WO2022180754A1

WO2022180754A1 - Aircraft and rotor blade module

Info

Publication number: WO2022180754A1
Application number: PCT/JP2021/007225
Authority: WO
Inventors: 航矢桑村; 佑中井
Original assignee: テトラ・アビエーション株式会社
Priority date: 2021-02-25
Filing date: 2021-02-25
Publication date: 2022-09-01
Also published as: WO2022180968A1; JPWO2022180968A1; JP7442907B2

Abstract

An aircraft 1 that takes off and lands vertically. The aircraft 1 comprises a fuselage 10, at least one pair of fixed wings 20–1–20–4 that extend from the fuselage 10 in the left/right direction, a plurality of first rotor blades 402–1, 402–2, a plurality of first rotating drive units, a plurality of first storage cells 405–1, 405–2, and a plurality of first cables 406–1, 406–2. The plurality of first rotor blades 402–1, 402–2 are supported by at least one pair of fixed wings 20–1–20–4 and, by being rotated and driven, generate thrust that thrusts the aircraft 1 up vertically. The plurality of first rotating drive units use power and rotate and drive each of the plurality of first rotor blades 402–1, 402–2. The plurality of first storage cells 405–1, 405–2 are fixed to at least one pair of fixed wings 20–1–20–4 and charge and discharge power. The plurality of first cables 406-1, 406-2 transmit power from the plurality of first storage cells 405-1, 405-2 to the plurality of first rotating drive units.

Description

Aircraft and rotor modules

The present invention relates to an aircraft and a rotor module.

Aircraft that perform vertical take-off and landing are known. For example, the aircraft described in Patent Document 1 includes a fuselage, a pair of fixed wings extending in the left-right direction from the fuselage, and being supported by and driven to rotate by the pair of fixed wings, so that the aircraft moves vertically upward. a plurality of rotor blades that generate a thrust to propel the rotor blades, a plurality of rotary drive units that rotate and drive the plurality of rotor blades by electric power, and a storage battery that is fixed to the fuselage and charges and discharges electric power.

WO2018/075414

The above aircraft is equipped with multiple cables that transmit power from the storage battery to multiple rotary drives. As described above, in the above aircraft, the storage battery is fixed to the fuselage and each rotor wing is supported by the fixed wing. Therefore, the distance between the storage battery and each rotary drive is relatively long. For this reason, the total length of a plurality of cables provided in an aircraft tends to be long. As a result, there is a problem that the weight of the aircraft tends to increase.

One of the purposes of the present invention is to reduce the weight.

In one aspect, the aircraft performs vertical take-off and landing.
The aircraft includes a fuselage, at least one pair of fixed wings extending in the left-right direction from the fuselage, a plurality of first rotor blades, a plurality of first rotary drive units, a plurality of first storage batteries, and a plurality of a first cable;
The plurality of first rotor blades are supported by at least one pair of fixed wings and rotationally driven to generate thrust for propelling the aircraft vertically upward.
The plurality of first rotation drive units rotationally drive the plurality of first rotor blades by electric power.
A plurality of first storage batteries are fixed to at least one pair of fixed wings and charge and discharge electric power.
The plurality of first cables transmit power from the plurality of first storage batteries to the plurality of first rotary drive units.

In another aspect, the rotor module is secured to fixed wings extending laterally from the fuselage of the aircraft.
The rotor module comprises a support, a pair of first rotors, a pair of first rotary drives, at least one first battery, and a pair of first cables.
The support extends longitudinally forward of the fixed wing and aft of the fixed wing in the longitudinal direction of the aircraft.
A pair of first rotor blades are supported by a support and positioned in front of the fixed wing and behind the fixed wing in the longitudinal direction of the aircraft. occurs.
The pair of first rotary drive units are fixed to the support and rotate the pair of first rotor blades by electric power.
At least one first storage battery is fixed to the support and positioned between the pair of first rotor blades in the longitudinal direction of the aircraft and charges and discharges electric power.
A pair of first cables respectively transmit power from the at least one first storage battery to the pair of first rotary drives.

"The weight can be reduced."

1 is a perspective view showing the configuration of an aircraft according to a first embodiment; FIG. 1 is a top view showing a schematic configuration of an aircraft according to a first embodiment; FIG. It is a block diagram showing a schematic structure of the rotary blade module of the first embodiment. It is a top view showing the schematic structure of the aircraft of 2nd Embodiment. FIG. 11 is a top view showing a schematic configuration of an aircraft according to a third embodiment; It is a top view showing the schematic structure of the aircraft of 4th Embodiment.

Hereinafter, embodiments of the aircraft and the rotor module of the present invention will be described with reference to FIGS. 1 to 6. FIG.

<First Embodiment>
(Overview)
The aircraft of the first embodiment performs vertical takeoff and landing.
The aircraft includes a fuselage, at least one pair of fixed wings extending in the left-right direction from the fuselage, a plurality of first rotor blades, a plurality of first rotary drive units, a plurality of first storage batteries, and a plurality of a first cable;
The plurality of first rotor blades are supported by at least one pair of fixed wings and rotationally driven to generate thrust for propelling the aircraft vertically upward.
The plurality of first rotation drive units rotationally drive the plurality of first rotor blades by electric power.
A plurality of first storage batteries are fixed to at least one pair of fixed wings and charge and discharge electric power.
The plurality of first cables transmit power from the plurality of first storage batteries to the plurality of first rotary drive units.

According to this, the distance between the first storage battery and the first rotor can be shortened compared to the case where the first storage battery is fixed to the body. Thereby, the length of the first cable that transmits electric power from the first storage battery to the first rotary drive section can be shortened. As a result, the weight of the aircraft can be reduced.
Next, the aircraft of the first embodiment will be described in more detail.

(Constitution)
As shown in FIGS. 1 and 2, the aircraft 1 performs vertical takeoff and landing. In this example, the aircraft 1 is an eVTOL (electric Vertical Take-Off and Landing) that flies the aircraft by electric power. The aircraft 1 flies in a vertical direction (in other words, ascends or descends in a vertical direction) in a vertical flight state (in other words, takeoff and landing state), and flies in a horizontal direction (in other words, cruises). The operating state is switched between a state of level flight (in other words, a cruising state).

In this example, each direction (for example, up-down direction, front-rear direction, or left-right direction) described below is the direction in the takeoff/landing state. Each direction may be a direction in a cruising state. The upward direction and the downward direction are the vertically upward direction and the vertically downward direction, respectively.

