JP7112049B2 - drone - Google Patents

Description

The present invention relates to a drone equipped with a fuel cell system that supplies fuel gas from a fuel filling container.

Conventionally, a drone equipped with a fuel cell system is known (see Patent Document 1, for example). The drone of Patent Document 1 drives a propeller motor, which is a drive unit, by a fuel cell system. Hydrogen, which is fuel gas to be supplied to the fuel cell system, is filled in a hydrogen cylinder, which is a fuel filling container.

JP 2018-181576 A

However, the drone of Patent Literature 1 does not take into account damage durability of the fuel-filled container when the drone falls during flight due to malfunction of the drone or lack of fuel in the fuel-filled container.

An object of the present invention is to solve the above problems, and to obtain a drone that can ensure durability against damage to a fuel-filled container when the drone falls during flight.

[1]
A drone according to the present invention includes a fuel filling container that fills fuel gas, a fuel cell system that supplies the fuel gas from the fuel filling container, a driving unit driven by the fuel cell system, and the fuel filling container. and a cushioning material surrounding the fuel container, the cushioning material having an inner layer arranged on the side of the fuel filling container, and an outer layer arranged outside the inner layer, the inner layer being made of a material softer than the outer layer. The cushioning material has an intermediate layer disposed between the inner layer and the outer layer, and the intermediate layer is made of a material that is harder than the inner layer and softer than the outer layer. It is.
[ 2 ]
A drone according to the present invention includes a fuel filling container that fills fuel gas, a fuel cell system that supplies the fuel gas from the fuel filling container, a driving unit driven by the fuel cell system, and the fuel filling container. a surrounding cushioning material, the cushioning material having an inner layer arranged on the side of the fuel-filled container and an outer layer arranged outside the inner layer, the fuel-filled container having a cylindrical portion; The outer layer is provided only on a portion including the impact point in the circumferential direction of the cylindrical portion of the fuel filling container.
[ 3 ]
In the drone described in [1] or [2] according to the present invention, the fuel-filled container is provided with an impact monitoring display unit that changes when an impact of a predetermined value or more to the fuel-filled container is applied.
[ 4 ]
In the drone according to [ 3 ] of the present invention, the impact monitoring display section changes color when an impact equal to or greater than a predetermined value is applied to the fuel-filled container.
[ 5 ]
In the drone described in [ 3 ] or [ 4 ] according to the present invention, the impact monitoring display unit includes a manufacturer display unit representing a manufacturer, and is coated from above while attached to the fuel filling container. there is
[ 6 ]
In the drone according to any one of [1] to [ 5 ] according to the present invention, the fuel filling container is provided with a pressure reducing valve integrated valve in which the pressure reducing valve is integrated with the fuel gas supply valve.
[ 7 ]
In the drone according to [ 6 ] of the present invention, the pressure reducing valve integrated valve is attached with a one-touch coupler connected to a fuel gas supply pipe connected to the fuel cell system.
[ 8 ]
The drone according to any one of [1] to [ 7 ] according to the present invention includes a battery that drives the drive section separately from the fuel cell system.
[ 9 ]
In the drone according to [ 8 ] of the present invention, the battery has a smaller capacity than the battery capacity for normal flight, and the drive control unit determines whether the internal capacity of the fuel filling container has decreased below a predetermined amount. is a battery that drives the driving unit in response to control for emergency landing on the ground by switching from the driving of the fuel cell system .

According to the drone according to the present invention, the cushioning material surrounding the fuel filling container is provided. As a result, if the drone falls during flight, the fuel container is protected from the impact of the drop by the cushioning material. Therefore, it is possible to ensure durability against damage to the fuel container when the drone falls during flight.

1 is an external perspective view showing a drone according to an embodiment; FIG. 1 is a functional block diagram showing a drone according to an embodiment; FIG. 3 is a block diagram showing a drive control section according to the embodiment; FIG. 1 is an external view showing a fuel-filled container surrounded by cushioning materials according to an embodiment; FIG. FIG. 4 is an external view showing the fuel-filled container with a part of the cushioning material removed according to the embodiment; 1 is a schematic configuration diagram showing a fuel-filled container surrounded by cushioning materials according to an embodiment; FIG. FIG. 5 is a schematic configuration diagram showing a longitudinal section of a fuel-filled container surrounded by cushioning materials shown in FIG. 4; FIG. 5 is a schematic configuration diagram showing a modification of the fuel-filled container surrounded by the cushioning material according to the embodiment; FIG. 4 is an external view showing the fuel-filled container in a state where the shock monitoring display section can be visually observed by removing the cushioning material according to the embodiment; FIG. 4 is an external view showing the fuel-filled container in which the impact monitoring display section according to the embodiment is discolored. FIG. 4 is a graph showing the correlation between various fuel-filled containers and mean crash acceleration for safety demonstration according to an embodiment; FIG. 4 is a graph showing the correlation between various fuel-filled containers and collision energy for safety verification according to an embodiment; It is a side view which shows the horizontal fall assumption collision test of the fuel filling container which concerns on embodiment. It is a side view which shows the vertical drop assumption collision test of the fuel filling container which concerns on embodiment. It is a side view which shows the angle fall assumption collision test of the fuel filling container which concerns on embodiment. 4 is a graph showing the correlation between the fuel-filled container and its degree of damage under various conditions in a collision test according to the embodiment; 4 is a graph showing the correlation between the fuel-filled container and its durability against burst pressure under various conditions in a crash test according to the embodiment.

