Patent Description:
<CIT> discloses an aircraft referred to as a vertical take-off and landing (VTOL) aircraft. The aircraft disclosed in <CIT> includes a fuselage, a front wing and a rear wing (main wing) connected to the fuselage, a plurality of takeoff and landing rotors disposed on the left and right sides of the fuselage, and a plurality of cruise rotors disposed above the rear wing. This aircraft uses the takeoff and landing rotors during takeoff and landing and during hovering, and uses the cruise rotors during cruising. In addition, this aircraft uses both the takeoff and landing rotors and the cruise rotors when transitioning from hovering to cruising and when transitioning from cruising to hovering.

In this aircraft, two takeoff and landing rotors arranged on the left and right sides of the fuselage form a pair. For example, this aircraft includes a pair of takeoff and landing rotors disposed forward of the front wing or at both ends of the front wing, one or more pairs of takeoff and landing rotors disposed between the front wing and the rear wing, and a pair of takeoff and landing rotors disposed rearward of the rear wing.

Further reference shall be made to document <CIT> which in a similar manner as document <CIT> discloses an aircraft with the features of the preamble of attached claim <NUM>. For the sake of completeness, reference shall also be made to document <CIT>.

When air flows to the wing from the front, lift is generated. In general, a main wing of an aircraft is configured to generate a large lift at a portion close to a fuselage. Therefore, a large lift can be obtained by smoothly guiding the air flowing from the front, to the vicinity of a connection portion between the main wing and the fuselage.

In the aircraft disclosed in <CIT>, a pair of takeoff and landing rotors are disposed forward of the rear wing (main wing) and close to the fuselage. When the takeoff and landing rotors and the cruise rotors are used together in this aircraft, the pair of takeoff and landing rotors disposed forward of the rear wing generates, in front of the rear wing, an air flow flowing from above to below. This air flow interferes with the flow of air guided from the front side of the rear wing to the vicinity of the connection portion between the rear wing and the fuselage. Then, the flow of the air guided to the vicinity of the connection portion between the rear wing and the fuselage may be disturbed, and the lift generated by the rear wing may be reduced.

The present invention has been made in view of such a problem, and an object thereof is to provide an aircraft capable of suppressing a decrease in lift generated by a wing when moving in a horizontal direction while using takeoff and landing rotors.

According to the present invention, there is provided an aircraft according to appended claim <NUM>.

According to each aspect of the present invention, it is possible to suppress a decrease in lift generated by the rear wing due to the operation of the second rotors.

A preferred embodiment of an aircraft according to the present invention will be presented and described in detail below with reference to the accompanying drawings.

In the present embodiment, an aircraft <NUM> is assumed to be an electric vertical take-off and landing (eVTOL) aircraft that generates lift and thrust using rotors each including an electric motor. In this specification, a vertically upward direction is referred to as an upward direction (upward), and a vertically downward direction is referred to as a downward direction (downward). Further, a moving direction of the aircraft <NUM> when the aircraft <NUM> moves (flies) in the horizontal direction is referred to as a forward direction (forward), and a direction opposite thereto is referred to as a rearward direction (rearward). Further, in a state of facing forward from the aircraft <NUM>, a direction toward the right side in the width direction of the aircraft <NUM> is referred to as a right direction (rightward), and a direction toward the left side in the width direction is referred to as a left direction (leftward). Further, the plan view of the aircraft <NUM> refers to a view in which the respective components are viewed from a position directly above the aircraft <NUM>. The front view of the aircraft <NUM> refers to a view in which the respective components are viewed from a position in front of the aircraft <NUM>.

The aircraft <NUM> includes a fuselage <NUM>, a front wing <NUM>, a rear wing <NUM>, two booms <NUM>, eight takeoff and landing rotors <NUM>, and two cruise rotors <NUM>. As shown in <FIG>, the structure of the aircraft <NUM> in plan view is bilaterally symmetrical about a position overlapping a central axis A of the fuselage <NUM> extending in the front-rear direction. In plan view, the central axis A overlaps a center of gravity G of the aircraft <NUM>.

