Flying body and thrust deflection device

Abstract

A flying body according to the present invention comprises: an airframe; a plurality of ducted fans that generate thrust for the airframe; and a thrust deflection device that covers a lower opening in the ducted fans from below and can change the travel direction of air pushed out from the ducted fans. The thrust deflection device comprises: a plurality of louver units that have a plurality of louvers, which extend in a first direction intersecting the axis of a duct and are disposed at intervals in a second direction intersecting both the axis of the duct and the first direction; an actuator that can adjust angles about the axes of the plurality of louver units; and a frame part that supports the plurality of louver units such that the axes of the plurality of louver units do not intersect each other within the duct when viewed from below.

Description

Aircraft and Thrust Deflection Device

[0001] The present disclosure relates to an aircraft and a thrust deflection device. This application claims priority to Japanese Patent Application No. 2024-195106 filed in Japan on November 7, 2024, the content of which is incorporated herein by reference.

[0002] Unmanned aircraft such as multicopters and drones are known. Patent Document 1 discloses an aircraft using a ducted fan as an unmanned aircraft. This aircraft of Patent Document 1 has a thrust deflection device that deflects the air sucked by the ducted fan. This thrust deflection device has louvers at every 90° in the circumferential direction centered on the rotation axis of the fan for one duct. These louvers form an X shape when viewed from below and can deflect thrust forward, backward, left, and right. Each louver is swingable about an axis extending in the radial direction centered on the rotation axis of the fan. The angle of each louver can be individually adjusted by an actuator.

[0003] International Publication No. 2017 / 145622

[0004] In a thrust change device using louvers arranged in an X shape as described in Patent Document 1, the air blown out at a position away from the louvers does not contribute to thrust deflection, and the lateral force generated by thrust deflection is small. On the other hand, if the lateral force is increased, there is a problem that the thrust deflection device becomes large.

[0005] The present disclosure has been made in view of the above circumstances, and provides an aircraft and a thrust deflection device capable of increasing the lateral force generated by thrust deflection while suppressing an increase in size.

[0006] To solve the above problems, the following configuration is adopted. The aircraft of this disclosure comprises an aircraft body, a plurality of ducted fans having fans in a duct and generating thrust for the aircraft by pushing the sucked air downward from the lower opening of the duct, and a thrust deflection device that covers the lower opening from below and can change the direction of travel of the air pushed out from the ducted fans, wherein the thrust deflection device comprises a plurality of louver units having a plurality of louvers extending in a first direction intersecting the axis of the duct and spaced apart in a second direction intersecting both the axis of the duct and the first direction, and a base portion that supports the plurality of louvers, a frame portion that supports the plurality of louver units so that each of them can rotate around an axis extending in the first direction, and an actuator that can adjust the angle of the plurality of louver units around the axis, wherein the frame portion supports the plurality of louver units such that the axes of each of the plurality of louver units do not intersect within the duct when viewed from below.

[0007] The thrust vectoring device of the present disclosure is a thrust vectoring device for an aircraft having an aircraft body and a plurality of ducted fans that generate thrust for the aircraft by pushing in sucked air downward from a lower opening of a duct, and comprises a plurality of louver units having a plurality of louvers extending in a first direction and arranged at intervals in a second direction intersecting the first direction and a base portion that supports the plurality of louvers, a frame portion that supports the plurality of louver units so as to be rotatable about an axis extending in the first direction and supports the plurality of louver units in a state arranged in series in the second direction, and an actuator that can adjust the angle of the plurality of louver units about the axis.

[0008] According to this disclosure, it is possible to increase the lateral force generated by thrust deflection while keeping the size of the device under control.

[0009] This is a plan view showing the schematic configuration of an aircraft in an embodiment of the present disclosure. This is a perspective view of a ducted fan in an embodiment of the present disclosure. This is a perspective view of a ducted fan in an embodiment of the present disclosure. This is a side view of a ducted fan and thrust vectoring device in an embodiment of the present disclosure, viewed from a first direction. This is a side view of a ducted fan and thrust vectoring device in an embodiment of the present disclosure, viewed from a second direction. This is a view of a ducted fan and thrust vectoring device in an embodiment of the present disclosure, viewed from below. This is a partial cross-sectional view showing the arrangement of louvers in the thrust vectoring device. This is a diagram showing the state in which the louver unit is rotated to one maximum angle. This is a diagram showing the state in which the louver unit is rotated to the other maximum angle. This is a diagram showing the arrangement of louvers in a modified example of an embodiment of the present disclosure.

