Flight vehicle

Abstract

To provide a technique that can avoid rigidity of an arm of a flight vehicle from deteriorating.SOLUTION: A flight vehicle according to one embodiment of the present invention comprises a body and a flying power mechanism for floating the body. The flight vehicle comprises an arm, a cover member and a wiring member. The arm is constituted to support the flying power mechanism. The cover member is mounted on the back side of the arm and the cover member forms a storage space between the outside surface of the arm and the member. The wiring member extends along the outside surface of the arm and is arranged in the storage space.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present invention relates to a flying object.

Background Art

[0002] There has been proposed a flying object having an arm that supports a flight power mechanism such as a propeller, and wiring or the like is passed through the space inside the arm (Patent Document 1). The wiring or the like is used, for example, for controlling and supplying power to the propeller or the like.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] When wiring or the like is arranged inside the arm, it is possible to protect the wiring or the like. However, for example, it is necessary to form holes in the arm for routing the wiring, and there is a concern that the rigidity of the arm may be reduced.

[0005] In view of the above circumstances, the present invention aims to provide a technique for avoiding a reduction in the rigidity of the arm of a flying object.

Means for Solving the Problems

[0006] According to one aspect of the present invention, there is provided a flying object including a body and a flight power mechanism for lifting the body. The flying object includes an arm, a cover member, and a wiring member. The arm is configured to support the flight power mechanism. The cover member is attached to the back side of the arm, and the cover member forms a housing space between the cover member and the outer surface of the arm. The wiring member extends along the outer surface of the arm and is disposed in the housing space.

[0007] According to the present disclosure, it is possible to avoid a decrease in the rigidity of the arm of the flying object.

Brief Description of the Drawings

[0008]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Figure 7

Mode for Carrying Out the Invention

[0009] [Embodiment] Hereinafter, embodiments of the present invention will be described with reference to the drawings. Various features shown in the following embodiments can be combined with each other.

[0010] 1. Explanation of the overall configuration FIG. 1 is a front view of the flying object 100 according to the embodiment. FIG. 2 is a top view of the flying object 100 shown in FIG. 1. FIG. 3 is an enlarged view of the periphery of one of the flight power mechanisms 140 included in the flying object 100 shown in FIG. 2. In FIG. 3, the internal structure (wiring member 160 and rib member 170) hidden inside the cover member 150 is schematically shown by a broken line.

[0011] The flying object 100 is a flying object including a body 120 and a flight power mechanism 140 for lifting the body 120. Specifically, in an example of the embodiment, the flying object 100 includes a body 120, arms 130, a flight power mechanism 140 (propeller), a cover member 150, a wiring member 160 (see Fig. 5(a)), and a rib member 170 (see Fig. 5(a)).

[0012] 1.1 Body 120 The body 120 is located, for example, at approximately the center of the flying object 100, and a plurality of arms 130 are provided on the body 120. Inside the body 120, for example, a battery unit, a control device, etc. (not shown) are provided. The control device is configured to execute control related to the flight of the flying object 100, for example.

[0013] In the embodiment, the shape of the body 120 shown in Fig. 1 etc. is an example, and the shape is not particularly limited as long as the flying object 100 can fly stably. Also, the body 120 may be made of, for example, metal, or may be made of a non-metal such as plastic or carbon fiber reinforced plastic.

[0014] 1.2 Arms 130 The arms 130 are configured to support the flight power mechanism 140. The flying object 100 has a plurality of arms 130, and the flying object 100 in the embodiment has 24 arms 130. Also, the flight power mechanism 140 is arranged on the end side of each arm 130. Among the arms 130, some are directly connected to the body 120, and some are connected to a pair of flight power mechanisms 140 and not directly connected to the body 120. Whether the flying object 100 has an arm 130 that is not directly connected to the body 120 is arbitrary. The arms 130 may be made of, for example, metal, or may be made of a non-metal such as plastic or carbon fiber reinforced plastic.

[0015] 1.3 Flight Power Mechanism 140 The flight power mechanism 140 is a propeller in one example of the embodiment, but other power mechanisms may be adopted. The flight power mechanism 140 includes a rotor 141 composed of a motor or the like, and blades 142 configured to be rotatable. In one example of the embodiment, the flying object 100 is equipped with 12 flight power mechanisms 140. As shown in FIG. 2, the flight power mechanism 140 is provided at a site where a plurality of arms 130 are connected, but is not limited thereto. For example, it may be arranged at a position on the end side of a single arm 130.