The fuselage <NUM> is long in the front-rear direction. The fuselage <NUM> includes a front portion 12f located forward of the center of gravity G, and a rear portion 12r located rearward of the center of gravity G. The front portion 12f is configured such that the front end thereof is narrow. The rear portion 12r is configured such that the rear end thereof is narrow. The main body of the fuselage <NUM> may be partially covered with a fairing. In this specification, the fuselage <NUM>, the front portion 12f, and the rear portion 12r are referred to as such, including the fairing.

The front wing <NUM> is connected to an upper portion of the front portion 12f of the fuselage <NUM> and is configured to generate lift when the aircraft <NUM> moves forward. The front wing <NUM> includes a front wing main body (also referred to as a horizontal stabilizer) <NUM> extending to the left and right (laterally) from the center, and left and right elevators <NUM> disposed at the trailing edge of the front wing <NUM>.

The rear wing <NUM> is connected to an upper portion of the rear portion 12r of the fuselage <NUM> via a pylon <NUM> and is configured to generate lift when the aircraft <NUM> moves forward. The rear wing <NUM> includes a rear wing main body <NUM> extending laterally rearward from the center, left and right elevons <NUM> disposed at the trailing edge of the rear wing <NUM>, and a pair of vertical tails <NUM> disposed at left and right wing tips of the rear wing <NUM>. Each vertical tail <NUM> includes a tail main body <NUM> (also referred to as a vertical stabilizer), and a rudder <NUM> disposed at the trailing edge of the vertical tail <NUM>.

The wing area of the rear wing <NUM> is larger than the wing area of the front wing <NUM>. Further, the wing width of the rear wing <NUM> is greater than the wing width of the front wing <NUM>. With such a configuration, when the aircraft <NUM> moves forward, the lift generated by the rear wing <NUM> is larger than the lift generated by the front wing <NUM>. That is, the rear wing <NUM> functions as a main wing of the aircraft <NUM>. The rear wing <NUM> is a swept wing that reduces air resistance. On the other hand, the front wing <NUM> functions as a canard wing of the aircraft <NUM>. The front wing <NUM> and the rear wing <NUM> also function as support members for supporting the two booms <NUM>.

Note that the lift generated by the rear wing <NUM> when the aircraft <NUM> moves forward and the lift generated by the front wing <NUM> when the aircraft <NUM> moves forward may be substantially the same. The magnitude relationship between the lift generated by the front wing <NUM> and the lift generated by the rear wing <NUM> is appropriately determined depending on the position of the center of gravity G, the attitude of the fuselage during cruising, and the like. Further, the size (the wing area, the length, and the like) of each of the front wing <NUM> and the rear wing <NUM> is determined so as to generate a desired lift.

The two booms <NUM> include a right boom <NUM> disposed on the right side of the fuselage <NUM>, and a left boom <NUM> disposed on the left side of the fuselage <NUM>. The two booms <NUM> form a pair and are arranged so as to be bilaterally symmetrical about a position overlapping the central axis A of the fuselage <NUM> in plan view. The two booms <NUM> function as support members for supporting the takeoff and landing rotors <NUM>.

The right boom <NUM> is a bar member that extends from the front toward the rear and is curved rightward (outward in the width direction) in an arc shape. The right boom <NUM> is connected to the right wing tip of the front wing <NUM> and is connected to the right wing of the rear wing <NUM> on the inner side of the elevon <NUM>. The front end of the right boom <NUM> is located forward of the front wing <NUM>. The rear end of the right boom <NUM> is located rearward of the rear wing <NUM>.

The left boom <NUM> is a bar member that extends from the front toward the rear and is curved leftward (outward in the width direction) in an arc shape. The left boom <NUM> is connected to the left wing tip of the front wing <NUM> and is connected to the left wing of the rear wing <NUM> on the inner side of the elevon <NUM>. The front end of the left boom <NUM> is located forward of the front wing <NUM>. The rear end of the left boom <NUM> is located rearward of the rear wing <NUM>.

