WO2020003657A1

WO2020003657A1 - Aircraft

Info

Publication number: WO2020003657A1
Application number: PCT/JP2019/012330
Authority: WO
Inventors: 雄介大西; 空野宮内; 哲弥宮腰; 悟服部; 認柴田
Original assignee: 新明和工業株式会社
Priority date: 2018-06-27
Filing date: 2019-03-25
Publication date: 2020-01-02
Also published as: JP2020001509A; JP7149116B2

Abstract

The purpose of the present invention is to provide an aircraft which comprises a left and right pair of rotors, a rotor disposed on the airframe centerline, and a fixed wing and exhibits excellent airframe stability during vertical takeoff and landing. This aircraft (1) comprises: a fuselage (10); a fixed wing (20) that is a swept-back wing; a propeller (40) that generates forward thrust; a left rotor (31) that is disposed on the left side of the airframe centerline (CL); a right rotor (32) that is disposed on the right side of the airframe centerline (CL); and a central rotor (33) that is disposed on the airframe centerline (CL). The center of gravity (CG) of the airframe is located inside a triangle (50) which is formed by connecting the rotation center line (31c) of the left rotor (31), the rotation center line (32c) of the right rotor (32), and the rotation center line (33c) of the central rotor (33).

Description

aircraft

The present invention relates to an aircraft having both a rotary wing and a fixed wing.

航空機 Conventionally, an aircraft having both a rotor (hereinafter referred to as a “rotor”) and a fixed wing has been known. For example, Patent Documents 1 and 2 disclose such an aircraft. According to the aircraft having both the rotor and the fixed wing, the take-off and landing can be performed by the rotor, so that the runway is not required. In addition, since horizontal flight with the fixed wings is possible, it is possible to fly at a relatively high speed and to increase the cruising distance.

Patent Document 1 discloses an aircraft including two pairs of left and right or three pairs of right and left rotors, fixed wings extending left and right from the fuselage, and a propeller provided at the tip of the fuselage. Patent Document 2 discloses an aircraft including four pairs of left and right rotors, front and rear fixed wings extending left and right from the fuselage, respectively, and a pair of left and right propellers provided on the rear fixed wings. In the aircraft disclosed in Patent Documents 1 and 2, all the rotors are provided so as to form a pair on the left and right, and the rotors of each pair are arranged symmetrically.

JP 2014-528382 A Japanese Patent No. 5421503

発明 The inventor of the present application has considered placing another rotor on the fuselage center line separately from the pair of left and right rotors. However, in such an aircraft, the airframes disclosed in Patent Documents 1 and 2 cannot be directly used. If the configuration of the aircraft is not modified, the stability of the aircraft during vertical takeoff and landing may be impaired.

The present invention has been made in view of the above, and an object of the present invention is to provide a pair of left and right rotors and rotors arranged on the fuselage center line, and fixed wings, and to have excellent stability of the fuselage during vertical takeoff and landing. Is to provide aircraft.

An aircraft according to the present invention includes a fuselage, a fixed wing fixed to the fuselage, at least three rotors respectively attached to the fuselage or the fixed wing to generate vertical thrust, and attached to the fuselage or the fixed wing. And a propeller for generating forward thrust. The rotor includes a left rotor arranged on the left side of the fuselage center line, a right rotor arranged on the right side of the fuselage center line, and a central rotor arranged on the fuselage center line. The fixed wing is a swept wing. A machine center of gravity is arranged inside a triangle formed by connecting the rotation center line of the left rotor, the rotation center line of the right rotor, and the rotation center line of the center rotor. In addition, "attached to the fuselage or the fixed wing" includes a case where it is directly attached to the fuselage or the fixed wing and a case where it is indirectly attached via another member.

According to the aircraft, in addition to the pair of left and right rotors (that is, the left rotor and the right rotor), the aircraft includes a center rotor disposed on the fuselage center line. However, since the fixed wings are the swept wings, the aircraft center of gravity can be positioned relatively rearward. Then, the machine center of gravity is arranged inside a triangle formed by connecting the rotation center of the left rotor, the rotation center of the right rotor, and the rotation center of the center rotor. For this reason, it is easy to secure the stability of the aircraft during vertical takeoff and landing while having the rotor arranged on the aircraft centerline.

