JP2021075191A - Vertical takeoff and landing aircraft - Google Patents

Abstract

To provide a vertical takeoff and landing aircraft which effectively utilizes lift force of fixed wings, and is reduced in weight while having high strength, and therefore increases transportation efficiency, and which properly secures safety with respect to users by eliminating dangerous exposure of its rotors.SOLUTION: A vertical takeoff and landing aircraft is equipped with: a plurality of rotors 30, 30 to allow vertical takeoff and landing; and fixed wings 20 to allow a horizontal flight accompanying lift force generated by their wing shapes. The fixed wings 20 are composed of right and left biplane wings 21, 22 formed by arranging upper and lower wings 20a, 20b, that are positioned one above the other during a horizontal flight, on the right and left sides with a fuselage in the center. The right and left biplane wings 21, 22 comprise wind tip continuous parts 21a, 22a having a form that makes the upper and lower wings 20a, 20b continuous at each wing tip. Rotors 30 are arranged within right and left internal spaces 23, 24 surrounded by the fuselage 10 and the right and left biplane wings 21, 22.SELECTED DRAWING: Figure 1

Description

The present invention includes a plurality of rotors for vertical takeoff and landing, and fixed wings for horizontal flight with lift generated by the wing shape, and the fixed wings are positioned up and down during horizontal flight. It relates to a vertical take-off and landing aircraft composed of left and right compound leaf wings formed by arranging the upper and lower wings to the left and right around the fuselage.

As a conventional vertical take-off and landing aircraft, a vertical take-off and landing aircraft that allows passengers to board, take off and land, and fly horizontally is formed to be approximately the same size as a passenger vehicle, and the fuselage of the aircraft can generate lift that contributes to horizontal flight. The takeoff and landing engine and the level flight engine are provided, and the takeoff and landing engine and the level flight engine are equipped inside the upward projection contour line of the fuselage (see Patent Document 1). Proposed. This type of vertical takeoff and landing aircraft will be equipped with separate engines for takeoff and landing and for level flight, which complicates the equipment and makes it difficult to reduce the weight. Therefore, for example, when applied to a drone for transportation, it is considered that efficient transportation cannot be performed.

On the other hand, as other conventional vertical takeoff and landing aircraft, like the Osprey, a rotor device (thrust generator) is mounted and supported so that the angle with respect to the fixed wing can be changed as appropriate, and is used for takeoff and landing and horizontal flight. A device that is also used as a thrust generator (see Patent Document 2) has been proposed. According to this, it is considered to be more effective than the above-mentioned aircraft equipped with a separate engine, but the mechanism for mounting and supporting the rotor device becomes complicated and it is difficult to reduce the weight. Therefore, for example, when applied to a drone for transportation, it is considered that efficient transportation cannot be performed. Further, when applied to a drone for transportation, the propeller of the rotor device is exposed in a dangerous state, and the form does not ensure safety for the user.

Further, as another conventional vertical take-off and landing aircraft, the flight control device of the fixed-wing aircraft is connected to the first left wing and the first right wing, and the first left rotor and the first left wing. A first left swash plate connected to an electric motor and a first right swash plate connected to a first right rotor and a first right electric motor connected to a first right wing. (See Patent Document 3), which has an aircraft and is provided with elevons on the left and right wings. Further, in this vertical takeoff and landing aircraft, an aircraft in which four wings are provided in an X-type wing structure and the fuselage is in the center is also proposed. According to this, it is considered possible to simplify the structure having the required strength as compared with the above-mentioned aircraft, but when applied to a drone for transportation, for example, a rotor device such as the above-mentioned Osprey is used. The propeller of the rotor device is exposed in a dangerous state as in the case of the provided one, and it is not in a form that ensures safety for the user.

WO2013012595A1 (page 1) U.S. Pat. No. 3,181810 (page 1) Special Table 2016-517821 (1st page)

The problem to be solved for vertical takeoff and landing aircraft is that in conventional aircraft equipped with fixed wings, the mounting and support structure of the rotor device (thrust generator) tends to be complicated and it is difficult to reduce the weight. Therefore, for example, a drone for transportation. When applied to, it is difficult to transport efficiently, and the configuration does not ensure safety for users.

Therefore, an object of the present invention is that the lift of the fixed wing can be effectively used, and the weight can be reduced simply, but the transport efficiency can be improved by making the form having high strength, and the propeller of the rotor device is dangerous. The purpose of the present invention is to provide a vertical take-off and landing aircraft that can ensure safety for users by being configured so as not to be exposed to an unpleasant state.