[0016] 1.4 Cover member 150 The cover member 150 has a first function of improving the aerodynamic performance of the flying object 100 and a second function of suppressing disadvantages caused by a collision with an object such as a bird flying in the air (hereinafter also referred to as an obstacle). The cover member 150 may be made of, for example, metal, or may be made of a non-metal such as plastic or carbon fiber reinforced plastic. Although the cover member 150 is provided on the arm 130, there are some that do not produce the first function related to aerodynamics or have a small influence. The configuration of the cover member 150 will be described in detail later.

[0017] 1.5 Wiring member 160 and rib member 170 The wiring member 160 is provided, for example, so as to extend from the body 120 side to the flight power mechanism 140 side. The wiring member 160 is utilized, for example, for control signals and power transmission. The wiring member 160 includes a wiring 16a and a mounting member 16b for fixing the wiring 16a to the rib member 170. The rib member 170 is disposed inside the cover member 150 and fixed to the arm 130. The cover member 150 is provided outside the rib member 170, and the rib member 170 reinforces the cover member 150 from the inside. As a result, deformation of the cover member 150 due to, for example, impact is effectively suppressed, and the above-described second function is enhanced. The rib member 170 may be made of, for example, metal, or may be made of a non-metal such as plastic or carbon fiber reinforced plastic.

[0018] In the embodiment, the wiring member 160 is not disposed within the arm 130, but is disposed in the space outside the arm 130 (the space inside the cover member 150). Thereby, it is not necessary to form a hole (access hole) for routing the wiring member 160 inside and outside the arm 130, and it is possible to avoid a decrease in the rigidity of the arm 130. On the other hand, if the wiring member 160 is exposed, when the arm 130 collides with an object such as a bird flying in the air, the wiring member 160 may be caught and the possibility of damage to the wiring member 160 increases. For this reason, in the embodiment, the wiring member 160 is protected by the cover member 150, and damage to the wiring member 160 is avoided (corresponding to the second function described above). Further, in the embodiment, the cover member 150 is arranged so as to improve the aerodynamic performance of the flying object 100 (corresponding to the first function described above).

[0019] 2. Detailed Configuration Description 2.1. Description of Non-attached Arm and Attached Arm FIG. 4 is a top view showing the attached arm 130b of the flying object 100 shown in FIG. 1 in (a), and a top view showing the non-attached arm 130a and the attached arm 130bb of the flying object 100 shown in FIG. 1 in (b). Note that the attached arm 130bb is not disposed on the back side of the arm 130, which will be described later. With reference to FIG. 4, the configuration of the arm 130 will be described in detail.

[0020] In the embodiment, the arm 130 of the flying object 100 can be divided into an arm to which the cover member 150 is attached and an arm to which the cover member 150 is not attached. That is, the plurality of arms 130 of the flying object 100 include a non-attached arm 130a and attached arms 130b and 130bb. The non-attached arm 130a is an arm to which the cover member 150 is not attached, and the attached arms 130b and 130bb are arms to which the cover member 150 is attached.

[0021] The flying object 100 has ten non-attached arms 130a, and the flying object 100 also has fourteen attached arms 130b and 130bb. Among the 14 mounting arms, 10 mounting arms 130b (see Fig. 4(a)) incorporate both the first function and the second function of the cover member 150. Thus, the cover member 150 incorporating the first function and the second function is attached to the back side (downstream side in the air flow direction) of the arm 130 in the traveling direction Dr of the flying object 100. Among the remaining 4 mounting arms 130bb (see Fig. 4(b)) of the 14 mounting arms, the significance of the aerodynamic first function is not great or is nonexistent, and the second function is the main one. This mounting arm 130bb is attached to, for example, the lower surface side of the arm 130.

[0022] 2.2. Detailed Configuration Explanation around the Cover Member 150 Fig. 5 is a perspective view showing the arm 130, the cover member 150, the wiring member 160, and the rib member 170. Fig. 6 is an end view of the arm 130 and the cover member 150 cut along a vertical plane. With reference to Figs. 5 and 6, the configuration such as the cover member 150 will be described in detail.

[0023] In Fig. 5, a state is shown in which the cover member 150 is separated into an upper cover member 15a and a lower cover member 15b, and the internal structure of the cover member 150 can be seen. Also, in Fig. 5, the wiring 16a of the wiring member 160 is schematically shown as passing through one, but it is not limited to this, and more wirings may be passed through. In Fig. 6, for convenience of explanation, the wiring member 160 and the rib member 170 are not shown.