According to a preferred aspect of the present invention, the fixed wings are disposed on the left and right of the fuselage center line and have a first swept wing portion having a first swept angle, and a first swept wing portion has a first swept wing portion on the outside in the left-right direction. A second swept wing portion disposed and having a second swept angle greater than the first swept angle.

According to the above aspect, since the fixed wing has the above-described configuration (that is, a multi-stage retreat wing), it is easy to arrange the machine center of gravity relatively rearward. Therefore, the machine center of gravity can be easily arranged inside the triangle. Therefore, the stability of the aircraft at the time of vertical takeoff and landing can be easily ensured.

According to a preferred aspect of the present invention, the left rotor, the right rotor, and the center rotor are arranged on the center side in the left-right direction with respect to the second swept wing portion. The aircraft includes an elevon provided on the second swept wing portion of the fixed wing.

According to the above aspect, since each of the rotors is not in front of the elevon, it is possible to prevent the airflow from the front toward the elevon from being disturbed by the rotors. Therefore, the performance of horizontal flight can be improved.

According to a preferred aspect of the present invention, the fixed wing has at least one hole. At least one of the left rotor, the right rotor, and the center rotor is disposed inside the hole.

According to the above aspect, at least one of the left rotor, the right rotor, and the center rotor is arranged inside the hole of the fixed wing. Therefore, the air resistance of the rotor during horizontal flight can be reduced. Therefore, the performance of horizontal flight can be improved.

According to a preferred aspect of the present invention, at least one hole is formed in the first swept wing portion of the fixed wing. At least one of the left rotor, the right rotor, and the center rotor is disposed inside the hole.

According to the above aspect, at least one of the left rotor, the right rotor, and the center rotor is disposed inside the hole of the first swept wing portion of the fixed wing. Therefore, the air resistance of the rotor during horizontal flight can be reduced. Further, since the first swept wing portion can easily secure the wing area more than the second swept wing portion, the area of the first swept wing portion can be easily ensured even if the hole is formed. Therefore, the horizontal flight performance can be improved by reducing the air resistance and securing the wing area.

According to a preferred aspect of the present invention, the aircraft includes a rotor cover fixed to the fuselage or the fixed wing and having a hole formed therein. At least one of the left rotor, the right rotor, and the center rotor is disposed inside the hole of the rotor cover.

According to the above aspect, at least one of the left rotor, the right rotor, and the center rotor is disposed inside the hole of the rotor cover. Therefore, the air resistance of the rotor during horizontal flight can be reduced. Therefore, the performance of horizontal flight can be improved.

According to a preferred aspect of the present invention, the propeller is disposed forward of the fixed wing. The left rotor and the right rotor are arranged at positions shifted left and right from a rotation center line of the propeller.

According to the above aspect, the propeller and all of the rotors rotate during the transition flight, but since the left rotor and the right rotor are arranged at positions shifted left and right from the propeller, turbulent flow behind the propeller causes the left rotor to rotate. In addition, it is possible to suppress adverse effects on the right rotor. Therefore, the performance of the transition flight can be improved.

According to a preferred aspect of the present invention, the left rotor, the right rotor, and the center rotor are disposed rearward of a front end of the fixed wing and frontward of a rear end of the fixed wing. .

According to the above aspect, the longitudinal length of the aircraft can be reduced, and the aircraft can be made compact.

According to a preferred aspect of the present invention, only the left rotor, the right rotor, and the center rotor are provided as rotors for generating a vertical thrust.

(4) In an aircraft having both rotors and fixed wings, the number of rotors is preferably as large as possible in order to improve the performance of vertical ascent. However, the rotor causes an increase in air resistance during level flight and also causes an increase in weight. Therefore, when the number of rotors is large, the level flight performance tends to decrease. In order to improve the level flight performance, the smaller the number of rotors, the better. However, simply reducing the number of rotors may impair the stability of the aircraft during vertical takeoff and landing. However, as described above, in the aircraft according to the present invention, the aircraft center of gravity is disposed inside a triangle connecting the rotation centers of the three rotors (that is, the left rotor, the right rotor, and the center rotor). Therefore, it is easy to secure the stability of the aircraft during vertical takeoff and landing. According to the above aspect, the number of rotors is reduced to three taking advantage of the property that stability is easily ensured. Thereby, the number of rotors is smaller than that of a conventional aircraft having two or more pairs of rotors on the left and right (in other words, four or more rotors), so that the level flight performance can be improved. Therefore, according to the above aspect, the horizontal flight performance can be improved as compared with the related art while securing the stability of the airframe during vertical takeoff and landing.