[0010] <Embodiments> Next, the aircraft and thrust vectoring device in the embodiments of this disclosure will be described with reference to the drawings. The aircraft in this embodiment is used, for example, to transport cargo. The aircraft can also be used to transport items other than cargo.

[0011] (Configuration of the aircraft) Figure 1 is a plan view showing the schematic configuration of the aircraft in an embodiment of the present disclosure. As shown in Figure 1, the aircraft 1 of this embodiment comprises an airframe 10, a ducted fan 20, and a thrust vectoring device 30. In this embodiment, the case in which four ducted fans 20 are connected to one airframe 10 will be described as an example. The number of ducted fans 20 connected to the airframe 10 may be three, five or more.

[0012] (Aircraft Structure) The aircraft 10 has a circular, polygonal, rectangular, or other shape centered on the central axis X in a plan view. In this embodiment, an aircraft 10 having a polygonal shape in a plan view is shown as an example. The central axis X here refers to the line passing through the geometric center of gravity of the aircraft 10. Although detailed explanation is omitted, the aircraft 10 is equipped with various devices such as a transceiver, battery, and gyro sensor.

[0013] (Configuration of the ducted fan) Figure 2 is a perspective view of a ducted fan in an embodiment of the present disclosure. Figure 3 is a perspective view of a ducted fan in an embodiment of the present disclosure. As shown in Figures 2 and 3, the ducted fan 20 comprises a duct 21, a fan 22, and a fixed arm 23.

[0014] (Duct) The duct 21 is cylindrical with an axis L1 as its center. The duct 21 has an upper opening 21a and a lower opening 21b. The duct 21 illustrated in this embodiment has a cylindrical shape with a circular cross-sectional contour. In this embodiment, the case in which the upper opening 21a and the lower opening 21b have the same diameter is illustrated. Furthermore, in the duct 21 of this embodiment, the inner and outer diameters of the cylinder are larger than the height in the direction in which the axis L1 extends. Note that the size and shape of the duct 21 can be changed as appropriate.

[0015] (Fan) Figure 4 is a side view of a ducted fan and thrust deflection device in an embodiment of the present disclosure, viewed from a first direction. The fan 22 is installed inside the duct 21. As shown in Figures 2 to 4, the fan 22 has a propeller 24 and a prime mover 25 (see Figure 4), and the propeller 24 is driven by the rotational energy output from the prime mover 25. The propeller 24 includes a hub 26 rotatably arranged on an axis L1, and a plurality of blades 27 extending radially from the hub 26 around the axis L1. For example, the prime mover 25 is supported in the duct 21, and the hub 26 is connected to the output shaft of the prime mover 25. An electric motor or an internal combustion engine can be used as the prime mover 25. The prime mover 25 can be controlled for rotational speed and other functions according to a signal received by a transceiver.

[0016] (Fixed Arm) The fixed arm 23 connects the duct 21 and the machine body 10. In this embodiment, the fixed arm 23 is connected to the duct 21 via the frame portion 50 (described later), while being fixed to the machine body 10 by fastening members such as screws. The fixed arm 23 transmits the thrust generated by driving the fan 22 from the duct 21 to the machine body 10.

[0017] (Operation of the ducted fan) With the ducted fan 20 configured as described above, when the propeller 24 is rotated by the prime mover 25, air is drawn into the duct 21 from the upper opening 21a. The air drawn into the duct 21 then passes through the propeller 24 and is pushed out downward along the axis L1 from the lower opening 21b. This air pushed out from the lower opening 21b becomes a thrust that pushes the ducted fan 20 upward. This thrust is transmitted to the aircraft body 10 via the fixed arm 23, so when sufficient upward thrust is obtained, the aircraft body 10 rises together with the ducted fan 20. In this embodiment, the case where the fan 22 is a so-called axial flow fan is illustrated, but the fan 22 is not limited to an axial flow fan as long as it is a fan capable of generating thrust by pushing air out from the lower opening 21b.