[0024] In Figs. 5 and 6, as an example, the arm 130 is shown schematically as being hollow and having a cylindrical shape (the cross-sectional shape is circular), but it is not limited to this. The arm 130 may be, for example, solid, or the cross-sectional shape may be, for example, polygonal or elliptical.

[0025] The cover member 150 includes an upper cover member 15a and a lower cover member 15b. The upper cover member 15a has an upper surface 15a1 and a rear surface 15a2. The lower cover member 15b is disposed below the upper cover member 15a and has a lower surface 15b1 and a rear surface 15b2. The cover member 150 forms an accommodation space Sp between it and the outer surface Sr of the arm 130 (mounting arm 130b). Specifically, the accommodation space Sp is formed by the upper cover member 15a, the lower cover member 15b, and the outer surface Sr of the arm 130 (mounting arm 130b). The accommodation space Sp is formed to extend in the longitudinal direction of the arm 130 (mounting arm 130b).

[0026] As shown in FIG. 6, in the cover member 150 of the flying object 100, the upper surface 15a1 and the lower surface 15b1 face each other. The cover member 150 is configured such that the facing interval D between the upper surface 15a1 and the lower surface 15b1 decreases as it goes rearward. In other words, the cover member 150 is formed to taper in the direction opposite to the traveling direction Dr of the flying object 100. Thereby, the air passing through the arm 130 can flow smoothly rearward, and air resistance can be suppressed. In the embodiment, the upper surface 15a1 has a curved surface that curves upwardly convex from the front end side to the rear end side. The lower surface 15b1 has a curved surface that curves downwardly convex from the front end side to the rear end side.

[0027] Note that the means by which the cover member 150 is attached to the arm 130 (attachment arm 130b) is not particularly limited. For example, the cover member 150 may be attached by being welded to the attachment arm 130b. Further, a first engaging portion (not shown) is provided on the cover member 150, a second engaging portion (not shown) is provided on the attachment arm 130b, and the cover member 150 may be attached by engaging the first engaging portion of the cover member 150 with the second engaging portion of the attachment arm 130b. As the first and second engaging portions, for example, a fitting mechanism may be employed, or they may be constituted by bolts and nuts. Further, these means may be used singly or in combination. Further, the first and second engaging portions may be formed by processing the cover member 150 itself, or may be configured by providing a mechanism (separate member) separate from the cover member 150 on the cover member 150.

[0028] As shown in FIG. 6, the back surface 15a2 and the back surface 15b2 are provided so that at least a part thereof overlaps. The back surface 15a2 and the back surface 15b2 can be attached to each other by any attachment means at the overlapping portion. As the attachment means, for example, the above-described means (for example, welding, engaging portions, etc.) can be used.

[0029] As shown in FIGS. 5 and 6, the rib member 170 is attached to the outer surface Sr of the arm 130 (attachment arm 130b), and the rib member 170 is disposed in the accommodation space Sp. In the embodiment, although it is described that a plurality of rib members 170 are arranged side by side in the longitudinal direction of the arm 130 for one arm 130, the present invention is not limited thereto, and a configuration in which a single rib member 170 is arranged may be employed. In this case, it is preferable that the rib member 170 has a configuration in which it is enlarged so as to extend in the longitudinal direction of the arm 130.

[0030] The rib member 170 has a first portion 171, a pair of upper and lower second portions 172, and a third portion 173. Further, an insertion portion 174 through which the wiring member 160 passes is formed in the rib member 170 in the flying object 100.

[0031] The first part 171 is formed, for example, along the outer surface Sr of the arm 130 (mounting arm 130b). And the first part 171 is attached to the arm 130 (mounting arm 130b). The attachment means is not particularly limited, and for example, the above-described means (such as welding or engaging portions, etc.) can be used.

[0032] The lower second part 172 is formed, for example, along the lower surface 15b1. Although the upper second part 172 is not shown in the figure, it is formed, for example, along the upper surface 15a1. The lower second part 172 is connected to the lower end of the first part 171, and the upper second part 172 is connected to the upper end of the first part 171. Also, the lower second part 172 is connected to the lower end of the third part 173, and the upper second part 172 is connected to the upper end of the third part 173.

[0033] The third part 173 is formed along the rear surfaces 15a2 and 15b2.