According to a preferred aspect of the present invention, the aircraft includes a vertical plate provided at a left-right end of the fixed wing, and does not include a tail.

The tail can cause air resistance during vertical flight. However, according to the above aspect, since the tail fin is not provided, the performance of vertical flight can be improved.

According to the present invention, it is possible to provide an aircraft having a pair of left and right rotors, a rotor disposed on the fuselage center line, and fixed wings, and having excellent stability of the fuselage during vertical takeoff and landing.

It is a top view of an aircraft concerning one embodiment of the present invention. It is a front view of the above-mentioned aircraft. It is a left view of the said aircraft. It is a top view of the aircraft concerning other embodiments. It is a top view of the aircraft concerning other embodiments. It is a top view of the aircraft concerning other embodiments.

Hereinafter, embodiments of the present invention will be described with reference to the drawings. FIG. 1 is a plan view of an aircraft 1 according to one embodiment of the present invention. FIG. 2 is a front view of the aircraft 1, and FIG. 3 is a left side view of the aircraft 1. The aircraft 1 is an aircraft having both a rotary wing (rotor) and a fixed wing, and is configured to be capable of vertical takeoff and landing using the rotary wing and horizontal flight using the fixed wing. Although the aircraft 1 according to the present embodiment is an unmanned aircraft, the aircraft according to the present invention may be a manned aircraft.

As shown in FIGS. 1 to 3, the aircraft 1 has a fuselage 10, a fixed wing 20, a propeller 40, three

rotors

31, 32, 33, a rotor cover (Rotor @ Cover) 45, and an elevon 23, And a vertical plate 24. The aircraft 1 is a so-called tailless aircraft, and does not have a horizontal tail and a vertical tail. However, the aircraft according to the present invention is not limited to the tailless aircraft. The aircraft according to the invention may have a horizontal or vertical tail.

ＣＬIn FIG. 1, CL represents the center line of the fuselage. Here, the fuselage 10 is disposed on the fuselage center line CL, but is not particularly limited. For example, the fuselage 10 is provided in a pair on the left and right, and the left and right fuselage 10 may not be on the fuselage center line CL. The configuration of the body 10 is not particularly limited.

The propeller 40 is attached to the tip of the body 10. The propeller 40 generates a forward thrust (that is, a forward thrust). In the present embodiment, the number of the propellers 40 is one, but two or more may be provided. As long as the stability can be ensured, the propeller 40 does not necessarily have to be arranged on the fuselage center line CL. Further, the propeller 40 does not necessarily have to be attached to the body 10. The propeller 40 may be attached to the fixed wing 20.

The fixed wing 20 is a swept wing. That is, the fixed wing 20 is formed so as to go rearward from the center in the left-right direction to the outside. In this specification, the center in the left-right direction refers to a side approaching the body center line CL, and the outside in the left-right direction refers to a side moving away from the body center line CL.

The fixed wing 20 may be a single-stage swept-back wing, but in this embodiment, the fixed wing 20 includes two-stage swept-back wings. The fixed wing 20 has a first swept wing portion 21 and a second swept wing portion 22. The first swept wing portions 21 are disposed on the left and right of the fuselage center line CL and have a first swept angle θ1. Note that the sweepback angle is an angle formed by a line connecting points located at a distance of 1/4 of the chord length from the leading edge of the wing with the left-right axis perpendicular to the fuselage center line CL. The second swept wing portion 22 is disposed outside the first swept wing portion 21 in the left-right direction, and has a second swept angle θ2 larger than the first swept angle θ1.

The first swept wing portion 21 has a constant chord length. The second swept wing portion 22 is formed such that the chord length becomes shorter as going outward in the left-right direction. However, these are merely examples, and the shapes and dimensions of the first swept wing portion 21 and the second swept wing portion 22 are not particularly limited.

The elevon 23 is a moving blade having a role of an auxiliary wing (Aileron) and a function of an elevator (Elevator). The elevons 23 are provided in a pair on the left and right, and are provided on the rear side of the left and right second swept wing portions 22 here.