Embodiments are described below on the basis of the drawings. In addition, in each figure, the same reference numerals denote the same or corresponding parts, and this is common throughout the specification. Furthermore, the forms of components shown in the entire specification are merely examples and are not limited to these descriptions.

Embodiment <configuration of drone>
FIG. 1 is an external perspective view showing a drone 100 according to an embodiment. FIG. 2 is a functional block diagram showing the drone 100 according to the embodiment.

As shown in FIGS. 1 and 2, the drone 100 includes a main body 10, a fuel filling container 1, a cushioning material 2, a fuel cell system 3, a drive unit 4, a battery 5, and a drive control unit 6. , provided. Further, an operation control unit 101 separated from the drone 100 is provided.

The body 10 has legs 11 . The legs 11 safely land the drone 100 without colliding the main body 10 and the like with the ground. The leg part 11 also serves as a guard fence below the main body 10 to prevent the main body 10 from colliding.

The fuel filling container 1 is filled with fuel gas. Hydrogen gas is used as the fuel gas. The fuel gas is compressed and stored in the fuel filling container 1 . Details of the fuel filling container 1 will be described later.

A cushioning material 2 surrounds the fuel filling container 1 . The cushioning material 2 is provided to improve the mechanical strength, which is the required pressure resistance of the fuel filling container 1, and prevents the fuel filling container 1 from being damaged when the drone 100 falls. Prevent fuel gas from leaking from inside.

The fuel cell system 3 is supplied with fuel gas from the fuel filling container 1 . The fuel cell system 3 generates power with a solid molecule fuel cell or the like using hydrogen as a fuel gas and oxygen in the air. Electricity generated by the fuel cell system 3 is supplied to actuators such as the driving unit 4 or sensors (not shown).

The drive unit 4 is driven by electricity supplied from the fuel cell system 3 . The driving part 4 has a plurality of arms 41 attached to the main body 10 . It should be noted that the plurality of arms 41 may be changeable in their extending directions. The drive unit 4 has a motor 42 and a propeller 43 attached to each arm 41 . The motor 42 is driven by electricity supplied from the fuel cell system 3 . The propeller 43 rotates at a rotational speed corresponding to the rotational speed of the driven motor 42 . Each propeller 43 cooperates with other propellers 43 to cause the drone 100 to ascend, descend, move horizontally forward, backward, leftward, or rightward, or a combination thereof, or hover at a certain point in the air.

The battery 5 drives the drive unit 4 separately from the fuel cell system 3 . A lithium ion battery or the like is used as the battery 5 . The battery 5 has a capacity smaller than that required for normal flight. Here, the normal flight is a flight in which the drone 100 freely continues to fly in the air according to the operation, and has a predetermined flight time. The battery 5 switches from driving the fuel cell system 3 to emergency landing on the ground when the drive control unit 6 determines that the content of the fuel container 1 is reduced to a predetermined amount or less. is the battery that drives the The battery 5 is also used when the drive unit 4 requires a large amount of power, such as when the drone 100 takes off and climbs. The fuel cell system 3 and the battery 5 may be used together when the instantaneous force of the fuel cell system 3 is relatively weak compared to the battery 5 and the instantaneous force is required.

The drive control unit 6 receives remote control information from the operation control unit 101 via the wireless communication 7 and drives the drive unit 4 . Thereby, the drone 100 performs normal flight. Further, the drive control unit 6 uses sensors to determine whether the content of the fuel container 1 is reduced to a predetermined amount or less. The drive control unit 6 performs control for emergency landing on the ground by switching from driving the fuel cell system 3 to driving the battery 5 when it is determined that the content of the fuel container 1 is reduced below a predetermined amount.

The drive control unit 6 has a communication unit (not shown) that performs wireless communication 7 . The communication unit transmits position information and the like to the operation control unit 101 located remotely via the wireless communication 7 .

The operation control unit 101 remotely operates the drone 100 by automatic operation by a program or manual operation. The operation control unit 101 is arranged at a position away from the flying drone 100 . The operation control unit 101 receives position information from the drive control unit 6 via the wireless communication 7 and transmits remote control information. The operation control unit 101 operates and controls the flight of the drone 100 within a range in which wireless communication 7 with the drive control unit 6 is possible.

