Method for securing aircraft during transport and method for providing MaaS

Abstract

The invention relates to a method for securing an aircraft during transport and a method for providing MaaS. The method is a fixing method when a battery-driven aircraft is conveyed, and a specified part of the aircraft is connected with a moving body through a wire to fix the aircraft.

Description

Technical Field

[0001] The present disclosure relates to a method for fixing an aircraft during transportation and a method for providing MaaS. Background Art

[0002] Conventionally, the following technology has been disclosed: a power receiving device that receives power by non-contact power supply using a magnetic resonance method is provided to an aircraft, and a thrust generation mechanism that obtains thrust for flight by using the power received by the power receiving device (for example, International Publication No. 2017 / 203590).

[0003] Conventionally, there has been no research on a method for fixing an aircraft during transportation on the sea and on land for a battery-powered aircraft. That is, there is still room for improvement in the technology for transporting a battery-powered aircraft on the sea and on land. Summary of the Invention

[0004] An object of the present disclosure completed in view of the above situation is to improve the technology for transporting a battery-powered aircraft on the sea and on land.

[0005] A method for fixing a battery-powered aircraft during transportation according to an embodiment of the present disclosure is a method for fixing a battery-powered aircraft during transportation, wherein

[0006] the aircraft is fixed by connecting a specified part of the aircraft to a moving body with a thread.

[0007] According to an embodiment of the present disclosure, the technology for transporting a battery-powered aircraft on the sea and on land can be improved. Brief Description of the Drawings

[0008] Hereinafter, with reference to the drawings, the features, advantages, and technical and industrial significance of exemplary embodiments of the present invention will be described. In the drawings, the same reference numerals denote the same elements, wherein

[0009] Figure 1 is a diagram showing an outline of a method for fixing an aircraft according to an embodiment of the present disclosure.

[0010] Figure 2 is a diagram showing an aircraft fixed by a fixing method according to an embodiment of the present disclosure.

[0011] Figure 3 is a schematic diagram of a lift generation part of an aircraft according to an embodiment of the present disclosure.

[0012] Figure 4 is a schematic diagram showing a method for fixing a propeller connection part.

[0013] Figure 5It is a schematic diagram of a motor housing part and a structural component of a lift generating part of an aircraft according to an embodiment of the present disclosure. Detailed Embodiment

[0014] Hereinafter, embodiments of the present disclosure will be described.

[0015] Summary of the Embodiment

[0016] Refer to Figure 1 , and a summary of the fixing method according to the embodiment of the present disclosure will be described. The fixing method according to the embodiment of the present disclosure is a method of fixing when a moving body 1 such as a ship or a vehicle transports a battery-driven aircraft 20 on the sea or on land. Figure 1 An example of the fixing method during sea transportation is shown, and an example where the moving body 1 is a ship is shown. The moving body 1 has an accommodation area 10 for accommodating the aircraft 20. As Figure 1 shown, a plurality of aircraft 20 are accommodated in the accommodation area 10 of the moving body 1. In Figure 1 , 4 aircraft 20 are accommodated in the accommodation area 10, but the number of the accommodated aircraft 20 is not limited to this, and it can be less than 4 or 5 or more.

[0017] The aircraft 20 flies by battery drive. The aircraft 20 includes a passenger aircraft, an airplane, a helicopter, a drone, etc. For example, the aircraft 20 has a cabin approximately the same size as a passenger car that can accommodate one or more passengers, and a mechanism including one or more electric rotors for generating lift and thrust. The aircraft 20 is an eVTOL (electric Vertical TakeOff and Landing) that is at least partially maneuvered by the Visual Flight Rules (VFR). The aircraft 20 has a drive mechanism including a motor for driving the electric rotor and its control device, and a battery for supplying power to the drive mechanism. The battery is, for example, a lithium-ion battery. The aircraft 20 can also be maneuvered by the Instrument Flight Rules (IFR). In addition, the aircraft 20 has a communication function and an information processing function and is connected to a network via a mobile communication network.

[0018] First, a summary of this embodiment will be described, and the details will be described later. As Figure 1 shown, the fixing method according to the embodiment of the present disclosure fixes by connecting a specified part of the aircraft 20 to the moving body 1 with silk threads 31, silk threads 32, silk threads 33, and silk threads 34. Among them, in Figure 1In this case, each aircraft 20 is fixed by four silk threads, but it is not limited thereto. The number of silk threads for fixing each aircraft 20 may be less than four, or may be five or more.

[0019] Thus, according to this embodiment, the moving body 1 and the specified part of the aircraft 20 are connected and fixed by silk threads. Therefore, the aircraft 20 is properly positioned in the accommodation area 10 of the moving body 1. As a result, the aircraft 20 is protected from vibrations and impacts caused by shaking during transportation, acceleration and deceleration during transportation. As a result, damage, deformation, breakage, etc. of the aircraft 20 can be prevented. In this way, the marine transportation and land transportation technologies related to battery-driven aircraft can be improved.

[0020] Next, the fixing method according to the embodiment of the present disclosure will be described in detail.