The aircraft 1 includes a fuselage 10, a pair of front fixed wings 20-1, 20-2, and a pair of rear fixed wings 20-3, 20-4. The number of pairs of fixed wings included in the aircraft 1 may be one, or three or more. In this example, each of the pair of front fixed wings 20-1, 20-2 and the pair of rear fixed wings 20-3, 20-4 are simply fixed wings 20-j (j is 1 to represents an integer of 4.).

The fuselage 10 extends in the front-rear direction of the aircraft 1 at the central portion in the left-right direction of the aircraft 1 . In this example, the fuselage 10 is composed of two rod-shaped or columnar bodies whose positions in the vertical direction of the aircraft 1 and positions in the longitudinal direction of the aircraft 1 are different from each other. It has shapes that are connected to each other.

In this example, the fuselage 10 has a vertically downward end face of the forward end of the aircraft 1 located vertically below the vertically downward end face of the rearward end of the aircraft 1 . In this example, the fuselage 10 has a vertically upward end face of the forward end of the aircraft 1 located vertically below the vertically upward end face of the rearward end of the aircraft 1 .

Note that the fuselage 10 may be rod-shaped or column-shaped extending in the forward direction of the aircraft 1 . For example, the fuselage 10 may have a shape (in other words, a tapered shape) at each of both ends in the longitudinal direction of the aircraft 1 that tapers toward the tip.
For example, the length of the torso 10 in the front-rear direction may be 1 m to 15 m.

A pair of front fixed wings 20-1 and 20-2 are plate-shaped and extend from the fuselage 10 to the left of the aircraft 1 and to the right of the aircraft 1, respectively. Each of the pair of front fixed wings 20-1 and 20-2 has an airfoil shape in a cross section cut by a plane perpendicular to the left-right direction of the aircraft 1. FIG.

The pair of front fixed wings 20-1 and 20-2 are plane-symmetrical to each other with respect to a plane perpendicular to the left-right direction of the aircraft 1 and passing through the center of the fuselage 10 in the left-right direction. For example, each of the pair of front fixed wings 20-1 and 20-2 may have a length of 0.5 m to 10 m in the horizontal direction.

A pair of forward fixed wings 20-1 and 20-2 are located forward of the center of the fuselage 10 in the longitudinal direction of the aircraft 1. In this example, a pair of forward fixed wings 20-1 and 20-2 are located at the ends of the fuselage 10 in the forward direction. For example, the pair of front fixed wings 20-1 and 20-2 are arranged in the longitudinal direction of the aircraft 1 from the front end of the fuselage 10 to the rear end of the pair of front fixed wings 20-1 and 20-2. has a position where the ratio of the distance to to the length of the fuselage 10 in the longitudinal direction of the aircraft 1 has a value between 0.01 and 0.4 (0.1 and 0.3 in this example).

A pair of forward fixed wings 20-1 and 20-2 are located below the center of the fuselage 10 in the vertical direction of the aircraft 1. In this example, the pair of forward fixed wings 20-1 and 20-2 are located at the ends of the fuselage 10 in the downward direction. For example, the pair of front fixed wings 20-1 and 20-2 are arranged in the vertical direction of the aircraft 1 from the lower end of the fuselage 10 to the upper end of the pair of front fixed wings 20-1 and 20-2. to the height of the fuselage 10 in the vertical direction of the aircraft 1 (in this example, the maximum height of the fuselage 10 in the vertical direction of the aircraft 1 excluding tails 11-1 and 11-2 described later) The ratio has positions with values between 0.01 and 0.4 (0.05 and 0.2 in this example).

A pair of rear fixed wings 20-3 and 20-4 are plate-shaped and extend from the fuselage 10 to the left of the aircraft 1 and to the right of the aircraft 1, respectively. Each of the pair of fixed rear wings 20-3 and 20-4 has an airfoil shape in a cross section cut by a plane perpendicular to the left-right direction of the aircraft 1. FIG.

The pair of rear fixed wings 20-3 and 20-4 are symmetrical to each other with respect to a plane perpendicular to the left-right direction of the aircraft 1 and passing through the center of the fuselage 10 in the left-right direction. The length in the left-right direction of each of the pair of rear fixed wings 20-3, 20-4 is substantially equal to the length in the left-right direction of each of the pair of front fixed wings 20-1, 20-2. In this example, the length in the left-right direction of each of the pair of rear fixed wings 20-3 and 20-4 is slightly longer than the length in the left-right direction of each of the pair of front fixed wings 20-1 and 20-2. to long. For example, each of the pair of rear fixed wings 20-3 and 20-4 may have a length of 0.5 m to 10 m in the lateral direction.

A pair of rear fixed wings 20-3 and 20-4 are positioned rearward of the center of the fuselage 10 in the longitudinal direction of the aircraft 1. In this example, the pair of rear fixed wings 20-3 and 20-4 are positioned at the rearward end of the fuselage 10. As shown in FIG. For example, the pair of fixed aft wings 20-3, 20-4 extend from the aft end of the fuselage 10 to the forward end of the pair of aft fixed wings 20-3, 20-4 in the longitudinal direction of the aircraft 1. has a position where the ratio of the distance to to the length of the fuselage 10 in the longitudinal direction of the aircraft 1 has a value between 0.01 and 0.4 (0.1 and 0.3 in this example).

A pair of rear fixed wings 20-3 and 20-4 are positioned above the center of the fuselage 10 in the vertical direction of the aircraft 1. In this example, the pair of fixed rear wings 20-3 and 20-4 are positioned at the ends of the fuselage 10 in the upward direction. For example, the pair of fixed rear wings 20-3 and 20-4 are arranged in the vertical direction of the aircraft 1 from the upper end of the fuselage 10 to the lower end of the pair of fixed rear wings 20-3 and 20-4. has a position where the ratio of the distance to to the height of the fuselage 10 in the vertical direction of the aircraft 1 is a value between 0.01 and 0.4 (0.05 and 0.2 in this example).

Thus, in this example, the aircraft 1 has two pairs of fixed wings 20-1 to 20-4 whose positions in the longitudinal direction of the aircraft 1 are different from each other and whose positions in the vertical direction of the aircraft 1 are different from each other.

The aircraft 1 includes a pair of fixed front wings 20-1, 20-2 and a pair of fixed rear wings 20-3, 20-4, and a plurality of (16 in this example) rotor blades. It has modules 40-1 to 40-16. Note that the number of rotor modules included in the aircraft 1 may be 2 to 15, or may be 17 or more. For example, the aircraft 1 may have 8, 12, 16, 20 or 24 rotor modules.

