CN111164010A

CN111164010A - Frame for unmanned aerial vehicle

Info

Publication number: CN111164010A
Application number: CN201880064193.3A
Authority: CN
Inventors: 米原慧纪; 吉原正典
Original assignee: Yamaha Motor Co Ltd
Current assignee: Yamaha Motor Co Ltd
Priority date: 2017-10-06
Filing date: 2018-04-27
Publication date: 2020-05-15
Anticipated expiration: 2038-04-27
Also published as: WO2019069498A1; KR20200040285A; JP2019069658A; KR102227049B1; CN111164010B; JP6522074B2

Abstract

The frame (10) for a multi-rotor aircraft (1) of the invention comprises: the frame body (24) has an opening (34) on the upper surface thereof, and has a 1 st recess (36) capable of accommodating the battery (12) and the electrical box (14). A flange part (66) is formed integrally with the frame main body (24) over the entire periphery of an edge part (68) on the opening (34) side of the frame main body (24). The frame body (24) has the 1 st ventilation holes (42a, 42b, 44a, 44b), the 2 nd ventilation holes (46), and ribs (58a, 58b, 60a, 60b, 62) are formed around the entire periphery of each ventilation hole. Wing attachment sections (74a, 74b) are integrally formed on the outer peripheral surface of the frame body (24). The wing mounting parts (74a, 74b) comprise: 2 nd recessed parts 76a, 76b recessed inward of the frame main body (24); and rib-like mounting body (78a, 80a, 78b, 80b) formed integrally with the frame body (24) in the 2 nd recess (76a, 76 b).

Description

Frame for unmanned aerial vehicle

Technical Field

The present invention relates to frames for unmanned aerial vehicles, and more particularly to frames for unmanned aerial vehicles for use in multi-rotor aircraft.

Background

In a frame used for an unmanned aerial vehicle, stress is transmitted from wing portions, leg portions, and the like during operations such as take-off, landing, and movement of the unmanned aerial vehicle, and a local load is increased by the weight of components such as a power source supporting the frame.

For example, in a frame used for a multi-rotor aircraft, during operations such as takeoff and landing, movement, and hovering of the multi-rotor aircraft, stress is transmitted from an aircraft wing portion including an arm, a skid (ski), and the like, and a local load is added by the weight of a component such as a battery supported by the frame. However, it is necessary to take measures so that the frame is not damaged by these stresses or loads and so that other components such as the inertial system sensor are not adversely affected.

As an example of such a conventional technique, patent document 1 discloses a drone for spreading agricultural chemicals. The unmanned aircraft comprises: a main body portion; wing parts arranged on the side surfaces of the main body part in a connected manner; a support part arranged at the lower part of the main body part in a connected manner; and a power supply part for supplying power to the wing part, wherein the main body part comprises a No. 1 frame and a No. 2 frame. The 1 st frame and the 2 nd frame are arranged in a horizontal direction at a distance from each other, and the fastening member of the wing part is fixed between the 1 st frame and the 2 nd frame, whereby the wing part is fixed to the main body part. The 1 st frame and the 2 nd frame are coupled to each other by a large number of 2 nd support members.

Documents of the prior art

Patent document

Patent document 1: korean patent No. 10-1662255

Disclosure of Invention

Technical problem to be solved by the invention

In patent document 1, as described above, the main body portion includes the 1 st frame and the 2 nd frame, the fastening member of the wing portion is fixed between the 1 st frame and the 2 nd frame, and the 1 st frame and the 2 nd frame are connected by the 2 nd support member in large number, so that the number of parts increases although it is possible to cope with stress or load generated during the operation of the drone.

Accordingly, a main object of the present invention is to provide a frame for an unmanned aerial vehicle, which can cope with stress and load generated when an unmanned aerial vehicle such as a multi-rotor aircraft operates, with a small number of components.

Means for solving the problems

According to an aspect of the present invention, there is provided a frame for an unmanned aerial vehicle having a power source, the frame for an unmanned aerial vehicle comprising: and a frame body having an opening on 1 surface and a 1 st recess portion capable of accommodating at least a part of the power source, and a flange portion integrally formed with the frame body on the entire circumference of the opening side of the frame body.

In the present invention, the flange portion is formed integrally with the frame body along the entire circumference of the opening of the frame body having the 1 st recessed portion, and the frame is configured as a single member, whereby the rigidity of the frame can be increased. Therefore, in the case where the frame body houses the components such as the power source and the unmanned aerial vehicle is configured by attaching the wing portions or the leg portions, stress is transmitted to the frame via the wing portions or the leg portions during operations such as take-off, landing, movement, and circling of the unmanned aerial vehicle, and even if a load is applied by the weight of the components, the frame is not damaged and can be handled without being adversely affected by other components. In this way, the number of components can be reduced to cope with stress and load generated when an unmanned aerial vehicle such as a multi-rotor aircraft operates.

Preferably, the flange portion is connected to an edge portion of the opening side of the frame main body. In this case, the rigidity of the entire frame and the rigidity of the edge portion can be increased.

Preferably, the flange portion is provided inside the frame body. In this case, the frame can be formed compactly without being enlarged outward.

More preferably, the flange portions are formed on the same plane. In this case, the rigidity of the frame can be further increased.