The present invention includes the following configurations in order to achieve the above object.
According to one form of a vertical take-off and landing aircraft according to the present invention, a plurality of rotors are provided so that vertical take-off and landing can be performed, and fixed wings are provided so that horizontal flight can be performed with lift generated by the wing shape. A vertical take-off and landing aircraft composed of left and right compound-leaf wings formed by arranging left and right wings around the fuselage, which are upper and lower wings located up and down during level flight.
The left and right biplane wings are provided with a wing tip continuous portion in a form in which the upper and lower wings are continuous at each wing tip, and the left and right inner spaces surrounded by the fuselage and the left and right biplane wings are described. The rotor is arranged.

Further, according to one form of a vertical take-off and landing aircraft according to the present invention, it is possible to be characterized in that moving blades are arranged immediately below the rear of the left and right rotors.

Further, according to one form of a vertical take-off and landing aircraft according to the present invention, the rotor is driven by a drive device supported by a bridge support portion formed by being bridged between the upper and lower wings. Can be.

Further, according to a form of a vertical take-off and landing aircraft according to the present invention, the moving blades are operated by an operating mechanism supported by a bridge support portion formed by being bridged between the upper and lower wings. Can be a feature.

Further, according to one form of the vertical takeoff and landing aircraft according to the present invention, the legs for vertical takeoff and landing extend rearward at each corner of each wing tip of the left and right biplanes provided with the wing tip continuous portion. It can be characterized that it is provided in the provided form.

Further, according to a form of a vertical take-off and landing aircraft according to the present invention, the fuselage may be provided with a storage space so that luggage can be loaded.

According to the vertical take-off and landing aircraft according to the present invention, the lift of the fixed wing can be effectively used, and the weight can be reduced simply. By configuring the propeller so that it is not exposed to a dangerous state, it has a special advantageous effect that the safety for the user can be ensured.

It is a perspective view which shows the takeoff and landing state of the form example of the vertical takeoff and landing aircraft which concerns on this invention. It is a perspective view which showed the front surface, the plane, and the left side surface of the horizontal flight state of the embodiment of FIG. It is a perspective view which showed the back surface, the plane, and the left side surface of the horizontal flight state of the embodiment of FIG. It is a front view of the form example of FIG. It is a left side view of the form example of FIG.

Hereinafter, a form example of the vertical takeoff and landing aircraft according to the present invention will be described in detail with reference to the accompanying drawings (FIGS. 1 to 5). This vertical takeoff and landing aircraft can be used as, for example, a drone (unmanned aerial vehicle), and can fly to a remote location by radio control or autopilot using GPS (Global Positioning System) or wireless communication network. It is available.

As a basic configuration, the vertical takeoff and landing aircraft according to the present invention is provided with a plurality of rotors 30 (in this embodiment, the left rotor 31 and the right rotor 32) so that vertical takeoff and landing can be performed, and the lift generated by the wing shape is provided. It is equipped with a fixed wing 20 so that it can fly horizontally. Further, the fixed wings 20 are upper and lower wings (upper wing 20a, lower wing 20b) located up and down during level flight, and are formed by being arranged on the left and right with the fuselage 10 as the center. It is composed of the compound wing (left compound wing 21 and right compound wing 22).

The left and right biplane wings 21 and 22 are provided with wing tip continuous portions 21a and 22a in which the upper and lower wings 20a and 20b are continuous at each wing tip, and are surrounded by the body 10 and the left and right biplane wings 21 and 22. Rotors 30 (left rotor 31 and right rotor 32) are arranged in each of the left and right inner spaces 23 and 24. The rotor 30 of this embodiment is provided with three propellers, but the rotor 30 is not limited to this, and it goes without saying that a known form can be selectively adopted as appropriate.

According to the vertical takeoff and landing aircraft according to the present invention, lift can be obtained by the fixed wings 20 composed of the left and right biplanes 21 and 22, so that efficient flight that can extend the cruising range can be realized. By providing the blade tip continuous portions 21a and 22a together with the effect, it is possible to obtain a blade form having high structural strength and rigidity although it is a simple form. Therefore, the weight of the airframe can be reduced and the transportation efficiency can be improved.

Further, by providing the wing tip continuous portions 21a and 22a, the propellers of the rotor device (left rotor 31 and right rotor 32) are arranged so as not to be exposed to a dangerous state. Safety can be ensured appropriately. That is, the blade tip continuous portions 21a and 22a are rotor guards, which not only provide safety but also have the effect of protecting the rotor device from damage. Further, it is considered that the aerodynamic efficiency can be improved because the left and right inner spaces 23 and 24 are formed in a frame shape that opens in the flight direction to have the effect of rectifying the airflow. The corners where the left and right wing tip continuous portions 21a and 22a and the upper and lower wing tips 20a and 20b of the left and right wing tips are continuous have a curved and continuous rounded shape so as to reduce air resistance. There is.