The vertical plate 24 is provided at the tip of the fixed wing 20 in the left-right direction. Specifically, the left vertical plate 24 is provided at the tip of the second left swept wing portion 22, and the right vertical plate 24 is provided at the tip of the right second swept wing portion 22. However, the location where the vertical plate 24 is provided is not necessarily the tip of the fixed wing 20. Further, the vertical plate 24 may be provided with a moving blade (Rudder).

The

rotors

31, 32, 33 generate upward vertical thrust. The rotor 31 is disposed on the left side of the fuselage center line CL. The rotor 32 is arranged on the right side of the fuselage center line CL. The rotor 33 is arranged on the fuselage center line CL. Hereinafter, the rotor 31, the rotor 32, and the rotor 33 are referred to as a left rotor 31, a right rotor 32, and a center rotor 33, respectively. The shapes and dimensions of the left rotor 31, right rotor 32, and center rotor 33 may be different from each other, but are the same in the present embodiment.

固定 As shown in FIG. 1, the fixed wing 20 has left and

right holes

25 and 26 formed therein. Here, a hole 25 is formed in the left first fixed wing portion 21, and a hole 26 is formed in the right first fixed wing portion 22. The left rotor 31 is arranged inside the left hole 25, and the right rotor 32 is arranged inside the right hole 26. The left rotor 31 and the right rotor 32 are arranged on the center side in the left-right direction with respect to the second swept wing portion 22. However, it is also possible to form the

holes

25, 26 in the left and right second fixed wing portions 22, and to arrange the left rotor 31 and the right rotor 32 inside the

holes

25, 26.

(2) As shown in FIG. 2, the left rotor 31 and the right rotor 32 do not protrude above and below the first fixed wing portion 21, and are arranged so as to reduce air resistance during horizontal flight. In the present embodiment, the driving sources of the left rotor 31 and the right rotor 32 are

electric motors

31E and 32E, respectively. The left rotor 31 is connected to an electric motor 31E, and the right rotor 32 is connected to an electric motor 32E. A beam 34 is disposed inside the first fixed wing portion 21. The left electric motor 31E is supported by the left beam 34, and the right electric motor 32E is supported by the right beam 34.

The positions of the

holes

25 and 26 in the front-rear direction are not particularly limited. Here, the centers of the

holes

25 and 26 are located forward of an intermediate position between the leading edge and the trailing edge of the first fixed wing portion 21. ing. The rotation center 31c of the left rotor 31 and the rotation center 32c of the right rotor 32 are located ahead of an intermediate position between the leading edge and the trailing edge of the first fixed wing portion 21.

The rotor cover 45 is fixed to the fuselage 10 or the fixed wing 20. A hole 46 is formed in the rotor cover 45. The center of the hole 46 is located on the fuselage center line CL.

The center rotor 33 is arranged inside the hole 46 of the rotor cover 45. The rotation center line 33c of the center rotor 33 is located on the fuselage center line CL. As shown in FIG. 3, the electric motor 33E that drives the center rotor 33 is disposed below the rotor cover 45. However, the central rotor 33 does not protrude above and below the rotor cover 45, and is arranged so that air resistance is reduced during horizontal flight. As shown in FIG. 1, a part of the central rotor 33 and the electric motor 33E are arranged behind the body 10.

において In FIG. 1, the symbol CG represents the center of gravity of the aircraft 1. Hereinafter, the center of gravity of the aircraft 1 will be referred to as the aircraft center of gravity CG. The machine center of gravity CG is located on the machine center line CL. In the aircraft 1 according to the present embodiment, the aircraft center of gravity CG is disposed relatively rearward. The machine center of gravity CG is arranged inside a triangle 50 connecting the rotation center line 31c of the left rotor 31, the rotation center line 32c of the right rotor 32, and the rotation center line 33c of the center rotor 33. In the present embodiment, the distance between the rotation center line 31c and the rotation center line 33c is equal to the distance between the rotation center line 32c and the rotation center line 33c. The distance between the rotation center line 31c and the rotation center line 32c is larger than the distance between the rotation center line 31c and the rotation center line 33c. Triangle 50 is an isosceles triangle. However, it is not limited. The triangle 50 may be an equilateral triangle.