<Details of Drive Control Unit 6>
FIG. 3 is a block diagram showing the drive control section 6 according to the embodiment. The operation control unit 101 also has the same configuration. As shown in FIG. 3, the drive control unit 6 is a processing circuit having a microcomputer having a CPU, memories such as ROM and RAM, and input/output devices such as I/O ports.

<Details of Fuel Filling Container 1>
FIG. 4 is an external view showing the fuel-filled container 1 surrounded by the cushioning material 2 according to the embodiment. As shown in FIG. 4 , the entire fuel-filled container 1 mounted on the drone 100 is surrounded by the cushioning material 2 . The cushioning material 2 prevents damage to the fuel filling container 1 when the drone 100 falls. EVA (ethylene-vinyl acetate copolymer resin) or the like is used for the cushioning material 2 .

FIG. 5 is an external view showing the fuel-filled container 1 with a part of the cushioning material 2 removed according to the embodiment. As shown in FIG. 5 , the cushioning material 2 has a cushioning material body portion 21 and a cushioning material lid portion 22 . The cushioning main body 21 is a bottomed cylindrical body that is attached to the drone 100 using a fixing member 23 and accommodates the fuel filling container 1 therein. The cushioning material lid portion 22 is a bottomed cylindrical body that is connected to the cushioning material body portion 21 by a hinge portion or the like, and opens and closes the pressure reducing valve integrated valve 1a side of the fuel filling container 1 from the cushioning material body portion 21 so as to be freely exposed. . When the cushioning cover 22 is opened, the fuel container 1 can be extracted from the cushioning material 2 .

FIG. 6 is a schematic configuration diagram showing the fuel-filled container 1 surrounded by the cushioning material 2 according to the embodiment. The fuel-filled container 1 has a cylindrical portion 1e and a dome-shaped dome portion 1f, and is made of, for example, aluminum alloy or plastic. Moreover, in the fuel filling container 1, CFRP (carbon fiber reinforced resin) is wound around at least the outer periphery of the cylindrical portion 1e. CFRP (carbon fiber reinforced resin) is provided to improve the mechanical strength, which is the required pressure resistance of the fuel filling container 1 . Details of CFRP (carbon fiber reinforced resin) will be described later.

As shown in FIG. 6, the fuel filling container 1 is provided with a pressure reducing valve integrated valve 1a in which a pressure reducing valve 1c for reducing the pressure of the high pressure fuel in the fuel filling container 1 to fuel gas is integrated with the fuel gas supply valve 1b. It is A one-touch coupler 1d connected to the fuel gas supply pipe 8 connected to the fuel cell system 3 is attached to the pressure reducing valve integrated valve 1a. The one-touch coupler 1d facilitates one-touch connection between the pressure reducing valve integrated valve 1a and the receiving side coupler 8a on the fuel gas supply pipe 8 side. A receiving side coupler 8a on the side of the fuel gas supply pipe 8 and a part of the fuel gas supply pipe 8 are arranged inside the cushioning material 2 together with the fuel filling container 1 .

<Details of cushioning material 2>
FIG. 7 is a schematic configuration diagram showing a longitudinal section of the fuel-filled container 1 surrounded by the cushioning material 2 shown in FIG.

As shown in FIG. 7, the cushioning material 2 is composed of three layers, an inner layer 2a arranged on the innermost side (on the fuel filling container 1 side), an outer layer 2c arranged on the outermost side, an inner layer 2a and an outer layer 2c. and an intermediate layer 2b disposed between.

The inner layer 2a is made of, for example, EVA (ethylene-vinyl acetate copolymer resin). The intermediate layer 2b is made of, for example, aramid fiber. The outer layer 2c is made of, for example, an aluminum alloy, GFRP (glass fiber reinforced resin), CFRP (carbon fiber reinforced resin), or a mixture of GFRP (glass fiber reinforced resin) and CFRP (carbon fiber reinforced resin).

CFRP (carbon fiber reinforced resin) is a composite material in which carbon fiber is used as a reinforcing material and is impregnated with resin such as epoxy resin or modified epoxy resin to improve strength. PAN-based carbon fiber, PITCH-based carbon fiber, or the like is used. In addition, GFRP (glass fiber reinforced resin) is a composite material in which glass fiber is used as a reinforcing material and is impregnated with resin such as epoxy resin or modified epoxy resin to improve strength. E-glass fiber, quartz glass fiber, or the like is used.