In the example of the present embodiment, the fixed wing 20 is in the form of two upper and lower biplane blades, and two rotors 30 (left rotor 31 and right rotor 32) are arranged. It is not limited. For example, the fixed wing 20 can be a biplane wing of three or more, or the rotor 30 can be arranged on each of the left and right sides (four or more in total on the left and right sides). ..

Further, in the vertical takeoff and landing aircraft of this embodiment, moving blades 40 (left moving blades 41 and right moving blades 42) are arranged immediately below the left and right rotors 31 and 32, respectively. According to the left and right rotors 31 and 32 and the two rotor blades 40 (left rotor blade 41 and right rotor blade 42), the attitude control of the vertical takeoff and landing aircraft according to the present invention can be appropriately performed. Since the moving blade 40 is located directly below the rotor 30, the responsiveness to the control operation (steering) can be enhanced, and the maneuverability of the aircraft can be enhanced. The moving blade 40 of this embodiment is an elevon and has the functions of an elevator (elevator) and an aileron (auxiliary wing).

That is, according to the example of this embodiment, the pitch axis is controlled by controlling the driving force (thrust) of the left rotor 31 and the right rotor 32 and controlling the operation of the left rotor blade 41 and the right rotor blade 42. It is possible to perform three-axis control of the aircraft by centered pitch control, roll control centered on the roll axis, and yaw control centered on the yaw axis.

The pitch control of this embodiment is a rotation shaft provided parallel to the pitch axis parallel to the extension direction of the fixed blade 20 extending to the left and right orthogonal to the axis extending back and forth (roll axis) which is the axis of the body 10. This can be done by rotating the moving blade 40 around the above. Unless other conditions such as the driving condition of the rotor 30 are taken into consideration, basically, the nose can be moved up and down by rotating the left rotor blade 41 and the right rotor blade 42 in the same direction. That is, the nose can be raised by rotating the rotating free end side of the left rotor blade 41 and the right rotor blade 42 downward, for example, in a horizontal flight attitude. On the contrary, the nose can be lowered by rotating the rotating free end side of the left rotor blade 41 and the right rotor blade 42 upward, for example, in a horizontal flight attitude. Further, according to this pitch control, for example, the transition from horizontal flight to vertical flight and the transition from vertical flight to horizontal flight can be smoothly performed.

In the roll control of this embodiment, the left rotor blade 41 and the right rotor blade 42 are rotated in opposite directions, and the operation of the left rotor blade 41 and the right rotor blade 42 is different from each other. This can be done by rolling the aircraft around its axis (roll axis). That is, for example, if the left rotor blade 41 is rotated upward and the right rotor blade 42 is rotated downward, the left rotor blade 41 is rotated downward, and conversely, the left rotor blade 41 is rotated downward and the right rotor blade 41 is rotated downward. If the rotor blade 42 is rotated upward, it will roll to the right.

The yaw control of this embodiment can be performed by controlling the thrust of the rotor. That is, by controlling the thrust of the right rotor to be larger than the thrust of the left rotor, the nose can be turned to the left. On the contrary, by controlling the thrust of the left rotor to be larger than the thrust of the right rotor, the nose can be turned to the right.

The above-mentioned three-axis control and flight control of the vertical takeoff and landing aircraft according to the present invention can be performed by using a known flight control device. For example, flight control can be performed by applying a drone (unmanned aerial vehicle) control device. That is, according to the flight control device, various types of information such as attitude information by a gyro sensor, GPS position information, wireless maneuvering information including those using a communication network, and light and radio wave information such as image processing and radio wave processing. By sensing and acquiring information, attitude control such as vertical takeoff and landing, hovering (fixed point flight) and horizontal flight, control and management of flight speed, flight altitude, flight time and cruising distance, control of payload (loading capacity) center of gravity It is possible to perform control related to flight such as management.

Further, in the vertical takeoff and landing aircraft of this embodiment, the left rotor 31 and the right rotor 32 are respectively a left bridge support 51 and a right bridge formed by being bridged between the upper and lower wings 20a and 20b, respectively. It is configured to be driven by the left drive device 31a and the right drive device 32a, which are supported by the support portion 52, respectively.