Preferably, the frame body has a 1 st hole for air cooling and a rib formed on the entire periphery of the 1 st hole. In this case, ventilation for air-cooling the inside of the 1 st recess of the frame body can be ensured, and a decrease in rigidity of the frame body and the frame due to the provision of the 1 st hole can be suppressed.

Preferably, the 1 st hole includes a plurality of 1 st ventilation holes formed in the front and rear portions of the frame body, respectively, and the rib is formed around the entire periphery of each of the 1 st ventilation holes. In this case, the ventilation in the front-rear direction during forward travel and backward travel of the unmanned aerial vehicle becomes good, and the reduction in the rigidity of the frame due to the provision of the 1 st ventilation hole can be suppressed.

Further, it is preferable that the 1 st hole portion includes a 2 nd vent hole opposed to the opening of the frame main body, and the rib is formed over the entire circumference of the 2 nd vent hole. In this case, the ventilation during the movement of the unmanned aerial vehicle becomes good, and the reduction in the rigidity of the frame due to the provision of the 2 nd ventilation hole can be suppressed.

Preferably, the frame body further includes a wing mounting portion integrally formed on an outer peripheral surface thereof for mounting a wing portion of the unmanned aerial vehicle. In this case, the wing attachment portion is integrally formed on the outer peripheral surface of the frame body, whereby the number of components for attaching the wing to the frame body can be further reduced.

Preferably, the flange portion is formed so that a portion corresponding to the wing mounting portion is wider than other portions. In this case, the rigidity of the frame in the vicinity of the wing attachment portion to which a relatively large stress or load is applied can be increased.

Further, preferably, the wing mounting portion includes: a 2 nd recess recessed inward of the frame body in an outer peripheral surface of the frame body except for an edge portion of the opening side of the frame body; a rib-shaped mounting part body integrally formed with the frame body in the 2 nd recess. In this case, by providing the 2 nd recessed portion recessed inward on the outer peripheral surface of the frame body and forming the rib-like mounting portion main body integrally with the frame body in the 2 nd recessed portion, the rigidity of the wing mounting portion can be further increased, and the mounting portion main body of the wing mounting portion can be suppressed from protruding outward beyond the edge portion on the opening side of the frame body.

Further preferably, the mounting portion further includes a reinforcing member provided to the mounting portion main body. In this case, the rigidity of the wing attachment portion can be further increased.

Preferably, a pair of wing attachment portions are provided on the outer peripheral surface of the frame body so as to sandwich a portion for housing the power source in the 1 st recess of the frame body. In this case, since the wing mounting portion is separated from the power source housed in the 1 st recess of the frame body, it becomes easy to acquire the power source housed in the 1 st recess of the frame body.

Further, it is preferable that the 1 st recess of the frame body is provided so that the power source can be disposed obliquely to a straight line connecting centers of the 1 st vent hole formed in the front portion and the 1 st vent hole formed in the rear portion. In this case, a large amount of ventilation air can be efficiently supplied to the power source housed in the 1 st recess of the frame, and the cooling effect of the power source can be increased.

Here, the "center of the 1 st vent hole" can be obtained, for example, as a midpoint of a line segment connecting the left end and the right end of the 1 st vent hole.

Further preferably, the 1 st ventilation hole formed in the front portion and the 1 st ventilation hole formed in the rear portion are provided on the left and right sides with respect to the center in the width direction of the frame body, respectively, and the 1 st recess portion of the frame body is provided, so that the power source can be disposed on the left and right sides with respect to the center in the width direction of the frame body, respectively. In this case, the cooling effect of the plurality of power sources can be maintained well, and the bias of the load distribution applied to the frame can be suppressed.

Preferably, the 1 st recess of the frame body is provided so that the 2 power sources can be arranged in a figure eight shape in which the distance between the front portions is smaller than the distance between the rear portions or the distance between the front portions is larger than the distance between the rear portions. In this case, the cooling effect of the plurality of power sources can be maintained well, and the bias of the load distribution applied to the frame can be suppressed.

Further, it is preferable that the 1 st recess of the frame body is provided so that the electrical box can be disposed in a portion where the interval between the 2 power sources is large. In this case, the portion where the interval between the 2 power sources is large can be effectively used as the arrangement space of the electrical box, and thus the power source and the electrical box can be cooled while suppressing the size of the frame body.

More preferably, the electric box includes a light emitting portion for emitting light at a rear portion, and the frame body has a 2 nd hole portion at a rear portion thereof through which the light emitting portion can be viewed. In this case, the light emitting section can be reliably viewed from behind.

Preferably, the inner peripheral surface of the frame body is formed so that the portions of the 2 power sources having a large interval protrude inward. In this case, the passage of the ventilation wind can be narrowed in the portion where the interval between the 2 power sources is large. This allows the ventilation air to be efficiently supplied to the power source, and the cooling effect of the power source can be further increased.

Effects of the invention

According to the present invention, it is possible to obtain an unmanned aerial vehicle frame that can cope with a stress or a load generated when an unmanned aerial vehicle such as a multi-rotor vehicle operates with a small number of parts.

Drawings

Fig. 1 is a perspective view showing a multi-rotor aircraft including a frame according to an embodiment of the present invention.