In this example, a plurality of rotor modules 40-1 to 40-16 are detachable to a pair of front fixed wings 20-1, 20-2 and a pair of rear fixed wings 20-3, 20-4. fixed to In addition, the plurality of rotor blade modules 40-1 to 40-16 are irremovably fixed to the pair of front fixed wings 20-1, 20-2 and the pair of rear fixed wings 20-3, 20-4. (For example, integrally formed).

The four rotary wing modules 40-1 to 40-4 are fixed to the front fixed wing 20-1 located on the left side of the fuselage 10 out of the pair of front fixed wings 20-1. The four rotary wing modules 40-5 to 40-8 are fixed to the front fixed wing 20-2 located on the right side of the fuselage 10 out of the pair of front fixed wings 20-1. The four rotary wing modules 40-9 to 40-12 are fixed to the rear fixed wing 20-3 located on the left side of the fuselage 10 out of the pair of rear fixed wings 20-3 and 20-4. . The four rotary wing modules 40-13 to 40-16 are fixed to the rear fixed wing 20-4 located on the right side of the fuselage 10 out of the pair of rear fixed wings 20-3 and 20-4. .

Eight rotor modules 40-1 to 40-4, 40-9 to 40-12 positioned on the left side of the fuselage 10 and eight rotor modules 40-5 to 40 positioned on the right side of the fuselage 10 -8, 40-13 to 40-16 are symmetrical to each other with respect to a plane perpendicular to the left-right direction of the aircraft 1 and passing through the center of the fuselage 10 in the left-right direction.

For example, a rotor module 40-i (i represents an integer from 1 to 16) fixed to the fixed wing 20-j rotates from the tip of the fixed wing 20-j in the lateral direction of the aircraft 1. A position where the ratio of the distance to the wing module 40-i to the length of the fixed wing 20-j in the lateral direction of the aircraft 1 is a value of 0 to 0.9 (0 to 0.8 in this example) have

In this example, four rotor blade modules 40-k to 40-l (where k is an integer of 1, 5, 9, or 13, l is an integer of k+3) are fixed to the stationary blade 20-j. ) are positioned at equal intervals in the horizontal direction of the aircraft 1 . Note that the four rotor modules 40-k to 40-l fixed to the fixed wing 20-j may have different intervals in the horizontal direction of the aircraft 1. FIG.

For example, the four rotor modules 40-k to 40-l fixed to the fixed wing 20-j are the , the ratio of the distance between two rotor modules adjacent to each other to the length of the fixed wing 20-j in the lateral direction of the aircraft 1 is 0.1 to 0.4 (0.2 to 0.2 in this example). 0.3).

In this example, the distance between two adjacent rotor modules among the four rotor modules 40-1 to 40-4 fixed to the front fixed wing 20-1 in the left-right direction of the aircraft 1 is and the distance between two adjacent rotor modules among the four rotor modules 40-9 to 40-12 fixed to the rear stationary wing 20-3 are equal to each other. Note that the distances between the two may be different from each other.

In this example, in the lateral direction of the aircraft 1, the positions of the four rotor modules 40-1 to 40-4 fixed to the front fixed wing 20-1 and the positions of the four rotor modules 40-1 to 40-4 fixed to the rear fixed wing 20-3 , and the positions of the rotor blade modules 40-9 to 40-12 coincide with each other. Note that the positions of both may be different from each other.

As shown in FIG. 3, the rotor module 40-i fixed to the stationary wing 20-j includes a support 401, a pair of first rotor blades 402-1 and 402-2, and a pair of Electric motors 403-1, 403-2, a pair of speed controllers 404-1, 404-2, a pair of first storage batteries 405-1, 405-2, a pair of first cables 406-1, 406-2, a pair of circuit protectors 407-1, 407-2, a pair of circuit switches 408-1, 408-2, a pair of controllers 409-1, 409-2, 1 a pair of first control signal lines 410-1, 410-2, a pair of second control signal lines 411-1, 411-2, a pair of third control signal lines 412-1, 412-2, Prepare.

The support 401 extends forwardly of the fixed wing 20-j and rearwardly of the fixed wing 20-j in the longitudinal direction of the aircraft 1 (in other words, when the aircraft 1 is viewed in the vertical direction). It is rod-shaped or column-shaped extending in the front-rear direction. The support 401 is detachably fixed to the fixed wing 20-j at the central portion in the longitudinal direction of the aircraft 1. As shown in FIG.

In this example, the support 401 is positioned below the fixed wing 20-j. According to this, since the center of gravity of the aircraft 1 can be positioned downward, even if the attitude of the aircraft changes, the change can be quickly suppressed. Note that the support 401 may be positioned above the fixed wing 20-j.

Each of the pair of first rotor blades 402-1 and 402-2 is rotatably supported by support 401 so that the central axis of rotation extends in a direction whose main component is the vertical direction of aircraft 1. be. The pair of first rotor blades 402-1 and 402-2 are rotationally driven by the pair of electric motors 403-1 and 403-2, respectively, to generate thrust for propelling the aircraft 1 upward.

The pair of first rotor blades 402-1 and 402-2 are positioned in front of the fixed wing 20-j and behind the fixed wing 20-j in the longitudinal direction of the aircraft 1, respectively. In this example, the pair of first rotor blades 402-1 and 402-2 are located at both ends of the support 401 in the longitudinal direction of the aircraft 1, respectively.

The pair of first rotor blades 402-1, 402-2 are fixed wing 20 in the longitudinal direction of aircraft 1, the distance between the pair of first rotor blades 402-1, 402-2 in the longitudinal direction of aircraft 1. It may have positions where the ratio of -j to length is a value between 1.2 and 4.5 (2 and 3 in this example).

In this example, the pair of first rotor blades 402-1 and 402-2 rotate in different directions.
In this example, the two first rotor blades 402-1 adjacent in the left-right direction of the aircraft 1 have different rotational directions, and the two first rotor blades 402-1 adjacent in the left-right direction of the aircraft 1 2 differ from each other in the direction of rotation. Also, in this example, the two first rotor blades 402-1 and 402-2 that are adjacent in the vertical direction of the aircraft 1 rotate in different directions.
In this example, the first rotor blades 402-1, 402-2 may be referred to as rotors.

Hereinafter, the configuration for rotationally driving the first rotor blade 402-1 (in this example, the electric motor 403-1, the speed controller 404-1, the first storage battery 405-1, the first cable 406-1, the circuit protector 407-1, circuit switch 408-1, controller 409-1, first control signal line 410-1, second control signal line 411-1, and third control signal line 412-1). . In addition, the configuration for rotationally driving the first rotor blade 402-2 (in this example, the electric motor 403-2, the speed controller 404-2, the first storage battery 405-2, the first cable 406-2, the circuit protector 407-2, circuit switch 408-2, controller 409-2, first control signal line 410-2, second control signal line 411-2, and third control signal line 412-2) are connected to the first Since it will be described in the same manner as the configuration for rotationally driving the rotor blade 402-1, the description will be omitted.