According to the left and right bridge support portions 51 and 52, since they are formed so as to be bridged between the upper and lower blades 20a and 20b, it is a simple form, but its structural strength and rigidity can be appropriately increased. The drive devices 31a and 32a and the rotor 30 (left rotor 31 and right rotor 32) can be appropriately supported.

Further, the left drive device 31a and the right drive device 32a according to this embodiment are composed of an electric motor, and are provided so as to be driven by a secondary battery such as a lithium ion battery as a power source. It should be noted that the drive devices 31a and 32a are not limited to the electric motor, and of course, the drive devices 31a and 32a may be configured by an engine.

Further, the moving blades 40 (left moving blade 41, right moving blade 42) are bridge support portions (left bridge support portion 51 and right bridge support portion 51) formed by being bridged between the upper and lower blades 20a and 20b. It is configured to be operated by an actuating mechanism supported by each of the support portions 52).

According to the left and right bridge support portions 51 and 52, since they are formed so as to be bridged between the upper and lower blades 20a and 20b, it is a simple form, but its structural strength and rigidity can be easily increased. It is possible to appropriately support each operating mechanism and the moving blade 40 (left moving blade 41, right moving blade 42) in the same manner as the effect related to the rotor 30 described above.

Further, in the vertical takeoff and landing aircraft of this embodiment, the leg portion 60 for vertical takeoff and landing is provided at each corner of each of the left and right biplanes 21 and 22 provided with the left and right wing tip continuous portions 21a and 22a. In the form example, it is provided in a form extending rearward at four places). The legs for vertical takeoff and landing have a rod-like shape extending in the direction along the flight direction, and are provided so as not to cause air resistance. In this embodiment, four legs 60 for vertical takeoff and landing are provided.

According to this, the load of the aircraft can be rationally dispersed and the landing can be performed stably.
The leg portion 60 for vertical takeoff and landing of the present embodiment is formed in a columnar shape having a circular cross section, but the present invention is not limited to this, and the leg portion 60 has a hollow cylindrical shape for weight reduction. Of course, it can be made into a form or provided in another known form with increased structural strength and rigidity.

Further, in the vertical takeoff and landing aircraft of this embodiment, a storage space 11 is provided on the fuselage 10 so that luggage can be loaded. For example, the cover forming the nose can be opened / closed or detached, and a structure can be provided in which luggage can be stored / loaded. According to this, since the luggage is covered with the streamlined cover and incorporated in the aircraft, the air resistance during flight can be reduced as much as possible and the transportation efficiency can be improved.

Although various examples of the present invention have been described above, the present invention is not limited to the examples of the present invention, and it goes without saying that many modifications can be made without departing from the spirit of the invention. That is.

10 Body 11 Storage space 20 Fixed wing 20a Upper wing 20b Lower wing 21 Left wing tip continuous part 22 Right wing tip continuous part 22 Right wing tip continuous part 23 Left inner space 24 Right inner space 30 Rotor 31 Left Rotor 31a Left drive 32 Right rotor 32a Right drive 40 Wing 41 Left wing 42 Right wing 51 Left bridge support 52 Right bridge support 60 Legs for vertical takeoff and landing

Claims (6)

It is equipped with multiple rotors for vertical takeoff and landing, and fixed wings for horizontal flight with the lift generated by the wing shape, and the fixed wings are the upper and lower wings located up and down during horizontal flight. It is a vertical take-off and landing aircraft composed of left and right compound wing formed by arranging left and right around the fuselage.
The left and right compound wing includes a wing tip continuous portion in a form in which the upper and lower wings are continuous at each wing tip, and the left and right inner spaces surrounded by the fuselage and the left and right compound wing are described in each of the left and right inner spaces. A vertical takeoff and landing aircraft characterized by a rotor arrangement. The vertical take-off and landing aircraft according to claim 1, wherein moving blades are arranged immediately below the rear of the rotors on the left and right sides. The vertical take-off and landing aircraft according to claim 1 or 2, wherein the rotor is driven by a drive device supported by a bridge support formed so as to be bridged between the upper and lower wings. The vertical take-off and landing aircraft according to claim 2 or 3, wherein the moving blades are operated by an operating mechanism supported by a bridge support formed so as to be bridged between the upper and lower wings. The claim is characterized in that the leg portion for vertical takeoff and landing is provided in a form extending rearward at each corner portion of each wing tip of the left and right biplane blades provided with the wing tip continuous portion. The vertical takeoff and landing aircraft according to any one of 1 to 4. The vertical take-off and landing aircraft according to any one of claims 1 to 5, wherein a storage space is provided on the fuselage so that luggage can be loaded.

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