Fig. 2 is a perspective view showing a state where the cover is lifted in the multi-rotor aircraft according to the embodiment of fig. 1.

Fig. 3 is a perspective view of the frame of the embodiment of fig. 1, viewed from the front and above.

Fig. 4 is a perspective view of the frame as viewed from the rear and below.

Fig. 5 is an a-a line end surface view through the centers of the 1 st vent holes formed at the front and rear of the frame.

Fig. 6 is a B-B line end view passing through the widthwise center of the frame.

Fig. 7 is a C-C wire end view through the 2 nd vent hole formed at the bottom of the frame and the mount body formed at the side of the frame.

Fig. 8 is a perspective view showing the vicinity of the wing mounting portion.

Fig. 9 is an enlarged view of a portion surrounded by a chain line in fig. 7.

Fig. 10 is a plan view showing a state where the cover portion is removed from the frame and the electrical box and 2 batteries are housed in the 1 st recess of the frame.

Fig. 11 is a perspective view of the vicinity of the wing mounting portion showing a state in which the bracket is mounted.

Fig. 12 is a perspective view showing a multi-rotor aircraft including a frame according to another embodiment of the present invention.

Fig. 13 is an end view of the line E-E through the width direction center of the frame of fig. 12.

Detailed Description

Embodiments of the present invention will be described below with reference to the drawings. Here, a case will be described in which the frame 10 according to an embodiment of the present invention is applied to the multi-rotor aircraft 1 which is an example of an unmanned aerial vehicle.

Referring to fig. 1 and 2, a multi-rotor aircraft 1 includes: a frame 10; a plurality of (2 in this embodiment) storage batteries 12; an electrical box 14; a cover portion 16; a plurality of (8 in this embodiment) airfoil portions 18; a foot assembly 20 and a spreading device 22.

Referring to fig. 3 and 4, the frame 10 has a hard-shell structure, and includes a frame main body 24, a flange portion 66 (described later), and

wing attachment portions

74a and 74b (described later). The frame body 24 has a downwardly convex shape. That is, the frame body 24 includes a front portion 26, a rear portion 28, left and

right side portions

30a, 30b, and a bottom portion 32, has an opening 34 on one surface (upper surface in this embodiment), and has a 1 st recess 36 capable of accommodating the battery 12 and the electrical box 14.

The lower portion of the widthwise central portion 38 of the rear portion 28 of the frame body 24 is formed so as to be concave inward of the frame body 24. Thus, the inner peripheral surface of the frame body 24 is formed so that the portion of the 2 batteries 12 housed therein with a large interval protrudes inward. Further, bulging

portions

40a, 40b are formed on both left and right sides of the front portion 26 of the frame body 24.

Referring to fig. 5 to 7, the frame main body 24 includes a plurality of 1

st vent holes

42a, 42b, 44a, and 44b and a 2 nd vent hole 46 as the 1 st hole for air cooling. The rear portion 28 of the frame body 24 has a 2 nd hole 48 for allowing a light emitting portion 94 (described later) of the electrical box 14 to be viewed (exposed). The 1

st ventilation holes

42a, 42b are provided on the left and right sides of the center of the frame body 24 in the width direction in the front portion 26 of the frame body 24. The 1

st ventilation holes

44a, 44b are provided on the left and right sides with respect to the center in the width direction of the frame main body 24 in the rear portion 28 of the frame main body 24, respectively. The 2 nd vent hole 46 is provided in a substantially central portion of the bottom portion 32 of the frame main body 24 so as to face the opening 34 of the frame main body 24. The 2 nd hole portion 48 is provided in the widthwise central portion 38 of the rear portion 28 of the frame main body 24. In other words, the 2 nd hole 48 is provided between the 1

st ventilation holes

44a and 44b and behind the 2 nd ventilation hole 46.

More specifically, the 1

st vent holes

42a and 42b are provided by forming protruding

concave portions

50a and 50b having a substantially trapezoidal cross section and a long transverse length so as to contract inward of the frame body 24 in the bulging

portions

40a and 40b on both the left and right sides of the front portion 26 of the frame body 24, respectively. Similarly, the 1

st ventilation holes

44a and 44b are provided by forming laterally

long recesses

52a and 52b having a substantially trapezoidal cross section and protruding so as to be contracted inward of the frame body 24 on both the left and right sides of the rear portion 28 of the frame body 24. Further, the 2 nd vent hole 46 is provided by forming a recessed portion 54 having a substantially trapezoidal cross section and protruding so as to be contracted inward of the frame main body 24 in a substantially central portion of the bottom portion 32 of the frame main body 24. The 2 nd hole portion 48 is provided by forming a recessed portion 56 having a substantially trapezoidal cross-sectional shape and a horizontally long shape protruding so as to be contracted inward of the frame body 24 in an upper portion of the widthwise central portion 38 of the rear portion 28 of the frame body 24.

Ribs

58a, 58b, 60a, and 60b are formed so as to protrude into the frame body 24 over the entire periphery of the 1

st ventilation holes

42a, 42b, 44a, and 44b, respectively. The rib 62 is formed so as to protrude into the frame main body 24 over the entire periphery of the 2 nd ventilation hole 46. The rib 64 is formed so as to protrude into the frame body 24 over the entire periphery of the 2 nd hole portion 48.