では In the present embodiment, the left rotor 31, the right rotor 32, and the center rotor 33 are arranged closer to the center in the left-right direction than the second swept-wing portion 22. Further, the left rotor 31, the right rotor 32, and the center rotor 33 are arranged on the rear side of the front end 20f of the fixed blade 20 and on the front side of the rear end 20r.

The propeller 40 is disposed forward of the fixed wing 20 and is located on the fuselage center line CL. On the other hand, the left rotor 31 is disposed on the left side of the fuselage center line CL, and the right rotor 32 is disposed on the right side of the fuselage center line CL. The fuselage center line CL coincides with the rotation center line 40c of the propeller 40. Therefore, the left rotor 31 and the right rotor 32 are arranged at positions shifted left and right from the rotation center line 40c of the propeller 40.

The above is the configuration of the aircraft 1. Next, the flight mode of the aircraft 1 will be described. The aircraft 1 performs a vertical flight when taking off and landing. That is, it rises vertically during takeoff and descends vertically during landing. The aircraft 1 can fly horizontally after takeoff. The aircraft 1 performs transition flight when transitioning from vertical flight to horizontal flight and when transitioning from horizontal flight to vertical flight.

During the vertical flight, the propeller 40 stops and drives the left rotor 31, the right rotor 32, and the center rotor 33. As a result, an upward vertical thrust is generated in the aircraft 1. Therefore, the aircraft 1 can perform vertical ascent and vertical descent, and can perform vertical takeoff and landing. According to the aircraft 1 according to the present embodiment, the aircraft center of gravity CG is arranged inside the triangle 50 connecting the rotation center lines 31c to 33c of the left rotor 31, the right rotor 32, and the center rotor 33. Therefore, the stability of the aircraft during vertical takeoff and landing can be easily ensured.

The aircraft 1 is capable of hovering flight that is stationary in the air. In the hovering flight, the propeller 40 stops, and the left rotor 31, the right rotor 32, and the center rotor 33 are driven. In a hovering flight stationary in the air, the left rotor 31, the right rotor 32, and the center rotor 33 generate an upward vertical thrust balanced with the weight of the aircraft 1. Thereby, the aircraft 1 can be stopped in the air.

During the transition flight, the propeller 40, the left rotor 31, the right rotor 32, and the center rotor 33 are all driven. When the rotation of the propeller 40 starts during vertical ascent or hovering, the aircraft 1 starts flying forward. When the aircraft 1 flies forward, lift is generated by the fixed wings 20. The lift by the fixed wings 20 increases as the airspeed of the aircraft 1 in the horizontal direction increases. Therefore, in the transition flight, as the airspeed in the horizontal direction increases, the rotation speeds of the left rotor 31, the right rotor 32, and the center rotor 33 are reduced. Then, when the lift by the fixed wings 20 becomes large enough to balance the own weight of the aircraft 1, the rotation of the left rotor 31, the right rotor 32, and the center rotor 33 is stopped, the transition flight ends, and the flight shifts to the level flight.

In the horizontal flight, the left rotor 31, the right rotor 32, and the center rotor 33 stop and drive the propeller 40. As a result, the aircraft 1 performs horizontal flight using the propeller 40 and the fixed wing 20.

When transitioning from horizontal flight to hovering flight or vertical flight, a transition flight reverse to the above operation is performed.

As described above, the aircraft 1 according to the present embodiment has both the fixed wings 20 and the rotors 31 to 33. Since the rotors 31 to 33 enable vertical takeoff and landing, no runway is required. Further, since the horizontal flight by the fixed wing 20 is possible, it is possible to fly at a relatively high speed, and the cruising distance can be lengthened.