In other words, the inner layer 2a is composed of the softest material among the three layers in order to absorb external impact. The outer layer 2c is made of the hardest material among the three layers in order to suppress deformation of the fuel container 1 due to external impact. The intermediate layer 2b is made of a material that is harder than the inner layer 2a and softer than the outer layer 2c in order to prevent damage to the fuel-filled container 1 when a sharp object impacts the fuel-filled container 1. ing. By forming the cushioning material 2 into three layers in this manner, the effect of improving the mechanical strength of the fuel-filled container 1 to be protected by the cushioning material 2 can be enhanced.

In order to provide the necessary mechanical strength to the fuel-filled container 1 to be protected by the cushioning material 2, the following should be taken. When the outer layer 2c is made of an aluminum alloy, the tensile strength is set to 250 MPa or more. When the outer layer 2c is made of CFRP, the tensile strength of the carbon fibers should be 3500 MPa or more, the breaking strain of the carbon fibers should be 1% or more, and the longitudinal elastic modulus of the carbon fibers should be 240 GPa or more. Further, when the outer layer 2c is made of GFRP (glass fiber reinforced resin), the tensile strength of the glass fiber is set to 1400 MPa or more.

When the outer layer 2c is made of GFRP (glass fiber reinforced resin), CFRP (carbon fiber reinforced resin), or a mixture thereof, the winding pattern to the outer periphery of the fuel container 1 is aligned with the longitudinal axis of the fuel container 1. A helical winding of ±50° or more, or a mixture of helical winding and hoop winding of ±50° or more with respect to the direction perpendicular to the In this way, by winding GFRP (glass fiber reinforced resin), CFRP (carbon fiber reinforced resin), or a mixture thereof from a plurality of directions around the fuel filling container 1, the gap in the outer layer 2c can be reduced. It is possible to enhance the effect of suppressing deformation of the fuel-filled container 1 against impact from the outside. It should be noted that the combination of helical winding and hoop winding can reduce the gaps in the outer layer 2c more than the helical winding alone, so that the above effect can be further enhanced.

In the embodiment, the cushioning material 2 is composed of three layers, the inner layer 2a, the intermediate layer 2b, and the outer layer 2c. and the outer layer 2c. By forming the cushioning material 2 into two layers in this manner, the effect of improving the mechanical strength of the fuel-filled container 1 to be protected by the cushioning material 2 can be enhanced as compared with the case of one layer.

Further, the outer layer 2c needs to be provided on the entire cylindrical portion 1e of the fuel-filled container 1 in the longitudinal direction, but it is provided only partially on the cylindrical portion 1e of the fuel-filled container 1 in the circumferential direction. good too. In that case, the outer layer is designed to protect an area of ±30° or more in the circumferential direction from the impact point, which is one of the impact points of the cylindrical portion 1e of the fuel-filled container 1, which is most likely to collide with the ground when the drone 100 falls. 2c should be provided. In this way, by providing the outer layer 2c only on a part of the cylindrical portion 1e of the fuel-filled container 1 in the circumferential direction including the impact point, the effect of protecting the fuel-filled container 1 is maintained while the cushioning material 2 can be made lighter, the weight of the drone 100 can be reduced, and the cost can be reduced.

FIG. 8 is a schematic configuration diagram showing a modification of the fuel-filled container 1 surrounded by the cushioning material 2 according to the embodiment.

In the embodiment, the cushioning material 2 is wrapped around the outer periphery of the fuel filling container 1, but the present invention is not limited to this. As shown in FIG. 8, the fuel-filled container 1 may be accommodated in the box-shaped outer layer 2c, and the inner layer 2a may be spread between the outer layer 2c and the fuel-filled container 1. A similar effect can be obtained. In addition, the shape of the outer layer 2c is not limited to a box shape, and may be a cylindrical shape or the like. Alternatively, the intermediate layer 2b instead of the inner layer 2a may be laid between the outer layer 2c and the fuel container 1, or both the inner layer 2a and the intermediate layer 2b may be laid.

<Details of Impact Monitoring Display Unit 9>
FIG. 9 is an external view showing the fuel-filled container 1 in a state in which the shock monitoring display portion 9 can be seen by removing the cushioning material 2 according to the embodiment. FIG. 10 is an external view showing the fuel-filled container 1 with the impact monitoring display section 9 discolored according to the embodiment.

As shown in FIGS. 9 and 10, the fuel-filled container 1 is provided with an impact monitoring display unit 9 that changes when the fuel-filled container 1 is impacted with a predetermined value or more. Here, the impact monitoring display portion 9 changes color when the fuel container 1 is impacted with a predetermined value or more. Only the central portion 9a in the impact monitoring display portion 9 is discolored. The discolored portions are indicated by hatching in FIG. Note that the impact monitoring display unit 9 may employ a method other than discoloration, such as swelling if the impact to the fuel container 1 is greater than or equal to a predetermined value.