The takeoff and landing rotors <NUM> each include a rotating mast (not shown) connected to an output shaft of an electric motor (not shown), and a propeller <NUM> attached to the rotating mast. The rotating mast is disposed so as to be parallel to the up-down direction and is rotatable about an axis extending in the up-down direction. The propeller <NUM> is located above the boom <NUM>, the front wing <NUM>, and the rear wing <NUM>. With such a structure, the propeller <NUM> is rotatable about an axis extending in the up-down direction. Each takeoff and landing rotor <NUM> generates lift by rotation of the propeller <NUM>.

The eight takeoff and landing rotors <NUM> include four takeoff and landing rotors 20a to 20d disposed on the right side of the fuselage <NUM>, and four takeoff and landing rotors 20a to 20d disposed on the left side of the fuselage <NUM>. The right-side takeoff and landing rotors 20a to 20d are supported by the right boom <NUM>. The left-side takeoff and landing rotors 20a to 20d are supported by the left boom <NUM>. Each of the right-side takeoff and landing rotors 20a to 20d and each of the left-side takeoff and landing rotors 20a to 20d form a pair, the position of each right-side takeoff and landing rotor and the position of the left-side takeoff and landing rotor paired with this right-side takeoff and landing rotor being the same in the front-rear direction.

As shown in <FIG>, the pair of takeoff and landing rotors 20a, the front wing <NUM>, the pair of takeoff and landing rotors 20b, the pair of takeoff and landing rotors 20c, the rear wing <NUM>, and the pair of takeoff and landing rotors 20d are arranged in this order from the front toward the rear in plan view. In other words, the pair of takeoff and landing rotors 20a are disposed forward of the front wing <NUM>. Further, the pair of takeoff and landing rotors 20b are disposed between the front wing <NUM> and the rear wing <NUM>, and are disposed forward of the pair of takeoff and landing rotors 20c. Furthermore, the pair of takeoff and landing rotors 20c are disposed between the front wing <NUM> and the rear wing <NUM>, and are disposed rearward of the pair of takeoff and landing rotors 20b. The pair of takeoff and landing rotors 20d are disposed rearward of the rear wing <NUM>. As shown in <FIG>, the takeoff and landing rotors 20a to 20d are disposed at the same height position.

Here, as shown in <FIG>, a distance between the fuselage <NUM> and each takeoff and landing rotor 20a in the width direction is defined as Dx. A distance between the fuselage <NUM> and each takeoff and landing rotor 20b in the width direction is defined as Dy. A distance between the fuselage <NUM> and each takeoff and landing rotor 20c in the width direction is defined as Dz. Note that the start point (or end point) of each of the distances Dx to Dz on the fuselage <NUM> side is a position on the outermost side of the outer surface of the fuselage <NUM> in plan view. Further, the start point (or end point) of each of the distances Dx to Dz on the takeoff and landing rotor <NUM> side is the position of the axis of the propeller <NUM>.

In the present embodiment, the takeoff and landing rotors <NUM> are arranged so that the following first condition and second condition are satisfied.

Note that the takeoff and landing rotors <NUM> may be arranged so that the following third condition is satisfied instead of the second condition. third condition: Dy < Dz.

Here, as shown in <FIG>, a distance between the pair of takeoff and landing rotors 20a is defined as Da. A distance between the pair of takeoff and landing rotors 20b is defined as Db. A distance between the pair of takeoff and landing rotors 20c is defined as Dc. A distance between the pair of takeoff and landing rotors 20d is defined as Dd. The start point and the end point of each of the distances Da to Dd are the positions of the axes of the propellers <NUM>.

In the present embodiment, the takeoff and landing rotors <NUM> are arranged so that the following fourth condition and fifth condition are satisfied in addition to the first to third conditions. fourth condition: Da < Db, Da < Dc, Dd < Db, Dd < Dc
fifth condition: Da = Dd, Db = Dc.

Note that the takeoff and landing rotors <NUM> may be arranged so that the following sixth condition is satisfied instead of the fifth condition. sixth condition: Da = Dd, Db < Dc.

In plan view, a center position Ca between the pair of takeoff and landing rotors 20a and a center position Cb between the pair of takeoff and landing rotors 20b are located forward of the center of gravity G. Further, in plan view, a center position Cc between the pair of takeoff and landing rotors 20c and a center position Cd between the pair of takeoff and landing rotors 20d are located rearward of the center of gravity G.