By the way, according to the aircraft 1 of the present embodiment, in addition to the pair of left and right rotors (that is, the left rotor 31 and the right rotor 32), the aircraft 1 includes the center rotor 33 arranged on the fuselage center line CL. The configuration is different from that of a conventional aircraft in which all rotors are arranged in pairs on the left and right. For this reason, there is a concern about the stability at the time of vertical takeoff and landing in the same aircraft configuration as the conventional one. However, according to the aircraft 1 according to the present embodiment, since the fixed wing 20 is a swept wing, the aircraft center of gravity CG can be positioned relatively rearward. By using the fixed wing 20 as a retreat wing, the machine center of gravity CG is arranged inside a triangle 50 connecting the rotation center 31c of the left rotor 31, the rotation center 32c of the right rotor 32, and the rotation center 33c of the center rotor 33. I decided. Therefore, according to the aircraft 1 according to the present embodiment, it is easy to secure the stability of the aircraft at the time of vertical takeoff and landing while including the central rotor 33 arranged on the aircraft centerline CL. Therefore, according to the present embodiment, the stability of the fuselage during vertical takeoff and landing is excellent while including the pair of left and

right rotors

31 and 32, the rotor 33 arranged on the fuselage center line CL, and the fixed wing 20. The aircraft 1 can be realized.

Further, according to the aircraft 1 according to the present embodiment, the fixed wing 20 includes the first swept wing portion 21 having the first swept angle θ1 and the second swept wing portion 22 having the second swept angle θ2. It consists of two stages of swept wings. Therefore, compared to the case where the fixed wing 20 is constituted by a single-stage swept wing having the first swept angle θ1, the machine body center of gravity CG is more easily arranged rearward. Accordingly, the machine center of gravity CG can be easily arranged inside the triangle 50. Therefore, the stability of the aircraft at the time of vertical takeoff and landing can be easily ensured.

Further, in the aircraft 1 according to the present embodiment, the elevon 23 is provided on the second swept-wing portion 22, but the rotors 31 to 33 are arranged on the center side in the left-right direction with respect to the second swept-wing portion 22. ing. The rotors 31 to 33 are not located in front of the elevon 23 but are arranged at positions shifted from the elevon 23 in the left-right direction. Therefore, when the aircraft 1 is moving forward, it is possible to prevent the airflow from the front toward the elevon 23 from being disturbed by the rotors 31 to 33. Therefore, the performance of horizontal flight can be improved.

The left rotor 31, right rotor 32, and center rotor 33 generate vertical thrust during vertical flight, but stop rotation during horizontal flight. The left rotor 31, the right rotor 32, and the center rotor 33 may cause an increase in air resistance during horizontal flight. However, according to the aircraft 1 according to the present embodiment, the

holes

25 and 26 are formed in the fixed wing 20, and the left rotor 31 and the right rotor 32 are disposed inside the

holes

25 and 26, respectively. Further, the aircraft 1 includes a rotor cover 45 having a hole 46 formed therein, and the center rotor 33 is disposed inside the hole 46 of the rotor cover 45. The fixed wings 20 reduce the air resistance of the left rotor 31 and the right rotor 32, and the rotor cover 45 plays a role of reducing the air resistance of the central rotor 33. Therefore, according to the aircraft 1 of the present embodiment, the air resistance of the rotors 31 to 33 during horizontal flight can be reduced, and the performance of horizontal flight can be improved.

Generally, the fixed wing 20 tends to have a shorter chord length as it approaches the wing tip. The closer to the wing tip, the more difficult it is to secure the wing area. In the present embodiment, the

holes

25 and 26 are formed in the first swept wing portion 21 of the fixed wing 20. That is, the

holes

25 and 26 are formed in a portion of the fixed blade 20 where the blade area is easily secured. Accordingly, the area of the first swept wing portion 21 can be secured despite the

holes

25 and 26 being formed. Therefore, the horizontal flight performance can be improved by the effect of reducing the air resistance and the effect of securing the wing area. In the present embodiment, the wing area of the first swept wing portion 21 is larger than the wing area of the second swept wing portion 22 when it is assumed that there are no

holes

25 and 26. However, the actual wing area of the first swept wing portion 21 (that is, the wing area excluding the holes 25 and 26) may be larger than the wing area of the second swept wing portion 22.

According to the aircraft 1 according to the present embodiment, during the transition flight, all of the propeller 40 and the rotors 31 to 33 rotate. However, the propeller 40 is arranged ahead of the fixed wing 20, and the left rotor 21 and the right rotor 22 are arranged at positions shifted left and right from the rotation center line 40 c of the propeller 40. Therefore, it is possible to suppress the turbulent airflow behind the propeller 40 from adversely affecting the left rotor 31 and the right rotor 22 during the transition flight. Therefore, the performance of the transition flight can be improved.