A flange portion 66 is formed integrally with the frame body 24 over the entire circumference on the opening 34 side of the frame body 24. In this embodiment, the flange portion 66 is connected to an edge portion 68 on the opening 34 side of the frame main body 24, and is integrally formed with the frame main body 24 so as to protrude (fold) inward of the frame main body 24. The flange portion 66 has a 2-layer configuration, including: a peripheral portion 70 connected to the edge portion 68; and an inner peripheral portion 72 connected with a step by being lowered at an inner peripheral edge of the outer peripheral portion 70. The flange portion 66 is formed so that the width of the portions formed on the

side portions

30a and 30b of the frame body 24 is wider than the width of the portions formed on the front portion 26 and the rear portion 28 of the frame body 24. That is, the flange portion 66 is formed so that the portion corresponding to the

wing mounting portions

74a and 74b, which will be described later, is wider than the other portions.

Referring to fig. 1 to 4, a pair of

wing attachment portions

74a, 74b are integrally formed on the outer peripheral surfaces of the left and

right side portions

30a, 30b of the frame body 24 so as to sandwich a portion for accommodating the battery 12 in the 1 st recess 36 of the frame body 24.

Referring to fig. 8, the airfoil mounting portion 74a includes a 2

nd recess

76a and 2 mounting

portion bodies

78a, 80 a. The 2 nd recessed portion 76a is formed in an outer peripheral surface of the side portion 30a of the frame main body 24 so as to be recessed inward, except for the edge portion 68 on the opening 34 side of the frame main body 24. The mounting

portion bodies

78a, 80a are integrally formed with the frame body 24 in a rib shape in the 2 nd recess 76 a.

A plurality of (2 in this embodiment) nuts 82 are provided in the front portion of the 2 nd recess 76a, and a plurality of (2 in this embodiment) nuts 84 are provided in the rear portion of the 2 nd recess 76 a. A nut 82 is provided on the front side of the lower surface of the mounting portion body 78a, and a plurality of (2 in this embodiment) nuts 86 are provided on the rear side. A plurality of (2 in this embodiment) nuts 86 are provided on the front side and a nut 84 is provided on the rear side of the lower surface of the mounting portion main body 80 a. The nuts 82, 84, 86 are attachment portions for wing attachment. Further, a nut 88 and a plurality of (2 in this embodiment) nuts 90 are provided on the outer peripheral surface of the side portion 30a of the frame body 24 and the vicinity thereof, below the

regressive nuts

82, 84, 86. The nuts 88 and 90 are attachment portions for attaching the leg portions. Reinforcing members 92 for mounting the wing portions 18 or the leg portions 112 are embedded in the portions where the nuts 82, 84, 86, 88, 90 are formed.

With reference to fig. 9, a structure embedded in the vicinity of the reinforcing member 92 of the mounting portion body 78a will be described.

In this embodiment, the frame body 24, the flange portion 66, and the

wing attachment portions

74a, 74b are formed as a single member made of Carbon Fiber Reinforced Plastic (CFRP), and include 4 layers of carbon fiber cloth. In this case, as shown in fig. 9, the reinforcing member 92 is formed as an insert having its periphery covered with 2 layers of carbon fiber cloth. The reinforcing member 92 is formed of, for example, a phenolic plastic, and in the reinforcing member 92, the nut 86 is provided by insert (insert) or injection molding (outert). The material of the reinforcing member 92 is not limited to phenolic plastic, and may be other resin or metal such as aluminum. Instead of the reinforcing member 92, a layer of carbon fiber cloth may be added. The attachment portion is not limited to the nut 86, and a female screw may be directly formed on the reinforcing member 92.

The reinforcing member 92 is embedded in the other portions of the wing attachment portion 74a where the nuts 82, 84, 86 are provided, and in the portions of the outer peripheral surface of the side portion 30a of the frame body 24 and the vicinity thereof where the nuts 88, 90 are provided.

Referring to fig. 4, the airfoil mounting portion 74b includes a 2

nd recess

76b and 2 mounting

portion bodies

78b, 80 b. The wing mounting portion 74b and the wing mounting portion 74a are formed in bilateral symmetry, and the 2 nd recessed portion 76b and the mounting

body

78b, 80b are formed in the same manner as the 2 nd recessed portion 76a and the mounting

body

78a, 80a of the wing mounting portion 74a, and therefore, redundant description is omitted. Further, in the wing attachment portion 74b and the side portion 30b of the frame body 24 and the vicinity thereof, the nuts 82, 84, 86, 88, and 90 are provided, as in the wing attachment portion 74a and the side portion 30a of the frame body 24 and the vicinity thereof, and the reinforcing member 92 is embedded in the portion where the nuts 82, 84, 86, 88, and 90 are provided.