[0018] Figure 5 is a side view of the ducted fan and thrust deflection device in an embodiment of the present disclosure, viewed from a second direction. Figure 6 is a view of the ducted fan and thrust deflection device in an embodiment of the present disclosure, viewed from below. (Thrust Deflection Device) The thrust deflection device 30 is capable of changing the direction of travel of the air pushed out from the ducted fan 20. As shown in Figures 2 to 6, the thrust deflection device 30 is positioned to cover the lower opening 21b of the ducted fan 20 from below. The thrust deflection device 30 comprises a plurality of louver units 40, a frame portion 50, and an actuator 60. In this embodiment, the contour of the thrust deflection device 30 viewed from below (see Figure 6) is generally rectangular, and when viewed from below, the entire inner circumferential surface of the duct 21 is positioned inside the contour of the thrust deflection device 30. Although the example shows a thrust vectoring device 30 installed on all ducted fans 20, the thrust vectoring device 30 may be installed on only some of the ducted fans 20.

[0019] (Configuration of the louver unit) The louver unit 40 comprises a plurality of louvers 41 and a base portion 42. In this embodiment, two louver units 40 are provided on one thrust deflection device 30. In other words, the two louver units 40 are arranged horizontally so as to cover the area below the lower opening 21b of the duct 21. Note that the number of louver units 40 on one thrust deflection device 30 is not limited to two. For example, three or more louver units 40 may be provided on one thrust deflection device 30.

[0020] (Louver configuration) As shown in Figure 5, when the direction of air pushed out from the ducted fan 20 is not changed (hereinafter simply referred to as the initial position), the multiple louvers 41 of the louver unit 40 each extend in a first direction D1 that intersects with the axis L1 of the duct 21. The multiple louvers 41 are then arranged in a line with spacing between them in a second direction D2 that intersects with both the axis L1 of the duct 21 and the first direction D1. In this embodiment, the louver unit 40 is illustrated with equal spacing between the multiple louvers 41 in the second direction D2, but it is not limited to equal spacing.

[0021] The louvers 41 in this embodiment are plate-shaped with the first direction D1 as the longitudinal direction and the direction perpendicular to the axis L1 of the duct 21 in the initial position (in other words, the second direction D2) as the thickness direction. The thickness of the louvers 41 is smaller than the distance between adjacent louvers 41. In addition, the length of each of the multiple louvers 41 in the axial direction Da (in other words, the vertical direction) along the axis L1 is constant. Here, the specific thickness and length of the louvers 41 can be appropriately set according to the required deflection performance.

[0022] Furthermore, in this embodiment, the positions of the first ends 45 and second ends 46 of the multiple louvers 41 provided on a single louver unit 40 are aligned in the first direction D1. In other words, the first ends 45 of each of the multiple louvers 41 are positioned at the same location in the first direction D1, and the second ends 46 of each of the multiple louvers 41 are positioned at the same location in the first direction D1. Note that the positions of the first ends 45 and second ends 46 of the louvers 41 are not limited to the above-mentioned same locations.

[0023] Furthermore, the distance from the first end 45 to the second end 46 of each of the multiple louvers 41 in this embodiment is the same as or slightly longer than the inner diameter of the duct 21. In this embodiment, the case in which five louvers 41 are provided in one louver unit 40 is illustrated. However, one louver unit 40 may be provided with two or more but less than four louvers 41, or with six or more louvers 41.

[0024] (Outer louvers, inner louvers) Figure 7 is a partial cross-sectional view showing the arrangement of louvers in the thrust deflection device described above. As shown in Figure 7, the multiple louvers 41 that make up one louver unit 40 include outer louvers 41a and inner louvers 41b. Two outer louvers 41a are provided in each louver unit 40. These two outer louvers 41a are the louvers 41 that are positioned furthest out in the second direction D2 among the multiple louvers 41 provided in one louver unit 40.