Here, as shown in <FIG>, in plan view, a distance between the center of gravity G and the center position Ca between the pair of takeoff and landing rotors 20a is defined as D01. In plan view, a distance between the center of gravity G and the center position Cb between the pair of takeoff and landing rotors 20b is defined as D02. In plan view, a distance between the center of gravity G and the center position Cc between the pair of takeoff and landing rotors 20c is defined as D03. In plan view, a distance between the center of gravity G and the center position Cd between the pair of takeoff and landing rotors 20d is defined as D04.

In the present embodiment, the takeoff and landing rotors <NUM> are arranged so that the following seventh condition is satisfied in addition to the first to sixth conditions. seventh condition: D02 < D01, D03 < D01, D02 < D04, D03 < D04.

Here, as shown in <FIG>, in plan view, a distance between a center position Cw of the rear wing <NUM> and the center position Cb between the pair of takeoff and landing rotors 20b is defined as D11. In plan view, a distance between the center position Cw of the rear wing <NUM> and the center position Cc between the pair of takeoff and landing rotors 20c is defined as D12. In plan view, a distance between the center position Cw of the rear wing <NUM> and the center position Cd between the pair of takeoff and landing rotors 20d is defined as D13. The center position Cw of the rear wing <NUM> may be the center of gravity of the rear wing <NUM>.

In the present embodiment, the takeoff and landing rotors <NUM> are arranged so that the following eighth condition is satisfied in addition to the first to seventh conditions. eighth condition: D12 < D11, D12 < D13.

As shown in <FIG>, the pair of takeoff and landing rotors 20a are disposed immediately forward of the front wing <NUM> in plan view. In plan view, a rotation range 48a of the propeller <NUM> of each of the takeoff and landing rotors 20a is in contact with or separated from the leading edge of the front wing <NUM>. Further, the pair of takeoff and landing rotors 20c are disposed immediately forward of the rear wing <NUM> in plan view. In plan view, a rotation range 48c of the propeller <NUM> of each of the takeoff and landing rotors 20c is in contact with or separated from the leading edge of the rear wing <NUM>. In this manner, according to the present embodiment, the rotation ranges 48a and 48c of the propellers <NUM> of the takeoff and landing rotors 20a and 20c disposed forward of the wings do not overlap the wings in plan view.

The two cruise rotors <NUM> are disposed on the rear portion 12r of the fuselage <NUM>. The position of each cruise rotor <NUM> in the left-right direction is on the inner side (the fuselage <NUM> side) of the position of each pair of takeoff and landing rotors <NUM> in the left-right direction. Further, the position of each cruise rotor <NUM> in the front-rear direction is between the pair of takeoff and landing rotors 20c and the pair of takeoff and landing rotors 20d. Furthermore, the position of the axis of each cruise rotor <NUM> in the up-down direction is lower than the position of the propeller <NUM> of each takeoff and landing rotor <NUM> in the up-down direction.

As shown in <FIG>, the cruise rotors <NUM> each include a rotating mast (not shown) connected to an output shaft of an electric motor (not shown), a propeller <NUM> attached to a front end portion of the rotating mast, and a cylindrical duct <NUM> surrounding the propeller <NUM>. The positions of the two cruise rotors <NUM> coincide with each other in both the front-rear direction and the up-down direction. Further, the two cruise rotors <NUM> are arranged side by side in the left-right direction. One of the cruise rotors <NUM> is disposed on the right side of a position overlapping the central axis A of the fuselage <NUM> in plan view, and is supported by the right wing of the rear wing <NUM>. The other cruise rotor <NUM> is disposed on the left side of the position overlapping the central axis A of the fuselage <NUM> in plan view, and is supported by the left wing of the rear wing <NUM>. The rotating mast is located below the rear wing <NUM> so as to be parallel to the front-rear direction, and is rotatable about an axis extending in the front-rear direction. With such a structure, the propeller <NUM> is rotatable about an axis extending in the front-rear direction. Each cruise rotor <NUM> generates thrust by rotation of the propeller <NUM>.