Referring to fig. 10, in the 1 st recess 36 of the frame body 24 of the

frame

10, 2 batteries 12 and the electric box 14 as power sources are housed. The batteries 12 are disposed on both the left and right sides with respect to the center in the width direction of the frame body 24. The left battery 12 is disposed obliquely to a straight line L1 connecting the centers of the 1

st vent holes

42a and 44 a. The battery 12 on the right side is disposed obliquely to a straight line L2 connecting the centers of the 1

st vent holes

42b, 44 b. That is, the left battery 12 is disposed such that the longitudinal direction M1 is not parallel to the straight line L1. The right battery 12 is disposed such that the longitudinal direction M2 is not parallel to the straight line L2. The 2 batteries 12 are arranged in a splayed shape in which the interval between the front portions is smaller than the interval between the rear portions. The electrical box 14 is disposed in a portion of the 2 batteries 12 having a large interval. In addition, in a plan view, the 2 batteries 12 and the electrical box 14 are provided so as not to overlap with the 2 nd vent hole 46. This improves ventilation through the 2 nd ventilation hole 46. In a plan view, the 2 batteries 12 are disposed on the right and left of the 2 nd vent hole 46, and the electrical box 14 is disposed behind the 2 nd vent hole 46. The electrical box 14 houses electrical components (not shown), and includes a light emitting portion 94 that emits light at the rear. The light emitting portion 94 is fitted into the rib 64 so as to be visible (exposed) from the 2 nd hole 48, and functions as a warning lamp, for example. The electrical components include, for example, a flight control panel, an Inertial Measurement Unit (IMU), a GPS antenna, and an orientation sensor.

Referring to fig. 1 to 3, the lid 16 is attached to the upper surface of the frame body 24. The lid portion 16 is fitted into the flange portion 66 of the frame body 24 so as to be in contact with the upper surface of the inner peripheral portion 72. The lid 16 is provided with 2

openings

96a and 96 b. The

openings

96a and 96b are arranged in a chevron shape similarly to the arrangement state of the 2 batteries 12. In a state where the lid 16 is covered on the frame body 24, the upper surface of the battery 12 is exposed from the

openings

96a, 96 b. Further, a vent hole 98 is provided between the

openings

96a and 96b of the lid portion 16 and at a substantially central portion of the lid portion 16.

4 wing portions 18 are mounted on the wing portion mounting portion 74 a. Each wing portion 18 includes an arm 100 and a rotor unit 102 provided at a front end portion of the arm 100. The rotor unit 102 includes an electric motor and rotor blades. In this embodiment, each rotor unit 102 is a single rotor unit.

Referring to fig. 8 and 11, in the wing attachment portion 74a, the arm 100 of the wing portion 18 extending forward is attached via the bracket 104, the arm 100 of the wing portion 18 extending rearward is attached via the bracket 106, and the arms 100 of 2 wing portions 18 extending leftward are attached via the bracket 108. The bracket 104 is fixed to the wing mounting portion 74a by screwing screws 110 into 3 nuts 82 provided in the recess 76a and the mounting portion body 78 a. The bracket 106 is fixed to the wing portion mounting portion 74a by screwing a screw 110 into 3 nuts 84 provided in the recess 76a and the mounting portion main body 80 a. The bracket 108 is fixed to the wing attachment portion 74a by screwing a screw 110 into 4 nuts 86 provided on the attachment portion

main bodies

78a, 80 a.

As in the case of the wing attachment portion 74a, the arm 100 of the wing portion 18 extending forward is attached to the wing attachment portion 74b via the bracket 106, the arm 100 of the wing portion 18 extending rearward is attached to the wing attachment portion 74b via the bracket 104, and the arms 100 of 2 wing portions 18 extending rightward are attached to the wing attachment portion 74b via the bracket 108.

When the rotation directions of the rotor units 102 of the 2 wing units 18 extending leftward are set to be opposite to each other, the rotor units substantially function as coaxial rotors (coaxial rotors). The same applies to each rotor unit 102 of 2 wing parts 18 extending rightward.

The foot unit 20 is attached to the outer peripheral surface of the frame body 24.

Referring to fig. 1 and 2, the foot assembly 20 includes: a plurality of (4 in this embodiment) leg portions 112; a pair of coupling members 114 (only 1 is shown) for coupling the adjacent 2 legs 112; and a pair of connecting members 116 (only 1 is shown) for connecting the adjacent 2 legs 114. Referring to fig. 8 and 11, the front 2 leg portions 112 are coupled to the frame main body 24 via brackets 118, respectively, and the rear 2 leg portions 112 are coupled to the frame main body 24 via brackets 120, respectively. The bracket 118 is attached to the frame body 24 by screwing a screw, not shown, into the nut 88 provided in the frame body 24. The bracket 120 is attached to the frame body 24 by screwing the screws 110 into 2 nuts 90 provided in the frame body 24.

Referring to fig. 1 and 2, a spreader 22 supported by the foot assembly 20 is provided below the frame 10. The spreading device 22 includes: a canister 122 containing a medicament; a plurality of (2 in this embodiment) arm-shaped

pipes

124a and 124 b; a plurality of (2 in this embodiment)

nozzles

126a and 126b for ejecting a medicine; and a pump 128 for pressurizing the medicine in the tank 122 to the

nozzles

126a, 126 b; and

support portions

130a and 130b for supporting the

nozzles

126a and 126 b. The tank 122 is provided below the frame body 24, and the medicine injection portion 132 of the tank 122 is located below the widthwise central portion 38 of the rear portion 28 of the frame body 24. The

pipes

124a and 124b extend in the left-right direction from both side surfaces of the tank 122. The

nozzles

126a and 126b are provided at the distal ends of the

pipes

124a and 124b, respectively. The

support portions

130a and 130b are provided to extend in the left-right direction from both sides of the tank 122, and support the

nozzles

126a and 126 b. A pump 128 is disposed below the tank 122. The medicine stored in the tank 122 is discharged downward from the

nozzles

126a and 126b through the

pipes

124a and 124 b.