The impact monitoring display section 9 includes a manufacturer display section 9b that indicates the manufacturer by displaying characters, graphics, or a combination thereof. The impact monitoring display unit 9 is coated from above while attached to the fuel filling container 1 .

<Consideration of Safety Verification of Fuel Filling Container 1>
FIG. 11 is a graph showing the correlation between various fuel-filled containers 1 and average crash acceleration for safety verification according to the embodiment. In FIG. 11, the case where the fuel-filled container 1 alone falls 3 m and collides with an angle that is a pointed portion is shown as a reference on the far left. The selection of the criteria is that there is no leakage in the cycle test of 1000 times (between 0 MPa and the maximum filling pressure of the fuel filling container 1), and the bursting pressure after the cycle test is 0, which is the minimum bursting pressure of the fuel filling container 1. It is a condition that satisfies the excessive demand of .9 times or more. Therefore, if the criteria are met, it can be said that the fuel filling container 1 is safe against dropping. When the single fuel container 1 shown to the right of the standard falls at 15 m/sec and collides with an angle that is a cusp, the average impact acceleration exceeds the standard. When the fuel-filled container 1 surrounded by the cushioning material 2 shown two to the right of the reference falls at 15 m/sec and collides with the sharp angle, the average collision acceleration is much lower than the reference. The fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100, which is the embodiment shown in the 3rd right, 4th right, and 5th right side of the reference, fell at 15 m/sec and fell at the cusp. If the vehicle collides at a certain angle, the average collision acceleration will be below the standard. In addition, in the embodiment, the average collision acceleration increases as the drone 100 is larger than the fuel-filled container 1 surrounded by the cushioning material 2 shown two to the right of the reference and as the weight of the drone 100 increases. Here, the weight applied to the fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100, which is the embodiment shown on the right side of the reference, is 10 kg. A weight of 15 kg is applied to the fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100 of the four right-side embodiments. A weight of 25 kg is applied to the fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100 of the fifth embodiment shown on the right side.

FIG. 12 is a graph showing the correlation between various fuel-filled containers 1 for safety verification according to the embodiment and energy at the time of collision. As shown in FIG. 12, the fuel-filled container 1 alone, the fuel-filled container 1 surrounded by the cushioning material 2, and the fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100 collide with each other as the weight increases in this order. The energy of time increases.

Considering the correlation of FIGS. 11 and 12, even if the fuel-filled container 1 falls on an angle and is damaged, it is necessary that the fuel-filled container 1 does not rupture. Here, the dominant factors for the degree of damage include impact velocity, the effect of the cushioning material 2 and the total weight of the drone 100 . If the safety can be proved even if these dominant factors of the degree of damage influence, it can be considered that the drone 100 of the embodiment can fly safely.

<Collision test device for fuel filling container 1>
FIG. 13 is a side view showing an assumed horizontal drop collision test of the fuel-filled container 1 according to the embodiment. FIG. 14 is a side view showing an assumed vertical drop collision test of the fuel-filled container 1 according to the embodiment. FIG. 15 is a side view showing a collision test assuming an angle drop of the fuel-filled container 1 according to the embodiment. As shown in FIGS. 13, 14 and 15, the inventors conducted a collision test using a collision test device 200 for the fuel-filled container 1. FIG.

FIG. 13 shows the state of the horizontal drop assumed collision test of the fuel filling container 1 . A collision test device 200 is provided with a vertically flat plate-like iron plate 201 . The fuel filling container 1 surrounded by the cushioning material 2 is hung by the hanging rope 203 . In this state, the collision test device 200 is pushed by the suspended fuel-filled container 1 by a pushing device or the like, and the iron plate 201 collides with the fuel-filled container 1. A collision test assumed for the horizontal drop of the fuel-filled container 1 is performed. gone. According to such a collision experiment, if the fuel-filled container 1 is suspended, the effect of friction with the ground can be ignored, and a horizontal drop can be faithfully reproduced.

FIG. 14 shows the condition of the assumed vertical drop collision test of the fuel-filled container 1 . A collision test device 200 is provided with a vertically flat plate-like iron plate 201 . The fuel filling container 1 surrounded by the cushioning material 2 is hung by the hanging rope 203 . In this state, the collision test device 200 is pushed by the suspended fuel-filled container 1 by a pushing device or the like, and the iron plate 201 collides with the fuel-filled container 1, and the collision test assumed that the fuel-filled container 1 falls vertically is performed. gone. According to such a collision experiment, if the fuel-filled container 1 is suspended, the effect of friction with the ground can be ignored, and a vertical drop can be faithfully reproduced.