The takeoff and landing rotors <NUM> are used when the aircraft <NUM> takes off, lands, and hovers. On the other hand, the cruise rotors <NUM> are used when the aircraft <NUM> is cruising. Further, the takeoff and landing rotors <NUM> and the cruise rotors <NUM> are used together when the aircraft <NUM> transitions from hovering to cruising and moves forward at a first speed (≥ <NUM>/h) or more and less than a second speed (> first speed). In this case, the usage rate of the cruise rotors <NUM> is gradually increased for acceleration. Since the lift generated by the wing increases with acceleration, the usage rate of the takeoff and landing rotors <NUM> is gradually decreased. For example, the usage rate of the takeoff and landing rotors <NUM> is decreased by decreasing the rotational speed of the takeoff and landing rotors <NUM> to reduce the lift. Alternatively, the usage rate of the takeoff and landing rotors <NUM> is decreased by changing the pitch angle of respective blades to reduce the lift.

In addition, the takeoff and landing rotors <NUM> and the cruise rotors <NUM> are used together when the aircraft <NUM> transitions from cruising to hovering and moves forward at a third speed (≥ <NUM>/h) or more and less than a fourth speed (> third speed). In this case, the usage rate of the cruise rotors <NUM> is gradually decreased for deceleration. Since the lift generated by the wing decreases with deceleration, the usage rate of the takeoff and landing rotors <NUM> is gradually increased. For example, the usage rate of the takeoff and landing rotors <NUM> is increased by increasing the rotational speed of the takeoff and landing rotors <NUM> to increase the lift. Alternatively, the usage rate of the takeoff and landing rotors <NUM> is increased by changing the pitch angle of respective blades to increase the lift.

The aircraft <NUM> may include four takeoff and landing rotors <NUM>, namely, two pairs of takeoff and landing rotors <NUM>. In this case, the first pair of takeoff and landing rotors <NUM> are disposed forward of the front wing <NUM> in plan view. Further, the second pair of takeoff and landing rotors <NUM> are disposed between the front wing <NUM> and the rear wing <NUM> in plan view.

In the same manner as in the above-described embodiment, in the first modification, the takeoff and landing rotors <NUM> are arranged so that the distance, in the width direction, between the fuselage <NUM> and each of the takeoff and landing rotors <NUM> disposed between the front wing <NUM> and the rear wing <NUM> is longer than the distance, in the width direction, between the fuselage <NUM> and each of the takeoff and landing rotors <NUM> disposed forward of the front wing <NUM>.

The aircraft <NUM> may include six takeoff and landing rotors <NUM>, namely, three pairs of takeoff and landing rotors <NUM>. In this case, the first pair of takeoff and landing rotors <NUM> are disposed forward of the front wing <NUM> in plan view. Further, the second pair of takeoff and landing rotors <NUM> are disposed between the front wing <NUM> and the rear wing <NUM> in plan view. Furthermore, the third pair of takeoff and landing rotors <NUM> are disposed rearward of the rear wing <NUM> in plan view.

In the same manner as in the above-described embodiment, in the second modification, the takeoff and landing rotors <NUM> are arranged so that the distance, in the width direction, between the fuselage <NUM> and each of the takeoff and landing rotors <NUM> disposed between the front wing <NUM> and the rear wing <NUM> is longer than the distance, in the width direction, between the fuselage <NUM> and each of the takeoff and landing rotors <NUM> disposed forward of the front wing <NUM>.

Further, the takeoff and landing rotors <NUM> are arranged so that the distance between the second pair of takeoff and landing rotors <NUM> disposed between the front wing <NUM> and the rear wing <NUM> is longer than the distance between the first pair of takeoff and landing rotors <NUM> disposed forward of the front wing <NUM> and the distance between the third pair of takeoff and landing rotors <NUM> disposed rearward of the rear wing <NUM>.

