment penetrate adjacent side surfaces of the main body 12A.

[0073] The main body 12A may be configured as a polygonal prism with more than four sides (such as six, eight, ten, etc.), and arms with motors and propellers at both ends may be bent and passed through the main body 12A on adjacent sides.

[0074] In the third embodiment, the main body 12A, the first arm 102C, and the second arm 104C are integrally manufactured using different materials by a 3D printer.

[0075] 4 shows a partial perspective view of the upper part of an aircraft 10D according to a fourth embodiment. The aircraft 10D according to the fourth embodiment has substantially the same configuration as the aircraft 10B according to the second embodiment, and therefore only the differences will be described.

[0076] The aircraft 10D is equipped with an arm 10204.

[0077] The aircraft 10B of the second embodiment is equipped with a first arm 102 and a second arm 104 that are separate members, spaced apart, and whose longitudinal directions are approximately perpendicular to each other (see Figure 2), whereas the aircraft 10D of the fourth embodiment differs in that it is equipped with a single arm 10204 where the first arm 102 and the second arm 104 intersect, for example, perpendicular to each other and are integrally constructed.

[0078] The main body 12A may be constructed from a polygonal column with more than four sides (5, 6, 7, 8, 9, 10, etc.), and may be manufactured so that an arm with a motor and propeller at one end passes through each side.

[0079] In the fourth embodiment, the main body 12A and the arm 10204 are manufactured as a single unit using a 3D printer and different materials.

[0080] Fifth Embodiment Fig. 5 shows an overall perspective view of an aircraft 10E according to a fifth embodiment. The aircraft 10E according to the fifth embodiment has substantially the same configuration as the aircraft 10A according to the first embodiment, and therefore only the differences will be described.

[0081] As shown in FIG. 5 , the aircraft 10E includes an integrally formed main body 12A and a plurality of (e.g., two) support sections, one end of which is inserted into the main body 12A. The plurality of support sections may be, for example, two support sections (a first support section and a second support section). As will be described in detail below, the first support section includes a first arm 14B, a second arm 16B, a first holding section 18, and a first support arm 22. The second support section includes a first arm 14A, a second arm 16A, a second holding section 20, and a second support arm 24. In particular, one end of each of the first arm 14A, the second arm 16A, the first arm 14B, and the second arm 16B is inserted into the main body 12A.

[0082] The first arm 14 and the second arm 16 of the aircraft 10A of the first embodiment pass through the main body 12A, whereas in the aircraft 10E of the fifth embodiment, the first arm 14 and the second arm 16 are each divided into two, and one end of each of the divided first arms 14A, 14B and second arms 16A, 16B is inserted into the main body 12A.

[0083] 5, the aircraft 10E includes four arms, namely, first arms 14A and 14B and second arms 16A and 16B, but the technology of the present disclosure is not limited thereto. For example, each of the first support portion and the second support portion of the aircraft 10E may include one arm having both ends, or may include more than two arms each having both ends.

[0084] The first arms 14A, 14B and the second arms 16A, 16B are an example of the "arm portion" of the technology of the present disclosure.

[0085] Next, a description will be given of a manufacturing method for the aircraft 10E. The manufacturing method for the aircraft 10E is substantially the same as the manufacturing method for the aircraft 10A, and therefore, only the differences will be mainly described.

[0086] One end of each of the first and second support parts is inserted into the main body 12A. A motor and a propeller rotated by the motor are disposed at the other end of each of the first and second support parts, i.e., at each of the multiple ends of the support body. Specifically, one end of each of the first arms 14A, 14B and the second arms 16A, 16B is inserted into the main body 12A.

[0087] Sixth Embodiment Fig. 6 shows an overall perspective view of an aircraft 10F according to a sixth embodiment. The aircraft 10F according to the sixth embodiment has substantially the same configuration as the aircraft 10A according to the first embodiment, and therefore only the differences will be described.

[0088] The main body 12A of the aircraft 10A of the first embodiment is not divided into an upper member and a lower member, but is composed of a single member, whereas the main body 12B of the aircraft 10F of the sixth embodiment differs in that it comprises an upper member 12U and a lower member 12D.