[0025] The inner louver 41b is positioned between the two outer louvers 41a. The inner louver 41b is positioned closer to the duct 21 than the outer louvers 41a in the axial direction Da along which the axis L1 of the duct 21 extends. The louver unit 40 in this embodiment has three inner louvers 41b, and the two inner louvers 41b on either side of the centrally located inner louver 41b are positioned closer to the lower opening 21b of the duct 21.

[0026] (Notch) As shown in Figure 6, the ducted fan 20 is provided with a central projection 28 that protrudes downward along the axis L1 of the duct 21. The outer louver 41a positioned closest to the axis L1 of the duct 21 in the second direction D2 is provided with a notch 47 to avoid the central projection 28. In other words, when the louver unit 40 is rotated around the axis L2, as will be described later, and the outer louver 41a on the side of the louver unit 40 closer to the axis L1 is displaced in a direction closer to the duct 21 (see Figures 8 and 9), the notch 47 is provided so that the outer louver 41a does not come into contact with the central projection 28. The central projection 28 may be a so-called tail cone that allows the air pushed out from the lower opening 21b to flow smoothly along the axis L1.

[0027] (Configuration of the base portion) The base portion 42 supports a plurality of louvers 41. More specifically, the base portion 42 supports the plurality of louvers 41 with spacing between them in the second direction D2. The base portion 42 of this embodiment has a first bracket 43 to which the first ends 45 of the plurality of louvers 41 are each fixed, and a second bracket 44 to which the second ends 46 of the plurality of louvers 41 are each fixed.

[0028] The first bracket 43 and the second bracket 44 are plate-shaped with the first direction D1 as the thickness direction. The first bracket 43 and the second bracket 44 extend in the second direction D2 to connect the upper ends of the multiple louvers 41 and are arranged parallel to each other. As will be described in detail later, the multiple louvers 41 that make up the louver unit 40 of this embodiment have different heights for adjacent louvers 41 in the second direction D2. Therefore, the first bracket 43 and the second bracket 44 each form an M shape (see Figure 5) when viewed from the first direction D1.

[0029] (Frame section) As shown in Figures 4 to 6, the frame section 50 supports a plurality of louver units 40 so that each can rotate around an axis L2 extending in the first direction D1. Furthermore, the frame section 50 supports the plurality of louver units 40 in such a way that, when viewed from below, the axes L2 of each of the plurality of louver units 40 do not intersect within the duct 21. In this embodiment, the frame section 50 supports two louver units 40 in such a way that, when viewed from below, the axes L2 of the two louver units 40 do not intersect on the inner side of the outer circumferential surface of the duct 21. Furthermore, in this embodiment, the axes L2 of the two louver units 40 supported by the frame section 50 extend parallel to each other. Note that in this embodiment, the axis L2 is set at the center or slightly offset from the center of the first bracket 43 and the second bracket 44 in the second direction D2.

[0030] Figure 8 shows the state in which the louver unit has been rotated to the maximum angle of one side. Figure 9 shows the state in which the louver unit has been rotated to the maximum angle of the other side. As shown in Figures 7 to 9, the frame portion 50 supports the two louver units 40 separated in the second direction D2 so that the two louver units 40 do not interfere with each other when the two louver units 40 are rotated from their initial position to the maximum angle (for example, about 45°). In this embodiment, the frame portion 50 illustrates the case in which, at the initial position, the distance between the two louver units 40 in the second direction D2 is the same as the distance between the louvers 41. It is preferable to set the distance between the two louver units 40 in the second direction D2 at the initial position as short as possible, provided that no interference occurs between the louver units 40.

[0031] As shown in Figure 6, the frame portion 50 in this embodiment includes a first support portion 51 and a second support portion 52. The first support portion 51 rotatably supports the first end portion 40a of the louver unit 40 in the first direction D1. The second support portion 52 supports the actuator 60 and, via the actuator 60, supports the second end portion 40b of the louver unit 40 in the first direction D1. In other words, the frame portion 50 of this embodiment sandwiches the two louver units 40 from the outside in the first direction D1 by the first support portion 51 and the second support portion 52, and rotatably supports the two louver units 40. In this embodiment, the frame portion 50 is positioned with the second support portion 52 on the side closer to the fixed arm 23 when viewed from below, and the first support portion 51 on the opposite side, which is further from the fixed arm 23.