In this example, speed controller 404-1, first battery 405-1, first cable 406-1, circuit protector 407-1, circuit switch 408-1, and controller 409-1 are It is housed inside 401 . At least part of the electric motor 403-1 may also be housed inside the support 401. FIG.

The electric motor 403-1 rotates the first rotor blade 402-1 according to the power supplied from the speed controller 404-1.

Speed controller 404-1 rotates first rotor blade 402-1 rotationally driven by electric motor 403-1 according to a control signal transmitted from controller 409-1 through second control signal line 411-1. The electric power supplied to the electric motor 403-1 is controlled so as to control the speed (in other words, the number of revolutions).

In this example, the speed controller 404-1 may be represented as an ESC (Electric Speed Controller).
In this example, the electric motor 403-1 and the speed controller 404-1 correspond to the first rotary drive section.

The first storage battery 405-1 charges and discharges power. In this example, the first storage battery 405-1 includes a plurality of single cells (in other words, cells) connected in series. In this example, the first battery 405-1 has a voltage between 24V and 120V.

The first storage battery 405-1 is fixed to the support 401. In this example, the first storage battery 405-1 is positioned between the pair of first rotors 402-1 and 402-2 in the longitudinal direction of the aircraft 1. FIG. For example, the first storage battery 405-1 is located in the center of the support 401 in the longitudinal direction of the aircraft 1. FIG. In this example, first battery 405-1 is located below fixed wing 20-j. First storage battery 405-1 may be positioned between first rotor 402-1 and fixed wing 20-j in the longitudinal direction of aircraft 1. FIG.

For example, the ratio of the total weight of all (thirty-two in this example) first storage batteries 405-1 and 405-2 included in the aircraft 1 to the maximum takeoff weight of the aircraft 1 is 0.05 to 0.18. (0.12 in this example). For example, the total weight of all (32 in this example) first storage batteries 405-1 and 405-2 provided in aircraft 1 may be 6 kg to 540 kg (53 kg in this example).

The first cable 406-1 transmits power from the first storage battery 405-1 to the speed controller 404-1. A first cable 406 - 1 is fixed to the support 401 . For example, the first cable 406-1 has an allowable current of 20A to 250A (100A in this example). Also, for example, the first cable 406-1 has a weight of 4.5 g to 450 g (50 g to 71 g in this example) per meter.

The circuit protector 407-1 is located between the speed controller 404-1 and the first storage battery 405-1 in the first cable 406-1. Circuit protector 407-1 interrupts the current flowing through first cable 406-1 when the current flowing through first cable 406-1 exceeds a predetermined threshold. In this example, circuit protector 407-1 may be represented as a power fuse.

The circuit switch 408-1 is connected between the speed controller 404-1 and the first storage battery 405-1 in the first cable 406-1 (in this example, the circuit protector 407-1 and the speed controller 404 -1). The circuit switch 408-1 is in an ON state allowing current to flow through the first cable 406-1 according to the control signal transmitted from the controller 409-1 through the third control signal line 412-1; The operating state switches between an OFF state that prohibits current from flowing through first cable 406-1 (in other words, cuts off the current flowing through first cable 406-1). In this example, circuit breaker 408-1 is a contactor.

The controller 409-1 controls the speed controller 404-1 and the circuit switch 408-1 according to control signals transmitted through the first control signal line 410-1 from the controller 16, which will be described later. do.

With such a configuration, the aircraft 1 can fly above the aircraft 1 from the pair of first rotor blades 402-1 and 402-2 provided in each of the plurality of rotor blade modules 40-1 to 40-16. Vertical take-off and landing are performed by the thrust that propels it in the direction.

The fuselage 10 has an internal space that accommodates objects to be transported. In this example, the internal space is located between a pair of front fixed wings 20-1, 20-2 and a pair of rear fixed wings 20-3, 20-4 in the longitudinal direction of the aircraft 1. . For example, the internal space is located in the center of the aircraft 1 in the longitudinal direction.

Transportation targets include at least one of people and objects. For example, a person included in a transport object may be designated as a passenger. For example, passengers may fly the aircraft 1 . Also, when the aircraft 1 is configured to fly by autopilot, the passengers do not need to operate the aircraft 1 . For example, the objects included in the transport object are cargo or luggage.

For example, the interior space of fuselage 10 may accommodate one to five passengers. In this example, the interior space of the fuselage 10 can accommodate one or two passengers.
For example, the maximum takeoff weight of the aircraft 1 may be between 120 kg and 3000 kg. In this example, the maximum takeoff weight of the aircraft 1 is between 150 kg and 460 kg. The body 10 includes a door (cowl in this example) that can open and close the accommodation space.

As shown in FIG. 2, the fuselage 10 includes a pair of tail wings 11-1 and 11-2, a second rotor 12, a second rotary drive unit 13, a second storage battery 14, and a second cable. 15 , a control device 16 , a third storage battery 17 , and a third cable 18 . The number of tail wings included in the fuselage 10 may be one, or three or more.

A pair of tail wings 11-1 and 11-2 are located at the ends of the fuselage 10 in the rearward direction. The pair of tails 11-1 and 11-2 have components in the upward direction of the aircraft 1 and in the left-right direction of the aircraft 1, and as they go upwards of the aircraft 1, they It has a plate shape extending from the body 10 in a direction in which the distance increases. The pair of tails 11-1 and 11-2 are symmetrical to each other with respect to a plane perpendicular to the left-right direction of the aircraft 1 and passing through the center of the fuselage 10 in the left-right direction.

The second rotor blade 12 is rotatably supported by the fuselage 10 so that the central axis of rotation extends in a direction whose main component is the longitudinal direction of the aircraft 1 . The second rotor blade 12 is rotationally driven by the second rotary drive section 13 to generate a thrust that propels the aircraft 1 forward.

With such a configuration, the aircraft 1 has the thrust generated by the second rotor 12 that propels the aircraft 1 forward, the pair of front fixed wings 20-1 and 20-2, and the pair of rear It flies horizontally due to the lift generated by the fixed wings 20-3 and 20-4.

In this example, the second rotor blade 12 is located at the rearward end of the fuselage 10 . Note that the second rotor blade 12 may be positioned at a portion other than the rear end of the body 10 (for example, the front end of the body 10, or the center of the body 10 in the longitudinal direction). .