[0034] Note that the lower second part 172 may be in direct contact with the lower surface 15b1, or a gap may be formed. Similarly, the upper second part 172 may be in contact with the upper surface 15a1, or a gap may be formed, and the third part 173 may be in contact with the rear surfaces 15a2 and 15b2, or a gap may be formed. These gaps (mm) are specifically, for example, 1, 2, 3, 4, 6, 8, 10, 12, 14, 16, 18, 20, and may be within the range between any two of the values exemplified here. Note that other members may be interposed in these gap portions to fill the gaps.

[0035] The insertion part 174 is an open part (an opening in the embodiment) formed inside the first part 171, the second part 172, and the third part 173. Note that the rib member 170 may not have, for example, the third part 173, and the shape of the rib member 170 may be a C shape.

[0036] The wiring member 160 extends along the outer surface Sr of the arm 130. Also, the wiring member 160 is disposed in the accommodation space Sp. The wiring 16a of the wiring member 160 is passed through the insertion portion 174. The attachment member 16b of the wiring member 160 is fixed to the first portion 171 of the rib member 170, but is not limited thereto, and may be fixed to the second portion 172 or the third portion 173.

[0037] FIG. 7 is a view showing a part of the flying object 100 and is an explanatory view of the angle θ of the mounting arm 130b and the like. As shown in FIG. 7, the mounting arm 130b in the flying object 100 forms a predetermined angle θ with respect to the lateral width direction Wd of the flying object 100. This predetermined angle θ is the angle formed by the lateral width direction Wd and the arm 130 in a state where the flying object 100 has landed. Also, this angle θ is the angle formed by the lateral width direction Wd and the arm 130 in a state where the flying object 100 is viewed from above. Specifically, the angle θ is, for example, 0, 5, 10, 15, 20, 25, 30, 35, 40, 45, 50, 55, 60 degrees, and may be within a range between any two of the numerical values exemplified herein. For example, this predetermined angle θ is 0 degrees or more and 60 degrees or less.

[0038] Note that it is not necessary to provide the cover member 150 taking into account the first function and the second function on all of the arms 130 that satisfy the above-described angle θ. For example, the arm 130 shown in FIG. 2 described above has an angle θ of about 50 degrees, for example, and is a non-mounting arm 130a, and the cover member 150 is not provided. Note that, among all of the arms 130 that satisfy the above-described angle θ, it is preferable that the cover member 150 is attached to α% of the arms 130. Specifically, the value of α is, for example, 30, 35, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, 95, 100, and may be within a range between any two of the numerical values exemplified herein.

[0039] As shown in FIG. 7, the cover member 150 is provided over the entire length in the longitudinal direction of the mounting arm 130b, but it does not necessarily have to be provided over the entire length. Specifically, for example, the cover member 150 is provided so as to extend over a range of 80, 82, 84, 86, 88, 90, 92, 94, 96, 98, 100% of the total length (total length in the longitudinal direction) of the mounting arm 130b, and it may be within the range between any two of the numerical values exemplified here. For example, the cover member 150 is provided so as to extend over a range of 80% or more of the total length of the mounting arm 130b in the longitudinal direction of the mounting arm 130b. Thereby, the aerodynamic first function and the second function for protecting the wiring member 160 can be appropriately exhibited.

[0040] 3. Avoidance of reduction in rigidity of the arm 130, etc. In the embodiment, the wiring member 160 is arranged in the accommodation space Sp and is not passed through the arm 130. For this reason, it is not necessary to form a hole (access hole) for routing the wiring member 160 in and out of the arm 130, and it is possible to avoid a reduction in the rigidity of the arm 130. Further, although the wiring member 160 is arranged outside the arm 130, since it is passed through the accommodation space Sp formed by the cover member 150, the wiring member 160 can be protected. Thereby, for example, when an obstacle collides with the arm 130, it is possible to avoid the obstacle catching the wiring member 160 and damaging the wiring member 160 (second function). Further, since the cover member 150 is arranged on the back side of the arm 130, air can flow smoothly and air resistance can be suppressed (first function), and as a result, the flight distance of the flying object 100 can be extended.

[0041] It may be provided in each of the aspects described below.

[0042] A flying object comprising a body and a flight power mechanism for lifting the body, the flying object comprising an arm, a cover member, and a wiring member, the arm being configured to support the flight power mechanism, the cover member being attached to the back side of the arm, and the cover member forming an accommodation space between the cover member and the outer surface of the arm, the wiring member extending along the outer surface of the arm and being disposed in the accommodation space.