配置 The arrangement of the rotors 31 to 33 is not particularly limited, but in the present embodiment, the rotors 31 to 33 are arranged behind the front end 20f of the fixed wing 20 and before the rear end 20r. Thereby, the front-back length of the aircraft 1 can be suppressed, and the aircraft 1 can be made compact.

では In the present embodiment, the number of the rotors 31 to 33 is three. The aircraft 1 according to the present embodiment includes only a left rotor 31, a right rotor 32, and a center rotor 33 as rotors that generate vertical thrust. In order to improve the level flight performance, the smaller the number of rotors, the better. However, simply reducing the number of rotors may impair the stability of the aircraft during vertical takeoff and landing. However, as described above, in the aircraft 1 according to the present embodiment, the aircraft center of gravity CG is arranged inside the triangle 50 connecting the rotation center lines 31c to 33c of the three rotors 31 to 33. Therefore, it is easy to secure the stability of the aircraft during vertical takeoff and landing. In the aircraft 1 according to the present embodiment, the number of rotors is set to three taking advantage of the above-described characteristic that stability is easily ensured. Thereby, since the number of rotors is smaller than that of a conventional aircraft having two or more pairs of rotors on the left and right (in other words, a total of four or more rotors), the level flight performance can be improved. Therefore, according to the aircraft 1 according to the present embodiment, the horizontal flight performance can be improved as compared to the related art while securing the stability of the aircraft during vertical takeoff and landing.

The aircraft 1 according to the present embodiment includes the vertical plate 24 provided at the tip of the fixed wing 20, but does not include the tail fin. Neither horizontal tail nor vertical tail is provided. Although the aircraft 1 is capable of vertical flight as well as horizontal flight, the tail fin (particularly the horizontal tail wing) may cause air resistance during vertical flight. However, according to the aircraft 1 according to the present embodiment, since it does not include the tail, the performance of vertical flight can be improved.

In the above description of the flight mode, the aircraft 1 performs the vertical takeoff and landing, but the takeoff and landing of the aircraft 1 is not limited to the vertical takeoff and landing (VTOL). By rotating the propeller 40 during takeoff and landing, short takeoff and landing (STOL) is also possible.

Although the embodiment of the present invention has been described above, the embodiment is merely an example. Various other embodiments are possible. Next, an example of another embodiment will be briefly described.

In the above embodiment, the rotor cover 45 is provided to cover the periphery of the central rotor 33. However, as shown in FIG. 4, the rotor cover 45 may not be provided.

Moreover, as shown in FIG. 5, the left rotor 31 and the right rotor 32 do not necessarily have to be arranged inside the

holes

25 and 26 of the fixed wing 20. As shown in FIG. 5, holes 25 and 26 may not be formed in fixed wing 20. The left rotor 31 and the right rotor 32 may be arranged in front of the fixed wing 20.

では In the above embodiment, the center rotor 33 is disposed behind the left rotor 31 and the right rotor 32. On the other hand, as shown in FIG. 6, the center rotor 33 may be arranged ahead of the left rotor 31 and the right rotor 32. In the embodiment shown in FIG. 6, a hole 27 is formed in the first swept wing portion 21 of the fixed blade 20, and the central rotor 33 is disposed inside the hole 27. The left rotor 31 and the right rotor 32 are arranged behind the fixed wing 20. The rotor covers 45 having the holes 46 may be provided on the left and right sides of the fixed blade 20 on the rear side, respectively, and the left rotor 31 and the right rotor 32 may be disposed inside the holes 46 of the left and right rotor covers 45, respectively. .

In the above embodiments, the shapes and dimensions of the left rotor 31, the right rotor 32, and the center rotor 33 may be the same or different.

In the above embodiments, the number of rotors is three, but the aircraft 1 may include four or more rotors. That is, the aircraft 1 may include another rotor that generates vertical thrust, in addition to the left rotor 31, the right rotor 32, and the center rotor 33.

In each of the above embodiments, the fixed wing 20 has two stages of swept wings, but the fixed wing 20 may have one stage of swept wings. Further, the fixed wing 20 may include three or more swept wings. In each of the above embodiments, the leading edge and the trailing edge of the fixed wing 20 extend linearly. However, the leading edge and the trailing edge of the fixed wing 20 may extend in a curved shape.