The aircraft <NUM> may include ten or more takeoff and landing rotors <NUM>, namely, five or more pairs of takeoff and landing rotors <NUM>. In this case, at least one pair of takeoff and landing rotors <NUM> are disposed forward of the front wing <NUM> in plan view. Further, at least one pair of takeoff and landing rotors <NUM> are disposed between the front wing <NUM> and the rear wing <NUM> in plan view. Furthermore, at least one pair of takeoff and landing rotors <NUM> are disposed rearward of the rear wing <NUM> in plan view.

In the same manner as in the above-described embodiment, in the third modification, the takeoff and landing rotors <NUM> are arranged so that the distance, in the width direction, between the fuselage <NUM> and each of the takeoff and landing rotors <NUM> disposed between the front wing <NUM> and the rear wing <NUM> is longer than the distance, in the width direction, between the fuselage <NUM> and each of the takeoff and landing rotors <NUM> disposed forward of the front wing <NUM>.

Further, the takeoff and landing rotors <NUM> are arranged so that the distance between the pair of takeoff and landing rotors <NUM> disposed between the front wing <NUM> and the rear wing <NUM> is longer than the distance between the pair of takeoff and landing rotors <NUM> disposed forward of the front wing <NUM> and the distance between the pair of takeoff and landing rotors <NUM> disposed rearward of the rear wing <NUM>.

The technical idea that can be grasped from the above embodiment will be described below.

According to a first example not covered by the presently claimed invention, provided is the aircraft <NUM> including: the fuselage <NUM>; the front wing <NUM> connected to the front portion 12f of the fuselage <NUM> and configured to generate lift when the aircraft moves in the horizontal direction; the rear wing <NUM> connected to the rear portion 12r of the fuselage <NUM> and configured to generate lift when the aircraft moves in the horizontal direction; and four or more rotors (the takeoff and landing rotors <NUM>) configured to generate lift, wherein the four or more rotors include: the pair of first rotors (the takeoff and landing rotors 20a) disposed forward of the front wing <NUM> so as to be bilaterally symmetrical about the position overlapping the central axis A of the fuselage <NUM> in plan view; and the pair of second rotors (the takeoff and landing rotors 20b, 20c) disposed between the front wing <NUM> and the rear wing <NUM> so as to be bilaterally symmetrical about the position overlapping the central axis A of the fuselage <NUM> in plan view, and wherein the distance (Dy, Dz) between the fuselage <NUM> and each of the second rotors in the width direction is longer than the distance (Dx) between the fuselage <NUM> and each of the first rotors in the width direction.

According to the above configuration, it is possible to suppress a decrease in the lift generated by the rear wing <NUM> due to the operation of the second rotors (the takeoff and landing rotors 20b, 20c) for the following reason. When the aircraft <NUM> moves in the horizontal direction while using the second rotors (for example, when transitioning from hovering to cruising), a downward air flow is generated in accordance with the operation of the second rotors, and air is guided from the front to the rear wing <NUM> in accordance with the movement in the horizontal direction. In the above configuration, at least the distance (Dy, Dz) between the fuselage <NUM> and each second rotor in the width direction is longer than the distance (Dx) between the fuselage <NUM> and each first rotor (the takeoff and landing rotor 20a) in the width direction. That is, a relatively large space is formed between the fuselage <NUM> and each second rotor. Accordingly, the flow of air guided from the front to the vicinity of the connection portion between the rear wing <NUM> and the fuselage <NUM> does not interfere with the downward air flow generated in accordance with the operation of the second rotors. Therefore, according to the above configuration, it is possible to smoothly guide the air flowing from the front, to the vicinity of the connection portion between the rear wing <NUM> and the fuselage <NUM> where the largest lift is generated, and as a result, it is possible to suppress a decrease in the lift generated by the rear wing <NUM>.

In said first example not covered by the presently claimed invention, the distance (Db, Dc) between the pair of second rotors may be longer than the distance (Da) between the pair of first rotors.

In said first example not covered by the presently claimed invention, the center of gravity G of the aircraft <NUM> may be located between the front wing <NUM> and the rear wing <NUM>, and the distance (D02, D03), in the front-rear direction, between the center of gravity G and the center position Cb, Cc between the pair of second rotors may be shorter than the distance (D01), in the front-rear direction, between the center of gravity G and the center position Ca between the pair of first rotors.