FIG. 15 shows the state of the collision test assuming the angle drop of the fuel filling container 1 . A collision test device 200 is provided with a vertically flat plate-like iron plate 201 . An angle 202 that is a pointed portion is installed on the iron plate 201 . The fuel filling container 1 surrounded by the cushioning material 2 is hung by the hanging rope 203 . In this state, the collision test device 200 is pushed by the suspended fuel container 1 by a pushing device or the like, and the iron plate 201 collides with the fuel container 1, and a collision test is performed assuming that the fuel container 1 falls at an angle. gone. According to such a collision experiment, if the fuel-filled container 1 is suspended, the effect of friction with the ground can be ignored, and the angle fall can be faithfully reproduced.

As a result of the collision tests shown in FIGS. 13, 14, and 15, as discussed using FIGS. 11 and 12, the collision test assuming an angle drop of the fuel-filled container 1 in FIG. It turned out to give. Therefore, each of the fuel-filled container 1 surrounded by the cushioning material 2 and the fuel-filled container 1 surrounded by the cushioning material 2 including the weight of the three types of drones 100 is suspended by the suspension rope 203. Then, the collision test shown in FIG. 15 was performed.

(1) Collision test conditions (1.1) The collision speed was the design maximum fall speed of the drone 100 at the time of trouble, and was set to 15 m/sec in this test. The drone 100 is designed in advance so that the maximum fall speed does not exceed 15 m/sec.
(1.2) The type of test specimen to be tested is the weight of the fuel-filled container 1 surrounded by the cushioning material 2 and the weight of the drone 100 added to the weight of 10 kg, 15 kg, and 25 kg, up to 25 kg. A fuel-filled container 1 surrounded by an added cushioning material 2 was used. In the cushioning material 2, the inner layer 2a is composed of (ethylene-vinyl acetate copolymer resin) wound one turn, the intermediate layer 2b is composed of aramid fiber wound one turn, and the outer layer 2c is composed of two layers of GFRP ( glass fiber reinforced resin) and four layers of CFRP (carbon fiber reinforced resin). The outer layer 2c of the cushioning material 2 is provided over the entire cylindrical portion 1e of the fuel-filled container 1 in the longitudinal direction. It is provided only in the area of ±45° from the point.

<Results of collision test for safety of fuel filling container 1>
FIG. 16 is a graph showing the correlation between the fuel-filled container 1 and its degree of damage under various conditions in the crash test according to the embodiment. In FIG. 16, the case where the fuel-filled container 1 alone collides with the angle 202, which is a pointed portion, at a speed of falling 3 m is shown as a reference on the far left. The selection of the criteria is that there is no leakage in the cycle test of 1000 times (between 0 MPa and the maximum filling pressure of the fuel filling container 1), and the bursting pressure after the cycle test is 0, which is the minimum bursting pressure of the fuel filling container 1. It is a condition that satisfies the excessive demand of .9 times or more. Therefore, if the criteria are met, it can be said that the fuel filling container 1 is safe against dropping. When the single fuel container 1 shown to the right of the standard is pulled at 15 m/sec and collides with the sharp angle 202, the degree of damage to the fuel container 1 exceeds the standard. When the fuel-filled container 1 surrounded by the cushioning material 2 shown on the right side of the standard is pulled at 15m/sec and collides with the sharp angle 202, the degree of damage to the fuel-filled container 1 is much lower than the standard. become. Three right, four right, and five right sides of the reference show fuel-filled containers 1 surrounded by cushioning materials 2 having the same weight when mounted on the drone 100 of the embodiment. there is When the fuel-filled container 1 surrounded by the cushioning material 2 with the same weight loaded on the drone 100 is pulled at 15 m/sec and collides with the sharp angle 202, the fuel-filled container 1 falls below the standard. damage degree. Also, the degree of damage to the fuel-filled container 1 is greater as the drone 100 is larger than the fuel-filled container 1 surrounded by the cushioning material 2 shown to the right of the standard and the weight of the drone 100 increases. Here, the weight applied to the fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100, which is the embodiment shown on the right side of the reference, is 10 kg. A weight of 15 kg is applied to the fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100 of the four right-side embodiments. A weight of 25 kg is applied to the fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100 of the fifth embodiment shown on the right side.