Note that the number of the second rotor blades 12 included in the body 10 may be two or more. In this case, for example, the plurality of second rotor blades 12 may be positioned at both the forward end of the fuselage 10 and the rearward end of the fuselage 10, or may be positioned at only one of them. may be located. Also, for example, the plurality of second rotor blades 12 are positioned on at least one of the pair of front fixed blades 20-1, 20-2 and the pair of rear fixed blades 20-3, 20-4. may
In this example, the second rotor 12 may be represented as a propeller.

The second rotation driving section 13 rotates the second rotor blade 12 according to the electric power supplied from the second storage battery 14 . In this example, the second rotary drive 13 comprises a speed controller and an electric motor, like the first rotary drive.

The second storage battery 14 charges and discharges power. In this example, the second storage battery 14 includes a plurality of cells connected in series. The second storage battery 14 has a higher voltage than the first storage batteries 405-1 and 405-2. In this example, the second battery 14 has a voltage that is between 48V and 400V higher than the first batteries 405-1 and 405-2.

A second storage battery 14 is fixed to the body 10 . In this example, the second storage battery 14 is located between the pair of front fixed wings 20-1, 20-2 and the pair of rear fixed wings 20-3, 20-4 in the longitudinal direction of the aircraft 1. To position. For example, the second storage battery 14 is positioned in the central portion of the body 10 in the front-rear direction.
Note that the number of second storage batteries 14 included in the body 10 may be two or more.

For example, the ratio of the weight of the second storage battery 14 to the maximum takeoff weight of the aircraft 1 may be a value between 0.05 and 0.18 (0.12 in this example). For example, the weight of the second storage battery 14 may range from 6 kg to 540 kg (53 kg in this example).

The second cable 15 transmits power from the second storage battery 14 to the second rotation drive section 13 . A second cable 15 is fixed to the body 10 . For example, the second cable 15 has an allowable current of 5A to 450A. In this example, the second cable 15 has a larger allowable current than the first cables 406-1 and 406-2. For example, the second cable 15 has an allowable current of 200A. Further, for example, the second cable 15 has a weight of 4.5 g to 450 g (180 g to 200 g in this example) per meter.

The control device 16 controls the aircraft 1 by operating with electric power. The control device 16 includes electronic equipment that acquires information representing the state of the aircraft 1 (eg, altitude, longitude, latitude, speed, etc.). In this example, controller 16 includes avionics (eg, communication equipment, navigation systems, flight management systems, etc.).

In this example, the control device 16 generates control signals according to the maneuvers of the passenger, and based on the generated control signals, the first rotor blades 402-1, 402-1, and 402-1 of the plurality of rotor blade modules 40-1 to 40-16 are controlled. 402-2 and the rotation speed of each of the second rotor blades 12 are controlled.

The third storage battery 17 charges and discharges power. In this example, the third storage battery 17 includes a plurality of cells connected in series. In this example, the third battery 17 has the same voltage as the first batteries 405-1 and 405-2. Note that the third storage battery 17 may have a higher voltage than the first storage batteries 405-1 and 405-2.

The third storage battery 17 is fixed to the body 10. In this example, the third storage battery 17 is located between the pair of front fixed wings 20-1, 20-2 and the pair of rear fixed wings 20-3, 20-4 in the longitudinal direction of the aircraft 1. To position. For example, the third storage battery 17 is positioned in the central portion of the body 10 in the front-rear direction.

For example, the ratio of the weight of the third storage battery 17 to the maximum takeoff weight of the aircraft 1 may be a value between 0.001 and 0.1 (0.015 in this example). For example, the third storage battery 17 may have a weight of 0.12 kg to 300 kg (6.6 kg in this example).

The third cable 18 transmits power from the third storage battery 17 to the control device 16 . A third cable 18 is fixed to the fuselage 10 . For example, the third cable 18 has an allowable current of 5A to 95A. In this example, the third cable 18 has a smaller allowable current than the first cables 406-1 and 406-2. For example, the third cable 18 has an allowable current of 7A. Further, for example, the third cable 18 has a weight of 2 g to 160 g (3 g to 10 g in this example) per meter.

(motion)
Next, operation of the aircraft 1 will be described.
First, passengers board the interior space of the fuselage 10 from the left side of the aircraft 1 through between the front fixed wing 20-1 and the rear fixed wing 20-3. Passengers may board the interior space of the fuselage 10 from the right side of the aircraft 1 through between the front fixed wing 20-2 and the rear fixed wing 20-4.

Next, the aircraft 1 rotates each of the 16 pairs of first rotor blades 402-1 and 402-2 provided in the 16 rotor blade modules 40-1 to 40-16. This generates a thrust that propels the aircraft 1 upward. As a result, the aircraft 1 takes off by flying vertically upward (in other words, ascending).

After that, the aircraft 1 drives the second rotor 12 to rotate. This generates a thrust that propels the aircraft 1 forward. As a result, the pair of front fixed wings 20-1, 20-2 and the pair of rear fixed wings 20-3, 20-4 generate lift. Next, the aircraft 1 stops rotating the 16 pairs of first rotor blades 402-1 and 402-2 provided in the 16 rotor blade modules 40-1 to 40-16, respectively. As a result, the aircraft 1 flies horizontally (in other words, cruises).

After that, the aircraft 1 rotates each of the 16 pairs of first rotor blades 402-1 and 402-2 respectively provided in the 16 rotor blade modules 40-1 to 40-16. This generates a thrust that propels the aircraft 1 upward. Next, the aircraft 1 stops the rotational drive of the second rotor 12 . As a result, the aircraft 1 lands by flying vertically downward (in other words, descending).

As described above, the aircraft 1 of the first embodiment performs vertical takeoff and landing. The aircraft 1 includes a fuselage 10, at least one pair of fixed wings 20-1 to 20-4 extending in the left-right direction from the fuselage 10, a plurality of first rotor blades 402-1 and 402-2, a plurality of of the first rotary drive unit (in this example, a plurality of electric motors 403-1, 403-2 and a plurality of speed controllers 404-1, 404-2) and a plurality of first storage batteries 405-1, 405- 2 and a plurality of first cables 406-1, 406-2.

The plurality of first rotor blades 402-1 and 402-2 are supported by at least one pair of fixed blades 20-1 to 20-4 and are rotationally driven to generate thrust for propelling the aircraft 1 vertically upward. do.
The plurality of first rotation drive units rotate and drive the plurality of first rotor blades 402-1 and 402-2 by electric power.
A plurality of first storage batteries 405-1, 405-2 are fixed to at least one pair of fixed wings 20-1 to 20-4 and charge and discharge electric power.
The plurality of first cables 406-1, 406-2 transmit power from the plurality of first storage batteries 405-1, 405-2 to the plurality of first rotary drive units.