According to the multi-rotor aircraft 1 including the frame 10, the flange portion 66 is formed integrally with the frame body 24 along the entire circumference of the opening 34 on the opening 34 side of the frame body 24 having the 1 st recess 36, and the frame body 24 and the flange portion 66 of the frame 10 are formed as a single member, whereby the rigidity of the frame 10 can be increased. Therefore, in the case where the frame body 24 houses the components such as the battery 12 and the electric box 14 and the wing portions 18 or the leg portions 112 are attached to configure the multi-rotor aircraft 1, even if stress is transmitted to the frame 10 via the wing portions 18 or the leg portions 112 during operations such as take-off, landing, movement, and hovering of the multi-rotor aircraft 1, and a load is applied by the weight of the components, it is possible to cope with this without damaging the frame 10 and without adversely affecting other components. In this way, stress and load generated during operation of multi-rotor aircraft 1 can be handled with a small number of components.

Since the flange portion 66 is connected to the edge portion 68 on the opening 34 side of the frame main body 24, the rigidity of the entire frame 10 and the rigidity of the edge portion 68 can be increased.

Since the flange portion 66 is provided inside the frame body 24, the frame 10 can be formed compactly without increasing its size outward.

The above-described effects can be obtained also in the multi-rotor aircraft 1a including the frame 10a shown in fig. 12.

In addition, according to multi-rotor aircraft 1, since frame body 24 includes: 1

st vent holes

42a, 42b, 44a, 44b and 2 nd vent holes 46 as 1 st hole portions for air cooling; and

ribs

58a, 58b, 60a, 60b, 62 formed around the entire periphery of these vent holes, it is possible to ensure ventilation for air-cooling the inside of the 1 st recess 36 of the frame body 24, and it is possible to suppress a decrease in the rigidity of the frame body 24 and even the frame 10 due to the provision of the 1 st hole.

Since the 1

st air holes

42a, 42b and the 1

st air holes

44a, 44b are formed in the front portion 26 and the rear portion 28 of the frame body 24, respectively, and the

ribs

58a, 58b, 60a, 60b are formed around the entire periphery of the 1

st air holes

42a, 42b, 44a, 44b, ventilation in the front-rear direction during forward traveling and backward traveling of the multi-rotor aircraft 1 becomes good, and a decrease in rigidity of the frame 10 due to the provision of the 1

st air holes

42a, 42b, 44a, 44b can be suppressed.

Since the 2 nd ventilation hole 46 is formed in the bottom portion 32 so as to face the opening 34 of the frame main body 24 and the rib 62 is formed over the entire periphery of the 2 nd ventilation hole 46, ventilation during movement of the multi-rotor aircraft 1 becomes good, and a decrease in rigidity of the frame 10 due to the provision of the 2 nd ventilation hole 46 can be suppressed. In particular, the 2 nd vent hole 46 is formed in the bottom portion 32, and the vent hole 98 is formed in the lid portion 16, whereby the ventilation in the vertical direction during circling can be made good.

By integrally forming the

wing attachment portions

74a, 74b on the outer peripheral surface of the frame body 24, the number of parts for attaching the wing portion 18 to the frame body 24 can be further reduced.

The flange portion 66 is formed so that the portion corresponding to the

wing attachment portions

74a, 74b is wider than the other portions, and thus the rigidity of the frame 10 in the vicinity of the

wing attachment portions

74a, 74b to which relatively large stress or load is applied can be increased.

By providing the 2 nd recessed

portions

76a, 76b recessed inward on the outer peripheral surface of the frame main body 24 and forming the rib-like mounting portion

main bodies

78a, 80a, 78b, 80b integrally with the frame main body 24 in the 2 nd recessed

portions

76a, 76b, the rigidity of the

wing mounting portions

74a, 74b can be further increased, and the mounting portion

main bodies

78a, 80a, 78b, 80b of the

wing mounting portions

74a, 74b can be suppressed from protruding outward from the edge portion 68 on the opening 34 side of the frame main body 24.

By providing the reinforcing members 92 to the mounting

portion bodies

78a, 80a, 78b, 80b, the rigidity of the

wing mounting portions

74a, 74b can be further increased.

By providing a pair of

wing attachment portions

74a, 74b on the outer peripheral surface of the frame body 24 so as to sandwich a portion for housing the battery 12 in the 1 st recessed portion 36 of the frame body 24, the

wing attachment portions

74a, 74b are separated from the battery 12 housed in the 1 st recessed portion 36 of the frame body 24. Therefore, it becomes easy to acquire (access) the battery 12 housed in the 1 st recess 36 of the frame body 24.

In the 1 st recess 36 of the frame body 24, the battery 12 is disposed obliquely to the straight line L1 connecting the centers of the 1 st vent hole 42a formed in the front portion 26 and the 1 st vent hole 44a formed in the rear portion 28, and the battery 12 is disposed obliquely to the straight line L2 connecting the centers of the 1 st vent hole 42b formed in the front portion 26 and the 1 st vent hole 44b formed in the rear portion 28, whereby a large amount of ventilation air can be efficiently applied to the battery 12 housed in the 1 st recess 36 of the frame 10, and the cooling effect of the battery 12 can be increased.