[0043] (2) The flying object according to (1) above, further comprising a rib member, the rib member being attached to the outer surface of the arm and disposed in the accommodation space, the cover member being provided outside the rib member.

[0044] (3) The flying object according to (2) above, wherein an insertion portion through which the wiring member passes is formed in the rib member.

[0045] (4) The flying object according to any one of (1) to (3) above, wherein the cover member has an upper surface and a lower surface facing each other, and the cover member is configured such that the facing interval between the upper surface and the lower surface becomes smaller as it goes backward.

[0046] (5) The flying object according to any one of (4) above, wherein the cover member has an upper cover member and a lower cover member, the upper cover member has the upper surface, the lower cover member is disposed below the upper cover member and has the lower surface, and the accommodation space is formed by the upper cover member, the lower cover member, and the outer surface of the arm.

[0047] (6) The flying object according to any one of (1) to (5) above, having a plurality of the arms, the plurality of arms having a non-attached arm and an attached arm, the non-attached arm being the arm to which the cover member is not attached, and the attached arm being the arm to which the cover member is attached.

[0048] (7) In the flying object according to (6) above, the attachment arm forms a predetermined angle with respect to the lateral width direction of the flying object, and the predetermined angle is the angle formed by the lateral width direction and the arm in a state where the flying object has landed, and is 0 degrees or more and 60 degrees or less. Flying object.

[0049] (8) In the flying object according to (6) or (7) above, the cover member is provided so as to extend over a range of 80% or more of the total length of the attachment arm in the longitudinal direction of the attachment arm. Flying object. Of course, this is not the limit.

[0050] Finally, although various embodiments of the present invention have been described, these are presented as examples and are not intended to limit the scope of the invention. The novel embodiments can be implemented in various other forms, and various omissions, replacements, and changes can be made without departing from the gist of the invention. The embodiments and their modifications are included in the scope and gist of the invention, and are included in the invention described in the claims and the equivalent scope thereof.

Explanation of Signs

[0051] 100: Flying object 120: Body 130: Arm 130a: Non-attachment arm 130b: Attachment arm 130bb: Attachment arm 140: Flying power mechanism 141: Rotor 142: Blade 150: Cover member 15a: Upper cover member 15a1: Upper surface 15a2: Rear surface 15b: Lower cover member 15b1: Lower surface 15b2: Rear surface 160: Wiring member 16a: Wiring 16b: Mounting member 170: Rib member 171: First part 172: Second part 173: Third part 174: Insertion part

Claims

1. An aircraft comprising a body and a flight power mechanism for lifting the body, comprising an arm, a cover member, and a wiring member, wherein the arm is configured to support the flight power mechanism, the cover member is attached to the back side of the arm, and the cover member forms a housing space between the cover member and the outer surface of the arm, the wiring member extends along the outer surface of the arm and is disposed in the housing space.

2. The aircraft according to claim 1, further comprising a rib member, wherein the rib member is attached to the outer surface of the arm and is disposed in the housing space, and the cover member is provided outside the rib member.

3. The aircraft according to claim 2, wherein an insertion portion for passing the wiring member is formed in the rib member.

4. The aircraft according to claim 1, wherein the cover member has an upper surface and a lower surface facing each other, and the cover member is configured such that the facing interval between the upper surface and the lower surface becomes smaller toward the rear.

5. The aircraft according to claim 4, wherein the cover member has an upper cover member and a lower cover member, the upper cover member has the upper surface, the lower cover member is disposed below the upper cover member and has the lower surface, and the housing space is formed by the upper cover member, the lower cover member, and the outer surface of the arm.

6. The aircraft according to claim 1, having a plurality of the arms, wherein the plurality of arms include a non-attached arm and an attached arm, the non-attached arm is the arm to which the cover member is not attached, and the attached arm is the arm to which the cover member is attached.

7. The aircraft according to claim 6, wherein the attached arm forms a predetermined angle with respect to the lateral width direction of the aircraft, and the predetermined angle is the angle formed by the lateral width direction and the arm in a state where the aircraft has landed, and is 0 degrees or more and 60 degrees or less.

8. The aircraft according to claim 6, wherein the cover member is provided to extend over a range of 80% or more of the total length of the attached arm in the longitudinal direction of the attached arm.

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