According to this, compared to the case where the first storage battery is fixed to the fuselage 10, the distance between the first storage battery 405-1, 405-2 and the first rotor 402-1, 402-2 is shortened. can do. This makes it possible to shorten the length of the first cables 406-1, 406-2 that transmit electric power from the first storage batteries 405-1, 405-2 to the first rotary drive unit. As a result, the weight of the aircraft 1 can be reduced.

Also, compared to the case where the first storage battery is fixed to the fuselage 10, the weight of the aircraft 1 can be distributed. As a result, for example, a change in the attitude of the aircraft 1 occurs due to a stoppage of some of the plurality of first rotor blades 402-1 and 402-2, a sudden change in wind direction, or a sudden change in wind speed. However, the fluctuation can be quickly suppressed.

By the way, in an aircraft that performs vertical take-off and landing, when the rotor blades that generate the thrust that propels the aircraft vertically upward are supported by the fixed wings, in the take-off and landing state, the stress that tends to bend the fixed wings vertically upward, A reaction force due to the rotation of the rotor blade is applied to the fixed blade. Therefore, the mechanical load on the fixed wing tends to increase. On the other hand, in the aircraft 1, since the weight is distributed, it is possible to suppress the stress that tends to bend the fixed wings 20-1 to 20-4 in the vertical upward direction during takeoff and landing. As a result, the mechanical load on the fixed wings 20-1 to 20-4 can be suppressed.

Furthermore, the aircraft 1 of the first embodiment includes a second rotor 12 that is rotationally driven to generate a thrust that propels the aircraft 1 forward, and a second rotor that rotationally drives the second rotor 12 by electric power. A drive unit 13 , a second storage battery 14 that is fixed to the body 10 and charges and discharges power, and a second cable 15 that transmits power from the second storage battery 14 to the second rotation drive unit 13 .

According to this, the first rotor blades 402-1 and 402-2 and the second rotor blade 12 can be operated independently of each other. Therefore, even if one of the first rotor blades 402-1, 402-2 and the second rotor blade 12 does not operate normally, the other can be operated normally to ensure safe flight. can be done.
Further, in aircraft 1, first storage batteries 405-1 and 405-2 are fixed to fixed wings 20-1 to 20-4, and second storage battery 14 is fixed to fuselage . Therefore, the weight of the aircraft 1 can be distributed in the horizontal direction. As a result, even if the attitude of the aircraft 1 fluctuates, the fluctuation can be quickly suppressed.

Furthermore, in the aircraft 1 of the first embodiment, at least one pair of fixed wings 20-1 to 20-4 includes two pairs of fixed wings 20-1 to 20-4 whose positions in the longitudinal direction are different from each other. A plurality of first storage batteries 405-1 and 405-2 are fixed to two pairs of fixed wings 20-1 to 20-4, respectively. The second storage battery 14 is positioned between the two pairs of fixed wings 20-1 to 20-4 in the longitudinal direction.

According to this, the plurality of first storage batteries 405-1 and 405-2 are distributed over the four fixed wings 20-1 to 20-4. Therefore, weight can be distributed in the aircraft 1 . Furthermore, the first storage batteries 405-1 and 405-2 and the second storage battery 14 have different positions in the front-rear direction. Therefore, the weight in the longitudinal direction of the aircraft 1 can be distributed. As a result, even if the attitude of the aircraft 1 fluctuates, the fluctuation can be quickly suppressed.

Furthermore, the aircraft 1 of the first embodiment includes a control device 16 that controls the aircraft 1 by operating with electric power, a third storage battery 17 that is fixed to the fuselage 10 and charges and discharges power, and a third storage battery 17 that is controlled by the third storage battery 17. and a third cable 18 for transmitting power to the device 16 .

According to this, the first rotor blades 402-1 and 402-2 and the control device 16 can be operated independently of each other. Therefore, even if the first rotor blades 402-1 and 402-2 do not operate normally, the control device 16 can be operated normally.
In aircraft 1, first storage batteries 405-1 and 405-2 are fixed to fixed wings 20-1 to 20-4, and third storage battery 17 is fixed to fuselage . Therefore, the weight of the aircraft 1 can be distributed in the horizontal direction. As a result, even if the attitude of the aircraft 1 fluctuates, the fluctuation can be quickly suppressed.

Furthermore, in the aircraft 1 of the first embodiment, at least one pair of fixed wings 20-1 to 20-4 includes two pairs of fixed wings 20-1 to 20-4 whose positions in the longitudinal direction are different from each other. A plurality of first storage batteries 405-1 and 405-2 are fixed to two pairs of fixed wings 20-1 to 20-4, respectively. The third storage battery 17 is positioned between the two pairs of fixed wings 20-1 to 20-4 in the longitudinal direction of the aircraft 1. As shown in FIG.

According to this, the plurality of first storage batteries 405-1 and 405-2 are distributed over the four fixed wings 20-1 to 20-4. Therefore, weight can be distributed in the aircraft 1 . Furthermore, the first storage batteries 405-1 and 405-2 and the third storage battery 17 have different positions in the front-rear direction. Therefore, the weight in the longitudinal direction of the aircraft 1 can be distributed. As a result, even if the attitude of the aircraft 1 fluctuates, the fluctuation can be quickly suppressed.

Furthermore, the aircraft 1 of the first embodiment includes a plurality of rotor modules 40-1 to 40-16 fixed to at least one pair of fixed wings 20-1 to 20-4. Each of the plurality of rotor blade modules 40-1 to 40-16 includes a support 401, a pair of first rotor blades 402-1 and 402-2, and a pair of first rotary drive units (in this example, A pair of electric motors 403-1, 403-2 and a pair of speed controllers 404-1, 404-2), at least one first storage battery 405-1, 405-2, and a pair of first and cables 406-1 and 406-2.

The support 401 extends in the longitudinal direction of the aircraft 1 from the front of the fixed wing 20-j to the rear of the fixed wing 20-j.
A pair of first rotor blades 402-1 and 402-2 are supported by a support 401 and positioned in front of the fixed wing 20-j and behind the fixed wing 20-j in the longitudinal direction of the aircraft 1, respectively.
A pair of first rotary drives are fixed to the support 401 .
At least one first battery 405-1, 405-2 is fixed to the support 401 and positioned between the pair of first rotors 402-1, 402-2 in the longitudinal direction of the aircraft 1. As shown in FIG.
A pair of first cables 406-1, 406-2 transmit power from at least one first storage battery 405-1, 405-2 to a pair of first rotary drives, respectively.