Since the 1

st vent holes

42a, 44a are provided on the left side and the 1

st vent holes

42b, 44b are provided on the right side with respect to the widthwise center of the frame body 24, and the batteries 12 are disposed in the 1 st recessed portion 36 of the frame body 24 on the left and right sides with respect to the widthwise center of the frame body 24, it is possible to suppress the bias of the load distribution applied to the frame 10 while maintaining the cooling effect of the plurality of batteries 12.

Since the 2 batteries 12 are arranged in the 1 st recessed portion 36 of the frame body 24 in a splayed shape in which the distance between the front portions is smaller than the distance between the rear portions, the cooling effect of the plurality of batteries 12 can be maintained well, and the bias of the load distribution applied to the frame 10 can be suppressed.

Since the electrical box 14 is disposed in the 1 st recess 36 of the frame body 24 at a portion where the interval between the 2 batteries 12 is large, the portion where the interval between the 2 batteries 12 is large is effectively utilized as the disposition space of the electrical box 14, whereby the size of the frame body 24 can be suppressed, and the batteries 12 and the electrical box 14 can be cooled together.

Since the rear portion 28 of the frame body 24 has the 2 nd hole portion 48 for allowing the light emitting portion 94 of the electrical box 14 to be viewed (exposed), the light emitting portion 94 can be reliably viewed from behind.

Since the portion of the inner peripheral surface of the frame body 24 where the interval between the 2 batteries 12 is large is formed so as to protrude inward, the passage of the ventilation air can be narrowed at the portion where the interval between the 2 batteries 12 is large. This can efficiently apply ventilation air to the battery 12, and can further increase the cooling effect of the battery 12.

Since the lower portion of the widthwise central portion 38 of the rear portion 28 of the frame body 24 is formed so as to be recessed inward of the frame body 24, it becomes easy to access the medicine injection portion 132 of the can 122.

In the above-described embodiment, the method of integrally forming the frame body 24, the flange portion 66, and the wing

portion mounting portions

74a and 74b is not limited to the integral molding, and may be a method of integrating by bonding. The same applies to the integration of the frame body 24a and the flange portion 66a in the embodiment shown in fig. 12 described later.

In the above-described embodiment, the organic wing 18 is attached to the

wing attachment portions

74a and 74b via the

brackets

104, 106, and 108, but the present invention is not limited thereto, and the wing 18 may be directly attached.

In the above embodiment, 1 st vent hole may be provided in the front portion 26 of the

frame body

24, and 2 1 st vent holes may be provided in the rear portion 28 of the frame body 24. In this case, it is preferable that 1 of the 1 st ventilation holes is provided in the center of the

front portion

26 and 1 is provided on each of the left and right sides of the rear portion 28.

In the above embodiment, the 2 batteries 12 can be arranged in the 1 st recess of the frame body in a splayed shape in which the distance between the front portions is larger than the distance between the rear portions. In this case, the cooling effect of the plurality of batteries 12 can be maintained well, and the bias of the load distribution applied to the frame can be suppressed.

In the above embodiment, the number of the batteries 12 may be 1.

Further, as in the case of the multi-rotor aircraft 1a shown in fig. 12, a frame 10a having an open lower surface may be used.

Referring to fig. 13, the frame 10a has a hard-shell structure, and includes a frame main body 24a and a flange portion 66 a. The frame body 24a has an upwardly convex shape. That is, the frame body 24a has an opening 34a on the lower surface and a 1 st recess 36a capable of storing a battery or an electric box, not shown. The flange portion 66a is formed integrally with the frame main body 24a over the entire circumference at an edge portion 68a of the frame main body 24a on the opening 34a side, and is provided on the same plane so as to be folded back toward the inside of the frame main body 24 a. A cover, not shown, is attached to the lower surface of the frame 10a, and a battery or an electric box is disposed on the cover.

According to such multi-rotor aircraft 1a including the frame 10a, the flange portions 66a are provided on the same plane, and therefore, the rigidity of the frame 10a can be further increased.

The flange portions 66 of the embodiment shown in fig. 1 may be provided on the same plane.

In the above-described embodiment, the frame (frame main body) is formed to be open on the upper surface or open on the lower surface, but is not limited thereto. The frame (frame body) may have an opening on 1 surface, and may be formed to have an opening on a side surface, for example.

In the above-described embodiment, the battery is housed in the frame body, but at least a part of the battery may be housed in the frame body.

In the above-described embodiment, the flange portion is connected to the edge portion of the opening side of the frame body, but the present invention is not limited thereto. The flange portion may be formed integrally with the frame body at a portion other than the edge portion in the opening side of the frame body.

The flange portion may be provided outside the frame body.

In the above-described embodiment, the power source is a battery, but the present invention is not limited thereto. The power source may also be an engine.

In the above-described embodiments, the case where the present invention is applied to a multi-rotor aircraft has been described, but the present invention is not limited to this. The present invention is also applicable to any unmanned aerial vehicle such as other rotary-wing aircraft or fixed-wing aircraft.