[0032] (First support section) As shown in Figures 2 and 5, the first support section 51 comprises a base section 53 and an arm section 54. The base section 53 is fixed to the duct 21. The arm section 54 extends downward from the base section 53. The arm section 54 branches out in multiple directions from the base section 53 in a second direction D2. In this embodiment, the arm section 54 branches out in two directions from the base section 53 in a second direction D2. These multiple arm sections 54 rotatably support the first brackets 43 of adjacent louver units 40 around the axis L2.

[0033] The thrust deflection device 30 of this embodiment is equipped with a rotating shaft 70 on the louver unit 40. A bearing portion 71 supporting the rotating shaft 70 is provided at the lower part of each of the two arm portions 54. In the first support portion 51 of this embodiment, a base portion 53 is positioned at the center of the two bearing portions 71 in the first direction D1. In other words, the two arm portions 54 are formed symmetrically in the first direction D1 with respect to the base portion 53.

[0034] (Second Support Section) As shown in Figures 3 and 4, the second support section 52 comprises a base section 56 and an actuator support section 57. The base section 56 is fixed to the duct 21 and connected to the fixing arm 23. The actuator support section 57 is ring-shaped and elongated in the second direction D2. The actuator support section 57 has an inner circumferential surface capable of fixing multiple actuators 60. In this embodiment, the height of the ring-shaped inner circumferential surface of the actuator support section 57 is the same as or slightly greater than the height of the two actuators 60. In this embodiment, the two actuators 60 are fixed to the actuator support section 57 in a state where they are in contact with the first end and the second end of the inner circumferential surface of the actuator support section 57 in the second direction D2, respectively.

[0035] Here, the outer louver 41a located furthest from the axis L1 of the duct 21 in the second direction D2 is positioned outside the inner surface of the duct 21 in the radial direction centered on the axis L1 of the duct 21. More specifically, in the initial position, the shortest distance from the axis L1 to the outermost louver 41 of the louver unit 40 is greater than the radius of the inner surface of the duct 21. As a result, the air pushed downward from the duct 21 passes inside the outer louver 41a, thus preventing the air from passing through without being deflected by the thrust deflection device 30.

[0036] (Actuator) The actuator 60 can adjust the angle of the multiple louver units 40 around the axis L2. For example, a servo motor can be used as the actuator 60. In this embodiment, one actuator 60 is provided for each louver unit 40. The actuator 60 in this embodiment adjusts the angle of the multiple louver units 40 around the axis L2 so that it corresponds to the angle of the received signal from the transceiver (not shown) mounted on the machine body 10.

[0037] The actuator 60 in this embodiment has an output shaft 60a (see Figure 4). The output shaft 60a of this actuator 60 is connected to the second bracket 44 of the base portion 42 of the louver unit 40. Although the example described is one actuator 60 provided for one louver unit 40, one actuator 60 may be provided for multiple louver units 40. In this case, a transmission mechanism (not shown) can be provided to divide and transmit the output of one actuator 60 to multiple louver units 40.

[0038] (Effects) In the above embodiment, the frame portion 50 supports the multiple louver units 40 so that each can rotate around an axis L2 extending in the first direction D1. Furthermore, the frame portion 50 supports the multiple louver units 40 so that, when viewed from below, the axes L2 of each of the multiple louver units 40 do not intersect within the duct 21. In addition, the actuator 60 makes it possible to adjust the angle of the multiple louver units 40 around the axis L2. As a result, the rotation radius of each louver unit 40 can be reduced compared to, for example, the case where the lower opening 21b is covered from below by a single louver unit. And, as the rotation radius of the louver unit 40 is reduced, when the distance between the lower opening 21b of the duct 21 and the thrust deflection device 30 is kept constant, the maximum rotatable angle of the louver unit 40 can be increased compared to the case where the lower opening 21b is covered from below by a single louver unit. On the other hand, if the maximum rotatable angle is kept constant, the rotation radius of the louver unit 40 becomes smaller, allowing the thrust vectoring device 30 to be positioned closer to the lower opening 21b of the duct 21. This reduces the amount of air leaking between the lower opening 21b and the thrust vectoring device 30 without contributing to thrust vectoring. Furthermore, because the rotation radius of the louver unit 40 can be reduced, the holding torque of the louver unit 40 can be reduced, and the actuator 60 can be miniaturized. Therefore, it becomes possible to increase the lateral force generated when the thrust of the ducted fan 20 is vectored while suppressing the enlargement of the thrust vectoring device 30 and the aircraft 1.