According to this, the thrust that propels the aircraft 1 vertically upward can be transmitted to the fixed wings 20-j while suppressing the torque in the yaw direction and the torque in the pitch direction. Furthermore, the position at which the thrust force acts on fixed wing 20-j and the position at which the weight of first storage batteries 405-1 and 405-2 act on fixed wing 20-j can be brought sufficiently close to each other. Therefore, the mechanical load on the fixed wings 20-j can be reduced.

Further, according to the rotary blade modules 40-1 to 40-16, even if the fixed positions of the rotary blade modules 40-1 to 40-16 are changed, the thrust force acts on the fixed blade 20-j. A position where the weight of first storage batteries 405-1 and 405-2 acts on fixed wing 20-j can be kept sufficiently close to each other. Therefore, the mechanical load on the fixed wings 20-j can be easily reduced.

Note that the aircraft 1 of the modified example of the first embodiment may be configured such that the second rotor blade 12 is rotationally driven by power generated by the internal combustion engine instead of or in addition to the electric power. good. Further, the aircraft 1 of the modified example of the first embodiment may have a jet engine instead of or in addition to the second rotor 12 .

Further, in the aircraft 1 of the modified example of the first embodiment, instead of or in addition to the second rotor 12, at least one of the plurality of first rotors 402-1 and 402-2 section may generate thrust that propels the aircraft 1 forward. In this case, at least some of the plurality of first rotor blades 402-1 and 402-2 may be configured to change the direction of the central axis of rotation.

Further, the aircraft 1 of the modified example of the first embodiment includes a power generation device, and the power generated by the power generation device is stored in the first storage battery 405-1, 405-2, the second storage battery 14, and the third storage battery 17. It may be configured to charge at least one.

Further, in the aircraft 1 of the modified example of the first embodiment, the number of first storage batteries included in the rotor module 40-i may be one. In this case, in rotor module 40-i, one first battery powers each of the pair of first rotary drives.
Further, in the aircraft 1 of the modified example of the first embodiment, the number of first storage batteries included in the rotor module 40-i may be three or more.

Further, in the aircraft 1 of the modified example of the first embodiment, the rotor module 40-i converts the speed controller 404-1 from the first storage battery 405-2 to the speed controller 404-1 when the power of the first storage battery 405-1 is insufficient. may be configured to supply power to the Even in this case, the length of the cable that transmits electric power from first storage battery 405-2 to speed controller 404-1 can be shortened. As a result, the weight of the aircraft 1 can be reduced.

Similarly, in the aircraft 1 of the modified example of the first embodiment, the rotor module 40-i switches from the first storage battery 405-1 to the speed controller 404-i when the power of the first storage battery 405-2 is insufficient. 2 may be configured to be powered. Even in this case, the length of the cable that transmits electric power from first storage battery 405-1 to speed controller 404-2 can be shortened. As a result, the weight of the aircraft 1 can be reduced.

Further, in the aircraft 1 of the modified example of the first embodiment, when the power of the third storage battery 17 is insufficient, the power is supplied from the second storage battery 14 to the control device 16 or the third storage battery 17. It may be configured as
Further, in the aircraft 1 of the modified example of the first embodiment, when the power of the second storage battery 14 is insufficient, the power is supplied from the third storage battery 17 to the second rotation drive unit 13 or the second storage battery 14. may be configured to be supplied.

<Second embodiment>
Next, the aircraft of the second embodiment will be explained. The aircraft of the second embodiment differs from the aircraft of the first embodiment in that a plurality of first storage batteries can be charged. The following description focuses on the points of difference. In addition, in the description of the second embodiment, the same reference numerals as those used in the first embodiment designate the same or substantially similar components.

As shown in FIG. 4 , an aircraft 1A of the second embodiment includes a power connection section 31 and a plurality (16 in this example) of fourth a cable 32;

An external power supply is connected to the power supply connection unit 31 . The power connector 31 is fixed to the body 10 . In this example, the power connection 31 is located near the control device 16 .

A plurality of fourth cables 32 transmit electric power from the power connection section 31 to 16 pairs of first storage batteries 405-1 and 405-2 respectively provided in the 16 rotor blade modules 40-1 to 40-16. Each of the multiple fourth cables 32 is fixed to the aircraft 1 .

Each of the multiple fourth cables 32 has a smaller allowable current than the first cables 406-1 and 406-2. For example, each of the plurality of fourth cables 32 has an allowable current of 5A to 95A. In this example, the fourth cable 32 has a smaller allowable current than the first cables 406-1 and 406-2. For example, the fourth cable 32 has an allowable current of 40A.

Also, each of the plurality of fourth cables 32 has a smaller weight per meter than the first cables 406-1 and 406-2. For example, each of the plurality of fourth cables 32 has a weight of 2 g to 160 g (25 g to 40 g in this example) per meter.

The aircraft 1A of the second embodiment can also achieve the same actions and effects as the aircraft 1 of the first embodiment.
Furthermore, the aircraft 1A of the second embodiment has a power supply connection section 31 to which an external power supply is connected, and power is transmitted from the power supply connection section 31 to each of the plurality of first storage batteries 405-1 and 405-2. and a plurality of fourth cables 32 having a smaller allowable current than the single cables 406-1 and 406-2.

According to this, the plurality of first storage batteries 405-1 and 405-2 can be charged without being removed from the aircraft 1A. Therefore, it is possible to reduce the trouble of charging the plurality of first storage batteries 405-1 and 405-2.

<Third Embodiment>
Next, the aircraft of the third embodiment will be explained. The aircraft of the third embodiment differs from the aircraft of the first embodiment in that it is configured so that electric power can be supplied from the third storage battery to the first storage battery when the power of the first storage battery is insufficient. there is The following description focuses on the points of difference. In addition, in the description of the third embodiment, the same or substantially similar parts are assigned the same reference numerals as those used in the first embodiment.

As shown in FIG. 5, the aircraft 1B of the third embodiment includes a plurality of (16 in this example) fifth cables 33 in addition to the configuration of the aircraft 1 of the first embodiment.

A plurality of fifth cables 33 transmit power from the third storage battery 17 to 16 pairs of first storage batteries 405-1 and 405-2 respectively provided in the 16 rotor blade modules 40-1 to 40-16. Each of the multiple fifth cables 33 is fixed to the aircraft 1 .