According to the above configuration, the attitude of the aircraft <NUM> can be stabilized for the following reason. As the distance between the rotor for generating lift and the center of gravity G of the aircraft <NUM> increases, the moment of the lift about the center of gravity G increases. In the above configuration, the pair of first rotors (the takeoff and landing rotors 20a) are disposed farther from the center of gravity G than the pair of second rotors (the takeoff and landing rotors 20b, 20c). Therefore, the moment of the lift about the center of gravity G generated by the pair of first rotors is larger than the moment of the lift about the center of gravity G generated by the pair of second rotors. Further, the moment in the roll direction increases as the distance between the pair of first rotors and the fuselage <NUM> increases. In the above configuration, the pair of first rotors disposed away from the center of gravity G are closer to the fuselage <NUM> than the pair of second rotors disposed close to the center of gravity G. That is, the fuselage <NUM> and each first rotor are relatively close to each other. Therefore, the moment in the roll direction is relatively small. Thus, according to the above configuration, the attitude of the aircraft <NUM> can be stabilized.

In said first example not covered by the presently claimed invention, the aircraft may include the pair of bar members (the booms <NUM>) disposed so as to be bilaterally symmetrical about the position overlapping the central axis A of the fuselage <NUM> in plan view, and the pair of bar members may be connected to the front wing <NUM> and the rear wing <NUM>, may be curved outward in the width direction, and may support the pair of first rotors and the pair of second rotors.

According to the above configuration, since both the front wing <NUM> and the rear wing <NUM> support the bar members (the booms <NUM>), it is not necessary to increase the rigidity of the bar members compared to a case where only one of the front wing <NUM> or the rear wing <NUM> supports the bar members.

In said first example not covered by the presently claimed invention, the rear wing <NUM> may be a swept wing, and the wing area of the rear wing <NUM> may be larger than the wing area of the front wing <NUM>, or the wing width of the rear wing <NUM> may be greater than the wing width of the front wing <NUM>.

According to the above configuration, since the rear wing <NUM> is a swept wing, disposing each second rotor (the takeoff and landing rotor 20c) on the outer side in the width direction makes it easier to separate the rotation range 48c of the propeller <NUM> of the second rotor and the leading edge of the rear wing <NUM> from each other in the front-rear direction in plan view. Therefore, the downward air flow generated in accordance with the operation of the second rotors is less likely to interfere with the rear wing <NUM>.

According to a second example not covered by the presently claimed invention, provided is the aircraft <NUM> including: the fuselage <NUM>; the front wing <NUM> connected to the front portion 12f of the fuselage <NUM> and configured to generate lift when the aircraft moves in the horizontal direction; the rear wing <NUM> connected to the rear portion 12r of the fuselage <NUM> and configured to generate lift when the aircraft moves in the horizontal direction; and four or more rotors (the takeoff and landing rotors <NUM>) configured to generate lift, wherein the four or more rotors include the pair of first rotors (the takeoff and landing rotors 20b) and the pair of second rotors (the takeoff and landing rotors 20c), the pair of first rotors and the pair of second rotors each being disposed so as to be bilaterally symmetrical about the position overlapping the central axis A of the fuselage <NUM> in plan view, and wherein the distance (D12), in the front-rear direction, between the center position Cw of the rear wing <NUM> and the center position Cc between the pair of second rotors is shorter than the distance (D11), in the front-rear direction, between the center position Cw of the rear wing <NUM> and the center position Cb between the pair of first rotors, and the distance (Dz) between the fuselage <NUM> and each of the second rotors in the width direction is longer than the distance (Dy) between the fuselage <NUM> and each of the first rotors in the width direction.