FIG. 17 is a graph showing the correlation between the fuel-filled container 1 and its durability against bursting pressure under various conditions in the crash test according to the embodiment. In FIG. 17, the case where the fuel-filled container 1 alone collides with the angle 202, which is a pointed portion, at a speed of falling 3 m is shown as a reference on the far left. The selection of the criteria is that there is no leakage in the cycle test of 1000 times (between 0 MPa and the maximum filling pressure of the fuel filling container 1), and the bursting pressure after the cycle test is 0, which is the minimum bursting pressure of the fuel filling container 1. It is a condition that satisfies the excessive demand of .9 times or more. Therefore, if the criteria are met, it can be said that the fuel filling container 1 is safe against dropping. When the single fuel container 1 shown on the right side of the standard is pulled at 15 m/sec and collides with the angle 202, which is a pointed portion, the durability performance against the bursting pressure of the fuel container 1 becomes lower than the standard. Fracture durability is weak. When the fuel-filled container 1 surrounded by the cushioning material 2 shown on the right side of the standard is pulled at 15 m/sec and collides with the sharp angle 202, the durability performance against the bursting pressure of the fuel-filled container 1 is the standard. It is higher than that and can ensure durability against breakage. Three right, four right, and five right sides of the reference show fuel-filled containers 1 surrounded by cushioning materials 2 having the same weight when mounted on the drone 100 of the embodiment. there is When the fuel-filled container 1 surrounded by the cushioning material 2 with the same weight loaded on the drone 100 is pulled at 15 m/sec and collides with the angle 202 which is a pointed portion, the following occurs. That is, the durability against bursting pressure of the fuel-filled container 1 is lower than that of the fuel-filled container 1 surrounded by the cushioning material 2 shown on the right side of the standard. However, the durability against bursting pressure is higher than the standard. As the weight of the drone 100 increases, the durability performance decreases. Here, the weight applied to the fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100, which is the embodiment shown on the right side of the reference, is 10 kg. A weight of 15 kg is applied to the fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100 of the four right-side embodiments. A weight of 25 kg is applied to the fuel-filled container 1 surrounded by the cushioning material 2 mounted on the drone 100 of the fifth embodiment shown on the right side.

From the collision test results of FIGS. 16 and 17, it is proved that the fuel-filled container 1 surrounded by the cushioning material 2 having the same weight when mounted on the drone 100 according to the embodiment exceeds the standard damage durability performance. did it. Here, the reference damage durability performance is the damage durability performance that satisfies the excessive requirement of causing the single fuel container 1 to collide with the angle 202, which is a pointed portion, at a speed of falling 3 m.

<Effect of Embodiment>
According to an embodiment, the drone 100 comprises a fuel filling container 1 filled with fuel gas. The drone 100 comprises a fuel cell system 3 that supplies fuel gas from a fuel filling container 1 . The drone 100 comprises a driving section 4 driven by the fuel cell system 3 . The drone 100 comprises a cushioning material 2 surrounding the fuel-filled container 1 .

According to this configuration, when the drone 100 falls during flight, the fuel filling container 1 is protected from the impact of the fall by the cushioning material 2 . Therefore, it is possible to ensure the damage durability of the fuel filling container 1 when the drone 100 falls during flight.

According to the embodiment, the fuel-filled container 1 is provided with an impact monitoring display unit 9 that changes when the fuel-filled container 1 is subjected to an impact of a predetermined value or more.

According to this configuration, the impact monitoring display section 9 changes when the fuel container 1 is impacted with a predetermined value or more, so that the state where the fuel container 1 receives the impact of falling can be easily recognized.

According to the embodiment, the impact monitoring display unit 9 changes color when the fuel container 1 is impacted with a predetermined value or more.

According to this configuration, the shock monitoring display section 9 changes color when the fuel container 1 is subjected to a shock of a predetermined value or more.

According to the embodiment, the impact monitoring indicator 9 includes a manufacturer indicator 9b representing the manufacturer and is coated from above while attached to the fuel filling container 1 .

According to this configuration, since the shock monitoring display section 9 includes the manufacturer display section 9b indicating the manufacturer, it is easy to recognize that the shock monitoring display section 9 is genuine. In addition, since the impact monitoring display portion 9 is coated from above while attached to the fuel filling container 1, the impact monitoring display portion 9 is difficult to be peeled off by a third party, and the impact monitoring display portion 9 is false. Hard to replace.

According to the embodiment, the fuel filling container 1 is provided with the integrated pressure reducing valve 1a in which the pressure reducing valve 1c is integrated with the fuel gas supply valve 1b.

According to this configuration, the fuel gas can be supplied from the inside of the fuel filling container 1 in a decompressed state after circulating through the pressure reducing valve 1c, and the supply management of the fuel gas is easy.

According to the embodiment, the one-touch coupler 1d connected to the fuel gas supply pipe 8 connected to the fuel cell system 3 is attached to the pressure reducing valve integrated valve 1a.

According to this configuration, the fuel filling container 1 can be easily connected to the fuel gas supply pipe 8 using the one-touch coupler 1d, and the supply management of the fuel gas is facilitated.

According to an embodiment, the drone 100 comprises a battery 5 that drives the drive 4 separately from the fuel cell system 3 .

According to this configuration, the drone 100 has two power supply sources for driving the driving unit 4, and the flight performance of the drone 100, which may fall during flight, can be stabilized.