Each of the plurality of fifth cables 33 has the same allowable current as the first cables 406-1, 406-2 or the fourth cable 32. Also, each of the plurality of fifth cables 33 has the same weight per meter as the first cables 406-1 and 406-2 or the fourth cable 32. FIG.

The aircraft 1B of the third embodiment can also achieve the same actions and effects as the aircraft 1 of the first embodiment.
Furthermore, according to the aircraft 1B of the third embodiment, when the power of the first storage batteries 405-1 and 405-2 is insufficient, power is supplied from the third storage battery 17 to the first storage batteries 405-1 and 405-2. By doing so, the first storage batteries 405-1 and 405-2 can be charged with electric power.

In the aircraft 1B of the modified example of the third embodiment, when the power of the third storage battery 17 is insufficient, the aircraft 1B supplies power from the second storage battery 14 to the control device 16 or the third storage battery 17. It may be configured as

Further, in the aircraft 1B of the modified example of the third embodiment, when the power of the second storage battery 14 is insufficient, the power is supplied from the third storage battery 17 to the second rotation drive unit 13 or the second storage battery 14. may be configured to be supplied.

Further, in the aircraft 1B of the modified example of the third embodiment, the aircraft 1B may further include the power connection section 31 and the plurality of fourth cables 32 provided in the aircraft 1A of the second embodiment.

<Fourth Embodiment>
Next, the aircraft of the fourth embodiment will be explained. The aircraft of the fourth embodiment differs from the aircraft of the first embodiment in the number of rotor modules that the aircraft comprises. The following description focuses on the points of difference. In addition, in the description of the fourth embodiment, the same reference numerals as those used in the first embodiment designate the same or substantially similar components.

As shown in FIG. 6, the aircraft 1C of the fourth embodiment has eight rotor blades instead of the 16 rotor blade modules 40-1 to 40-16 provided in the aircraft 1 of the first embodiment. It has modules 40-1 to 40-8.

The aircraft 1C of the fourth embodiment can also achieve the same actions and effects as the aircraft 1 of the first embodiment.

It should be noted that the present invention is not limited to the above-described embodiments. For example, various modifications that can be understood by those skilled in the art may be added to the above-described embodiments without departing from the scope of the present invention.

1, 1A, 1B, 1C Aircraft 10 Fuselage 11-1, 11-2 Tail 12 Second rotor 13 Second rotary drive unit 14 Second storage battery 15 Second cable 16 Control device 17 Third storage battery 18 Third cable 20- 1, 20-2 front fixed wing 20-3, 20-4 rear fixed wing 40-1 to 40-16 rotor module 401 support 402-1, 402-2 first rotor 403-1, 403-2 electric motor 404-1, 404-2 Speed controller 405-1, 405-2 First storage battery 406-1, 406-2 First cable 407-1, 407-2 Circuit protector 408-1, 408-2 Circuit switch 409-1, 409-2 Controllers 410-1, 410-2 First control signal lines 411-1, 411-2 Second control signal lines 412-2, 412-2 Third control signal lines 31 Power connection section 32 4th cable 33 5th cable

Claims

An aircraft that performs vertical take-off and landing,
torso and
at least one pair of fixed wings extending laterally from the fuselage;
a plurality of first rotor blades that are supported by and rotationally driven by the at least one pair of fixed wings to generate a thrust that propels the aircraft vertically upward;
a plurality of first rotation drive units that rotate and drive the plurality of first rotor blades by electric power;
a plurality of first storage batteries fixed to the at least one pair of fixed wings and charging and discharging electric power;
a plurality of first cables that transmit the electric power from the plurality of first storage batteries to the plurality of first rotary drive units;
an aircraft.
An aircraft according to claim 1, wherein
a second rotor that is rotationally driven to generate a thrust that propels the aircraft forward;
a second rotary drive unit that rotates the second rotary blade by electric power;
a second storage battery fixed to the body and charging and discharging electric power;
a second cable that transmits the electric power from the second storage battery to the second rotary drive unit;
an aircraft.
An aircraft according to claim 2, wherein
The at least one pair of fixed wings includes two pairs of fixed wings whose positions in the front-rear direction are different from each other,
The plurality of first storage batteries are respectively fixed to the two pairs of fixed wings,
The aircraft, wherein the second storage battery is positioned between the two pairs of fixed wings in the longitudinal direction.
An aircraft according to any one of claims 1 to 3,
a controller that controls the aircraft by operating with electric power;
a third storage battery fixed to the body and charging and discharging electric power;
a third cable that transmits the power from the third storage battery to the control device;
an aircraft.
An aircraft according to claim 4,
The at least one pair of fixed wings includes two pairs of fixed wings whose positions in the front-rear direction are different from each other,
The plurality of first storage batteries are respectively fixed to the two pairs of fixed wings,
The aircraft, wherein the third storage battery is positioned between the two pairs of fixed wings in the longitudinal direction.
An aircraft according to any one of claims 1 to 5,
a plurality of rotor modules secured to the at least one pair of stator wings;
each of the plurality of rotor modules,
a support extending longitudinally from the front of the fixed wing to the rear of the fixed wing in the longitudinal direction of the aircraft;
a pair of said first rotors supported by said support and positioned respectively forwardly of said fixed wing and rearwardly of said fixed wing in the longitudinal direction of said aircraft;
a pair of the first rotary drive units fixed to the support;
at least one first storage battery fixed to the support and positioned between the pair of first rotor blades in the front-rear direction;
a pair of first cables respectively transmitting the power from the at least one first storage battery to the pair of first rotary drives;
an aircraft.
An aircraft according to any one of claims 1 to 6,
a power connection to which an external power source is connected;
a plurality of fourth cables that transmit power from the power supply connection portion to each of the plurality of first storage batteries and have a smaller allowable current than the first cables;
an aircraft.
A rotary wing module fixed to fixed wings extending laterally from an aircraft fuselage,
a support extending longitudinally from the front of the fixed wing to the rear of the fixed wing in the longitudinal direction of the aircraft;
1 which is supported by the support, is located in front of the fixed wing and behind the fixed wing in the longitudinal direction of the aircraft, and is rotationally driven to generate thrust for propelling the aircraft vertically upward; a pair of first rotor blades;
a pair of first rotary drive units fixed to the support and configured to rotate the pair of first rotary blades by electric power;
at least one first storage battery fixed to the support and positioned between the pair of first rotor blades in the longitudinal direction of the aircraft for charging and discharging electric power;
a pair of first cables respectively transmitting the power from the at least one first storage battery to the pair of first rotary drives;
a rotor module.