While the preferred embodiments of the present invention have been described above, it is needless to say that various modifications can be made without departing from the scope and spirit of the present invention. The scope of the invention is only limited by the scope of the appended claims.

Description of reference numerals

1. 1a multi-rotor aircraft

10. 10a frame

12 accumulator

14 electric box

18 wing part

24. 24a frame body

26 front part of the frame body

28 rear part of the frame body

30a, 30b side portions of the frame body

32 bottom of the frame body

34. 34a, 96b open

36. 36a 1 st recess

38 the width direction center part of the rear part of the frame body

42a, 42b, 44a, 44b 1 st ventilation hole

46 nd 2 nd vent hole

48 nd 2 nd hole part

58a, 58b, 60a, 60b, 62, 64 ribs

66. 66a flange portion

68. 68a edge portion

74a, 74b wing mount

76a, 76b 2 nd recess

78a, 78b, 80a, 80b mounting part body

92 reinforcing member

94 light emitting part

100 arm

112 foot part

L1 and L2 are straight lines connecting the centers of the front 1 st vent hole and the rear 1 st vent hole.

Claims

1. An unmanned aerial vehicle frame for use in an unmanned aerial vehicle having a power source, the unmanned aerial vehicle frame comprising:

a frame body having an opening on 1 surface and having a 1 st recess capable of accommodating at least a part of the power source; and

the opening side of the frame body has a flange portion formed integrally with the frame body over the entire circumference.

2. The frame for an unmanned aerial vehicle of claim 1, wherein:

the flange portion is connected to an edge portion of the opening side of the frame main body.

3. The frame for an unmanned aerial vehicle according to claim 1 or 2, wherein:

the flange portion is disposed inside the frame main body.

4. The frame for an unmanned aerial vehicle according to any one of claims 1 to 3, wherein:

the flange portions are disposed on the same plane.

5. The frame for an unmanned aerial vehicle according to any one of claims 1 to 4, wherein:

the frame body has a 1 st hole for air cooling and a rib formed on the entire circumference of the 1 st hole.

6. The frame for an unmanned aerial vehicle of claim 5, wherein:

the 1 st hole part includes a plurality of 1 st ventilation holes formed at the front and rear parts of the frame main body, respectively,

the rib is formed on the entire circumference of each 1 st vent hole.

7. The frame for an unmanned aerial vehicle of claim 5 or 6, wherein:

the 1 st hole portion includes a 2 nd vent hole opposed to the opening of the frame main body,

the rib is formed on the entire circumference of the 2 nd vent hole.

8. The frame for an unmanned aerial vehicle according to any one of claims 1 to 7, wherein:

in order to mount the wing part of the unmanned aerial vehicle, a wing part mounting part is integrally formed on the outer circumferential surface of the frame body.

9. The frame for an unmanned aerial vehicle of claim 8, wherein:

the flange portion is formed so that a portion corresponding to the wing portion mounting portion has a width wider than that of other portions.

10. The frame for an unmanned aerial vehicle of claim 8 or 9, wherein:

the wing portion mounting portion includes: a 2 nd recessed portion recessed inward of the frame body in an outer peripheral surface of the frame body except for an edge portion of the opening side of the frame body; and a rib-shaped mounting portion main body integrally formed with the frame main body in the 2 nd recess.

11. The frame for an unmanned aerial vehicle of claim 10, wherein:

the mounting portion further includes a reinforcing member provided to the mounting portion main body.

12. The frame for an unmanned aerial vehicle according to any one of claims 8 to 11, wherein:

the first concave portion 1 of the frame body is provided with a pair of wing portion attachment portions on an outer peripheral surface of the frame body so as to sandwich a portion for housing the power source.

13. The frame for an unmanned aerial vehicle of claim 6, wherein:

the 1 st recess portion, in which the frame main body is provided, may be arranged such that the power source is inclined with respect to a straight line connecting respective centers of the 1 st vent hole formed in the front portion and the 1 st vent hole formed in the rear portion.

14. The frame for an unmanned aerial vehicle of claim 13, wherein:

the 1 st vent hole formed in the front portion and the 1 st vent hole formed in the rear portion are respectively provided on the left and right sides with respect to the center in the width direction of the frame main body,

the 1 st recess portion in which the frame body is provided can be configured such that the power sources are respectively disposed on both left and right sides with respect to the center in the width direction of the frame body.

15. The frame for an unmanned aerial vehicle of claim 13 or 14, wherein:

the 1 st recess provided in the frame body may be configured such that the 2 power sources are arranged in a splayed shape in which the distance between the front portions is smaller than the distance between the rear portions or the distance between the front portions is larger than the distance between the rear portions.

16. The frame for an unmanned aerial vehicle of claim 15, wherein:

the 1 st recess provided in the frame body enables an electrical box to be disposed in a portion where the interval between the 2 power sources is large.

17. The frame for an unmanned aerial vehicle of claim 16, wherein:

the electric box includes a light emitting portion that emits light at a rear,

the rear part of the frame body has a 2 nd hole part through which the light emitting part can be viewed.

18. The frame for an unmanned aerial vehicle according to any one of claims 15 to 17, wherein:

the inner peripheral surface of the frame body is formed so that 2 portions of the power source having a large interval protrude inward.