According to an embodiment, the battery 5 has a smaller capacity than the battery capacity for normal flight. The battery 5 switches from driving the fuel cell system 3 to emergency landing on the ground when the drive control unit 6 determines that the content of the fuel container 1 is reduced to a predetermined amount or less. is the battery that drives the

According to this configuration, when the drive control unit 6 of the drone 100 determines that the content of the fuel container 1 is reduced to a predetermined amount or less, the drive control unit 6 switches from driving the fuel cell system 3 to driving the battery 5. , the drone 100 can land on the ground in an emergency.

According to the embodiment, the buffer material 2 has an inner layer 2a arranged on the side of the fuel filling container 1 and an outer layer 2c arranged outside the inner layer 2a, and the inner layer 2a is made of a softer material than the outer layer 2c. consists of

According to this configuration, since the outer layer 2c suppresses deformation of the fuel-filled container 1 against an external impact and the inner layer 2a absorbs an external impact, the shock-absorbing material 2 protects the fuel-filled container 1, which is to be protected. It is possible to enhance the effect of improving the target strength.

According to the embodiment, the cushioning material 2 has an intermediate layer 2b arranged between the inner layer 2a and the outer layer 2c, the intermediate layer 2b being harder than the inner layer 2a and softer than the outer layer 2c. It is

According to this configuration, when an object that impacts the fuel-filled container 1 is sharp, the intermediate layer 2b prevents the fuel-filled container 1 from being damaged. The effect of improving the mechanical strength of 1 can be further enhanced.

According to the embodiment, the fuel-filled container 1 has the cylindrical portion 1e, and the outer layer 2c is provided only partially, including the impact point, in the circumferential direction of the cylindrical portion 1e of the fuel-filled container 1. .

According to this configuration, the cushioning material 2 can be lightened while maintaining the effect of protecting the fuel filling container 1, so that the weight of the drone 100 can be reduced and the cost can be reduced.

1 fuel filling container 1a decompression valve integrated valve 1b fuel gas supply valve 1c decompression valve 1d one-touch coupler 1e cylindrical portion 1f dome portion 2 cushioning material 2a inner layer 2b intermediate layer 2c outer layer 3 fuel Battery system 4 Drive unit 5 Battery 6 Drive control unit 7 Wireless communication 8 Fuel gas supply pipe 8a Receiving side coupler 9 Impact monitoring display unit 9a Central unit 9b Manufacturer display unit 10 Main unit 11 Leg Part 21 Cushioning material main body 22 Cushioning material cover 23 Fixing member 41 Arm 42 Motor 43 Propeller 100 Drone 101 Operation control unit 200 Collision test device 201 Iron plate 202 Angle 203 Suspension rope .

Claims (9)

a fuel filling container filled with fuel gas;
a fuel cell system that supplies the fuel gas from the fuel filling container;
a drive unit driven by the fuel cell system;
and a cushioning material surrounding the fuel filling container ,
The buffer material has an inner layer arranged on the side of the fuel filling container and an outer layer arranged outside the inner layer,
The inner layer is made of a softer material than the outer layer,
The cushioning material has an intermediate layer disposed between the inner layer and the outer layer,
The drone , wherein the intermediate layer is made of a material that is harder than the inner layer and softer than the outer layer . a fuel filling container filled with fuel gas;
a fuel cell system that supplies the fuel gas from the fuel filling container;
a drive unit driven by the fuel cell system;
and a cushioning material surrounding the fuel filling container,
The buffer material has an inner layer arranged on the side of the fuel filling container and an outer layer arranged outside the inner layer,
The fuel filling container has a cylindrical portion,
The drone , wherein the outer layer is provided only on a portion including the impact point in the circumferential direction of the cylindrical portion of the fuel filling container. 3. The drone according to claim 1, wherein the fuel-filled container is provided with an impact monitoring display unit that changes when an impact of a predetermined value or more on the fuel-filled container is applied. 4. The drone according to claim 3 , wherein the impact monitoring display unit changes color when an impact equal to or greater than a predetermined value is applied to the fuel container. 5. The drone according to claim 3 or 4 , wherein the impact monitoring indicator includes a manufacturer indicator representing a manufacturer, and is coated from above while attached to the fuel filling container. The drone according to any one of claims 1 to 5 , wherein the fuel filling container is provided with a pressure reducing valve integrated valve in which the pressure reducing valve is integrated with the fuel gas supply valve. 7. The drone according to claim 6 , wherein the pressure reducing valve integrated valve is attached with a one-touch coupler connected to a fuel gas supply pipe connected to the fuel cell system. The drone according to any one of claims 1 to 7 , further comprising a battery that drives the drive unit separately from the fuel cell system. The battery has a smaller capacity than the battery capacity for normal flight, and when the drive control unit determines that the internal capacity in the fuel filling container has decreased below a predetermined amount, the fuel cell system is switched from driving to an emergency. 9. The drone of claim 8 , wherein the drone is a battery that drives the drive unit in response to control to land on the ground.

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