[0089] The upper member 12U and the lower member 12D are examples of the "first member" and the "second member" of the technology of the present disclosure.

[0090] Between the upper and lower members 12U, 12D, the support, in particular the first and second arms 14, 16, pass.

[0091] Next, a description will be given of a manufacturing method for the aircraft 10E. The manufacturing method for the aircraft 10E is substantially the same as the manufacturing method for the aircraft 10A, and therefore, only the differences will be mainly described.

[0092] The main body 12B is manufactured by producing the upper member 12U and the lower member 12D using a 3D printer. The upper member 12U and the lower member 12D are connected together with the support, particularly the first arm 14 and the second arm 16, passing through them. The upper member 12U and the lower member 12D are connected together by connecting parts such as screws, for example.

[0093] 7 to 9 show partial perspective views of the upper portions of aircraft 10G to 10I according to the seventh to ninth embodiments. The aircraft 10G to 10I according to the seventh to ninth embodiments have substantially the same configuration as the aircraft 10B to 10D according to the second to fourth embodiments, and therefore only the differences will be described.

[0094] The main body 12A of the aircraft 10B to 10D of the second to fourth embodiments is not divided into an upper member and a lower member but is composed of a single member, whereas the main body 12B of the aircraft 10G to 10I of the seventh to ninth embodiments differs in that it comprises an upper member 12U and a lower member 12D.

[0095] The manufacturing method for the aircraft 10G to 10I according to the seventh to ninth embodiments is substantially similar to the manufacturing method for the aircraft 10B to 10D according to the second to fourth embodiments, and therefore only the differences will be described.

[0096] The main body 12B is manufactured by manufacturing the upper member 12U and the lower member 12D using a 3D printer.

[0097] In the aircraft 10G (see FIG. 7 ), a first arm 102 passes through an upper member 12U, and a second arm 104 passes through a lower member 12D. The upper member 12U and the lower member 12D are connected together with the first arm 102 passing through the upper member 12U and the second arm 104 passing through the lower member 12D.

[0098] In the aircraft 10H (see FIG. 8), the upper member 12U and the lower member 12D are connected together so that the first arm 102C and the second arm 104C pass through them.

[0099] In the aircraft 10I (see FIG. 9), the upper member 12U and the lower member 12D are connected together so that the arm 10204 passes through them.

[0100] In the seventh embodiment of the aircraft 10G (see Figure 7), the main body 12B may be configured as a polygonal prism with more than four sides (such as a polygonal prism with six, eight, ten, etc.), and arms with motors and propellers at both ends may pass through each opposing side.

[0101] In the eighth embodiment of the aircraft 10H (see Figure 8), the main body 12B may be configured as a polygonal prism having a size greater than four (e.g., a polygonal prism having a size of six, eight, ten, etc.), and arms having motors and propellers at both ends may be bent and passed through the main body 12A on adjacent sides.

[0102] In the ninth embodiment of the aircraft 10I (see Figure 9), the main body 12B may be constructed as a polygonal prism with more than four sides (e.g., polygonal prisms of 5, 6, 7, 8, 9, 10, etc.), and may be manufactured so that arms with motors and propellers at one end pass through from each side.

[0103] The aircraft may be, for example, a drone (i.e., a rotary-wing aircraft), but may also be a vertical takeoff and landing (VTOL) aircraft with a propeller, a fixed-wing aircraft with a propeller, or a helicopter. The aircraft may be manned or unmanned.

[0104] The first to ninth embodiments described above are merely examples, and it goes without saying that unnecessary components may be deleted, new components may be added, unnecessary processing steps may be deleted, new processing steps may be added, or the processing order may be changed, without departing from the spirit of the invention.

[0105] All publications, patent applications, and technical standards mentioned in this specification are herein incorporated by reference to the same extent as if each individual publication, patent application, or technical standard was specifically and individually indicated to be incorporated by reference.

Claims

[Claim 1] The main body and a support having a plurality of ends and extending through the body; a motor disposed at each of the plurality of ends of the support and a propeller rotated by the motor; An aircraft comprising: The aircraft, wherein the main body is integrally constructed by being made of a single member.