[0039] Furthermore, in the above embodiment, among the multiple louvers 41 of the louver unit 40, the inner louver 41b is positioned between the two outermost louvers 41a located in the second direction D2. In the axial direction Da along the axis L1 of the duct 21, the inner louver 41b is positioned closer to the duct 21 than the outer louvers 41a. As a result, when the louver unit 40 is rotated, the outer louvers 41a are less likely to come into contact with the duct 21. Therefore, compared to the case where all louvers 41 are positioned at the position of the inner louver 41b, the rotatable angle of the louver unit 40 can be increased without increasing the distance between the inner louver 41b and the lower opening 21b of the duct 21. Thus, a further increase in lateral force associated with thrust deflection can be achieved.

[0040] Furthermore, in the above embodiment, the outer louver 41a positioned closest to the axis L1 of the duct 21 in the second direction D2 is provided with a notch 47 to avoid the central projection 28 of the ducted fan 20. This makes it possible to increase the lateral force without reducing the rotatable angular range of the louver unit 40, by suppressing an increase in the distance between the multiple louver units 40 in the second direction D2, and the distance between the louver unit 40 and the lower opening 21b of the duct 21.

[0041] Furthermore, in the above embodiment, the first support portion 51 includes a base portion 56 fixed to the duct 21, and a plurality of arm portions 54 that extend downward from the base portion 56 and branch in a second direction D2 to rotatably support the first end portion 45 of the louver unit 40. This makes it possible to support the first end portions 45 of a plurality of louver units 40 while suppressing an increase in the weight of the first support portion 51.

[0042] Furthermore, in the above embodiment, the second support portion 52 has an inner circumferential surface capable of fixing multiple actuators 60, and an actuator support portion 57 that is ring-shaped and elongated in the second direction D2. This makes it possible to support multiple actuators 60 without complicating the shape of the second support portion 52.

[0043] <Other Embodiments> The present disclosure is not limited to the configurations of the above-described embodiments, and design changes can be made without departing from the gist thereof. FIG. 10 is a diagram showing the arrangement of louvers in a modification of an embodiment of the present disclosure. For example, in the above-described embodiment, when the louver unit 40 is in the initial position, the case where the inner louver 41b is arranged closer to the duct 21 than the outer louver 41a was exemplified. However, the arrangement of the plurality of louvers 41 included in the louver unit 40 is not limited to the above arrangement. For example, as in the modification shown in FIG. 10, in the case of the initial position, the arrangements of the plurality of louvers 41 included in one louver unit 40A may all be the same.

[0044] Further, in the above-described embodiment, the case where the plurality of louvers 41 included in one louver unit 40 have the same shape except for the outer louver 41a having the notch portion 47 was described. However, the shapes of the louvers 41 may be made different as necessary. Furthermore, in the above embodiment, the case where the notch portion 47 is provided was described, but if the louver 41 does not interfere with the central protrusion 28, the notch portion 47 may be omitted.

[0045] <Supplementary Note> The flying object and the thrust deflection device described in the embodiment are understood as follows, for example.

[0046] (1) According to the first embodiment, the aircraft 1 comprises an aircraft body 10, a plurality of ducted fans 20 having fans 22 inside a duct 21 which generate thrust for the aircraft body 10 by pushing the sucked air downward from the lower opening 21b of the duct 21, and a thrust deflection device 30 which covers the lower opening 21b from below and is capable of changing the direction of travel of the air pushed out from the ducted fans 20, wherein the thrust deflection device 30 extends in a first direction D1 which intersects the axis L1 of the duct 21 and a plurality of thrust deflection devices are arranged at intervals in a second direction D2 which intersects both the axis L1 of the duct 21 and the first direction D1 The duct 21 comprises a plurality of louver units 40, 40A, each having a louver 41 and a base portion 42 that supports a plurality of the louvers 41; a frame portion 50 that supports the plurality of louver units 40, 40A so that they can rotate around an axis L2 extending in the first direction D1; and an actuator 60 that can adjust the angle of the plurality of louver units 40, 40A around the axis L2, wherein the frame portion 50 supports the plurality of louver units 40, 40A so that, when viewed from below, the respective axes L2 of the plurality of louver units 40, 40A do not intersect within the duct 21.