[0021] Figure 2 It is a diagram showing an aircraft 20 fixed by the fixing method according to an embodiment of the present disclosure. As Figure 2 shown, the specified parts of the aircraft 20 fixed by the silk thread 31, the silk thread 32, the silk thread 33, and the silk thread 34 may be, for example, the lift generating part 21 and the lift generating part 22 of the aircraft 20. In addition, the specified part may be the axles 23 and 24 of the aircraft 20. The lift generating part 21, the lift generating part 21, the axles 23, and the axles 24 are the driving parts of the aircraft 20 and have high durability. Therefore, it is preferable to fix them by the silk thread 31, the silk thread 32, the silk thread 33, and the silk thread 34. The other ends of the silk thread 31 and the silk thread 32 are connected to the ceiling 11 of the accommodation area 10 of the moving body 1. In addition, the other ends of the silk thread 33 and the silk thread 34 are connected to the floor 12 of the accommodation area 10 of the moving body 1. Among them, in Figure 1 and Figure 2 the example shown, the aircraft 20 is suspended in the accommodation area 10. As a result, the vibration or impact from the floor 12 can be suppressed from being transmitted to the aircraft 20. In addition, the aircraft 20 may not be suspended. For example, the aircraft 20 may be in contact with the floor 12.

[0022] Figure 3It is a schematic diagram of the lift generating part 21 of the aircraft 20 according to an embodiment of the present disclosure. The lift generating part 21 of the aircraft 20 according to this embodiment includes a propeller rotating shaft 211, a propeller 212, and a propeller connecting part 213. For example, a wire 31 can be connected to the propeller rotating shaft 211. A fairing fitting part such as a wire is provided on the upper part of the propeller rotating shaft 211. The propeller rotating shaft 211 can be connected to the wire 31 using the fairing fitting part. Specifically, for example, when transporting, the fairing of the propeller rotating shaft 211 is removed, and a wire connecting component is installed at the fairing fitting part. The wire connecting component connects the end of the wire 31 on the aircraft side. Among them, the wire connecting component has a fitting part such as a wire corresponding to the fairing fitting part. In this way, the propeller rotating shaft 211 in the lift generating part 21 can be used as the specified part to which the wire is connected. Since the lift generating part 22 has the same structure, the description thereof is omitted.

[0023] The specified part fixed by the wire can also be a place other than the lift generating part 21. For example, the specified part can also be the propeller connecting part 213. When the specified part is the propeller connecting part 213, it can be fixed by clamping it from both side surfaces of the propeller connecting part 213 with a plurality of wires. Figure 4 It is a schematic diagram showing an example of the fixing method of the propeller connecting part 213. As Figure 4 shown, the propeller connecting part 213 can be fixed in a form clamped by the wire 311 and the wire 312.

[0024] The specified part of the aircraft 20 fixed by the wire can also be a part other than the lift generating part 21. Figure 5 It is a schematic diagram showing the motor housing part 214 and the structural component 215 of the lift generating part 21 of the aircraft according to an embodiment of the present disclosure. As Figure 5 shown, the lower end part of the propeller rotating shaft 211 of the lift generating part 21 is connected to the motor housing part 214. An electric rotor for generating lift and thrust is provided inside the motor housing part 214. The motor housing part 214 is provided on the structural component 215 connected to the fuselage of the aircraft 20. For example, the specified part of the aircraft 20 fixed by the wire can be the motor housing part 214. In addition, the specified part of the aircraft 20 fixed by the wire can also be the structural component 215 connecting the lift generating part 21 to the fuselage.

[0025] As described above, according to the present embodiment, a predetermined part of the aircraft 20 is connected to the moving body 1 by a wire for fixing. Therefore, the aircraft 20 is properly positioned in the accommodation area of the moving body 1. As a result, the aircraft 20 can be protected from vibrations and impacts caused by shaking during transportation, acceleration, and deceleration during transportation. As a result, damage, deformation, breakage, etc. of the aircraft 20 can be prevented. In this way, the marine transportation and land transportation technologies related to battery-driven aircraft can be improved.

[0026] The present disclosure has been described based on the respective drawings and embodiments. However, note that those skilled in the art can also make various deformations and changes based on the present disclosure. Therefore, note that these deformations and changes are included in the scope of the present disclosure. For example, the functions and the like included in each component or each step can be reconfigured in a logically consistent manner, and a plurality of components or steps can be combined into one or divided.

[0027] For example, the predetermined part of the aircraft 20 fixed by the wire may also be a ground installation part or a jack-up point. In addition, when the lift generating part of the aircraft 20 has an inclined axis, the predetermined part of the aircraft 20 fixed by the wire may also be the inclined axis.

[0028] In one example, the aircraft 20 can also be used for providing MaaS (Mobility as a Service), a service that flexibly utilizes mobility.

Claims

1. A fixing method, which is a fixing method during the conveyance of a battery-driven aircraft, wherein the fixing is performed by connecting a specified part of the aircraft to a moving body through a silk thread.

2. The fixing method according to claim 1, wherein the specified part is a lift generating part of the aircraft.

3. The fixing method according to claim 2, wherein the lift generating part is a propeller, and the specified part is a propeller rotation shaft.

4. The fixing method according to claim 3, wherein the specified part is a motor housing part of the lift generating part of the aircraft.

5. The fixing method according to claim 1, wherein the specified part is a structural component that connects the lift generating part of the aircraft to the airframe.

6. A method for providing MaaS, wherein the method for providing MaaS uses an aircraft fixed by the fixing method according to claim 1, wherein MaaS refers to Mobility as a Service.

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