In the above embodiments, the elevon 23 is provided on the second swept wing portion 22, but may be provided on the first swept wing portion 21.

In each of the above embodiments, the left rotor 31 and the right rotor 32 are arranged at positions shifted left and right from the rotation center line 40 c of the propeller 40. Specifically, the entirety of the rotating left rotor 31 and the entirety of the right rotor 32 do not cross the rotation center line 40 c of the propeller 40. However, when a plurality of propellers 40 are provided, the left rotor 31 and the right rotor 32 may be arranged on the rotation center line 40c of one of the propellers 40. That is, a part of the rotating left rotor 31 and a part of the right rotor 32 may intersect with the rotation center line 40 c of any of the propellers 40.

In each of the above embodiments, the center rotor 33 is disposed rearward of the front end 20f of the fixed blade 20 and forward of the rear end 20r. However, at least a part of the center rotor 33 may be arranged on the front side of the front end 20f of the fixed wing 20 or on the rear side of the rear end 20r. Further, at least a part of the left rotor 31 and the right rotor 32 may be arranged on the front side of the front end 20f of the fixed wing 20 or on the rear side of the rear end 20r.

DESCRIPTION OF SYMBOLS 1 ... Aircraft, 10 ... fuselage, 20 ... fixed wing, 21 ... 1st swept wing part, 22 ... 2nd swept wing part, 23 ... elevon, 24 ... vertical plate, 25 ... hole, 26 ... hole, 31 ... left rotor , 31c: center line of rotation of left rotor, 32: center line of rotation of right rotor, 32c: center line of rotation of 33, center rotor, 33c: center line of rotation of center rotor, 40: propeller, 40c: center line of rotation of propeller, 45: rotor cover, 46: hole, 50: triangle formed by connecting the rotation center line of the left rotor, the rotation center line of the right rotor, and the rotation center line of the center rotor.

Claims

The torso,
Fixed wings fixed to the fuselage,
At least three rotors each mounted on the fuselage or the fixed wing and generating vertical thrust;
A propeller attached to the fuselage or the fixed wing to generate forward thrust,
The rotor includes a left rotor disposed on the left side of the fuselage center line, a right rotor disposed on the right side of the fuselage center line, and a center rotor disposed on the fuselage center line,
The fixed wing comprises a swept wing,
An aircraft, wherein the aircraft center of gravity is disposed inside a triangle formed by connecting the rotation center line of the left rotor, the rotation center line of the right rotor, and the rotation center line of the center rotor.
The fixed wing is disposed on the left and right of the fuselage center line and has a first swept angle, and a first swept wing portion is arranged outside the first swept wing portion in the left-right direction and has a greater angle than the first swept angle. A second swept wing portion also having a large second swept angle.
The left rotor, the right rotor, and the central rotor are disposed on the center side in the left-right direction with respect to the second swept wing portion,
The aircraft according to claim 2, further comprising an elevon provided on the second swept wing portion of the fixed wing.
The fixed wing has at least one hole formed therein,
The aircraft according to any one of claims 1 to 3, wherein at least one of the left rotor, the right rotor, and the center rotor is disposed inside the hole.
At least one hole is formed in the first swept wing portion of the fixed wing,
The aircraft according to claim 2 or 3, wherein at least one of the left rotor, the right rotor, and the center rotor is disposed inside the hole.
A rotor cover fixed to the fuselage or the fixed wing and having a hole formed therein,
The aircraft according to any one of claims 1 to 5, wherein at least one of the left rotor, the right rotor, and the center rotor is disposed inside the hole of the rotor cover.
The propeller is arranged ahead of the fixed wing,
The aircraft according to any one of claims 1 to 6, wherein the left rotor and the right rotor are arranged at positions shifted left and right from a rotation center line of the propeller.
The vehicle according to any one of claims 1 to 7, wherein the left rotor, the right rotor, and the center rotor are disposed behind a front end of the fixed wing and forward of a rear end of the fixed wing. The aircraft described in one.
The aircraft according to any one of claims 1 to 8, wherein only the left rotor, the right rotor, and the center rotor are provided as rotors for generating vertical thrust.
A vertical plate provided at a tip in the left-right direction of the fixed wing,
The aircraft according to any one of claims 1 to 9, wherein the aircraft is not provided with a tail.