In the above configuration, at least the distance (Dz) between the fuselage <NUM> and each second rotor (the takeoff and landing rotor 20c) in the width direction is longer than the distance (Dy) between the fuselage <NUM> and each first rotor (the takeoff and landing rotor 20b) in the width direction. That is, a relatively large space is formed between the fuselage <NUM> and each second rotor. Accordingly, the flow of air guided from the front to the vicinity of the connection portion between the rear wing <NUM> and the fuselage <NUM> does not interfere with the downward air flow generated in accordance with the operation of the second rotors. Therefore, according to the above configuration, it is possible to smoothly guide the air flowing from the front, to the vicinity of the connection portion between the rear wing <NUM> and the fuselage <NUM> where the largest lift is generated, and as a result, it is possible to suppress a decrease in the lift generated by the rear wing <NUM>.

According to a third example not covered by the presently claimed invention, provided is the aircraft <NUM> including: the fuselage <NUM>; the front wing <NUM> connected to the front portion 12f of the fuselage <NUM> and configured to generate lift when the aircraft moves in the horizontal direction; the rear wing <NUM> connected to the rear portion 12r of the fuselage <NUM> and configured to generate lift when the aircraft moves in the horizontal direction; and six or more rotors (the takeoff and landing rotors <NUM>) configured to generate lift, wherein the six or more rotors include: the pair of first rotors (the takeoff and landing rotors 20a) disposed forward of the front wing <NUM> so as to be bilaterally symmetrical about the position overlapping the central axis A of the fuselage <NUM> in plan view; the pair of second rotors (the takeoff and landing rotors 20b, 20c) disposed between the front wing <NUM> and the rear wing <NUM> so as to be bilaterally symmetrical about the position overlapping the central axis A of the fuselage <NUM> in plan view; and the pair of third rotors (the takeoff and landing rotors 20d) disposed rearward of the rear wing <NUM> so as to be bilaterally symmetrical about the position overlapping the central axis A of the fuselage <NUM> in plan view, and wherein the distance (Db, Dc) between the pair of second rotors is longer than the distance (Da) between the pair of first rotors and the distance (Dd) between the pair of third rotors.

In the above configuration, at least the distance (Db, Dc) between the pair of second rotors (the takeoff and landing rotors 20b, 20c) is longer than the distance (Da) between the pair of first rotors (the takeoff and landing rotors 20a) and the distance (Dd) between the pair of third rotors (the takeoff and landing rotors 20d). That is, a relatively large space is formed between the fuselage <NUM> and each second rotor. Accordingly, the flow of air guided from the front to the vicinity of the connection portion between the rear wing <NUM> and the fuselage <NUM> does not interfere with the downward air flow generated in accordance with the operation of the second rotors. Therefore, according to the above configuration, it is possible to smoothly guide the air flowing from the front, to the vicinity of the connection portion between the rear wing <NUM> and the fuselage <NUM> where the largest lift is generated, and as a result, it is possible to suppress a decrease in the lift generated by the rear wing <NUM>.

In addition, according to the above configuration, the width of the aircraft <NUM> on the front side and the rear side thereof can be reduced. Accordingly, the aircraft <NUM> can be stored in a small space.

Claim 1:
An aircraft (<NUM>) comprising:
a fuselage (<NUM>);
a front wing (<NUM>) connected to a front portion (12f) of the fuselage and configured to generate lift when the aircraft moves in a horizontal direction;
a rear wing (<NUM>) connected to a rear portion (12r) of the fuselage and configured to generate lift when the aircraft moves in the horizontal direction; and
four or more rotors (<NUM>) configured to generate lift,
wherein the four or more rotors include:
a pair of first rotors (20a) disposed forward of the front wing so as to be bilaterally symmetrical about a position overlapping a central axis (A) of the fuselage in plan view; and
a pair of second rotors (20b, 20c) disposed between the front wing and the rear wing so as to be bilaterally symmetrical about the position overlapping the central axis of the fuselage in the plan view, and
wherein a distance (Dy, Dz) between the fuselage and each of the second rotors in a width direction is longer than a distance (Dx) between the fuselage and each of the first rotors in the width direction,
characterized in that
the aircraft further comprises a pair of bar members (<NUM>) disposed so as to be bilaterally symmetrical about the position overlapping the central axis of the fuselage in the plan view, wherein
the pair of bar members are connected to the front wing and the rear wing, are curved outward in the width direction, and support the pair of first rotors and the pair of second rotors.