[0047] As a result, the radius of rotation of each of the louver units 40 and 40A can be made smaller than when the lower opening 21b is covered from below by one louver unit. And as the radius of rotation of the louver units 40 and 40A becomes smaller, when the distance between the lower opening 21b of the duct 21 and the thrust deflection device 30 is made constant, the maximum angle at which the louver units 40 and 40A can rotate can be made larger than when the lower opening 21b is covered from below by one louver unit. On the other hand, when the maximum rotatable angle is made constant, since the radius of rotation of the louver units 40 and 40A becomes smaller, the thrust deflection device 30 can be arranged closer to the lower opening 21b of the duct 21, so that the air leaking between the lower opening 21b and the thrust deflection device 30 without contributing to the thrust deflection can be reduced. Further, since the radius of rotation of the louver units 40 and 40A can be made smaller, the holding torque of the louver units 40 and 40A can be made smaller, and the actuator 60 can be miniaturized. Therefore, it is possible to increase the lateral force generated when deflecting the thrust by the ducted fan 20 while suppressing the increase in size of the thrust deflection device 30 and the aircraft 1.

[0048] (2) According to the second aspect, the aircraft 1 is the aircraft 1 of (1), wherein the louver unit 40 includes two outer louvers 41a arranged on the outermost side in the second direction D2 among the plurality of louvers 41, and an inner louver 41b arranged between the two outer louvers 41a and closer to the duct 21 than the outer louvers 41a in the axial direction of the duct 21.

[0049] As a result, when the louver unit 40 is rotated, it becomes difficult for the outer louver 41a to contact the duct 21. Therefore, the rotatable angle of the louver unit 40 can be increased without increasing the distance between the inner louver 41b and the lower opening 21b of the duct 21 as compared with the case where all the louvers 41 are arranged at the position of the inner louver 41b. Therefore, a further increase in the lateral force associated with the thrust deflection can be achieved.

[0050] (3) According to the third embodiment, the aircraft 1 is the aircraft 1 of (2), wherein the ducted fan 20 further comprises a central projection 28 that protrudes downward along the axis L1 of the duct 21, and the outer louvers 41a that are positioned closest to the axis L1 of the duct 21 in the second direction D2 comprises a notch 47 that avoids the central projection 28.

[0051] This makes it possible to increase the lateral force without reducing the rotatable angular range of the louver units 40, 40A, by suppressing an increase in the distance between the multiple louver units 40, 40A in the second direction D2, and by suppressing an increase in the distance between the louver units 40, 40A and the lower opening 21b of the duct 21.

[0052] (4) According to the fourth embodiment, the flying body 1 is one of the flying body 1 of (2) or (3), wherein the outer louvers 41a that are positioned furthest from the axis L1 of the duct 21 in the second direction D2 can be positioned outside the inner circumferential surface of the duct 21 in the radial direction centered on the axis L1 of the duct 21.

[0053] As a result, the air pushed downward from the duct 21 passes inside the outer louvers 41a, thus preventing the air from passing through without being deflected by the thrust deflection device 30.

[0054] (5) According to the fifth embodiment, the aircraft 1 is any one of the aircraft 1 from (1) to (4), wherein the frame portion 50 comprises a first support portion 51 that rotatably supports the first end portion 45 of the louver units 40, 40A in the first direction D1, and a second support portion 52 that supports the actuator 60 and supports the second end portion 46 of the louver units 40, 40A in the first direction D1 via the actuator 60.

[0055] This allows the two louver units 40 and 40A to be rotatably supported by the first support portion 51 and the second support portion 52, so as to sandwich the two louver units 40 and 40A from the outside in the first direction D1.

[0056] (6) According to the sixth embodiment, the flying body 1 is the flying body 1 of (5), wherein the first support portion 51 comprises a base portion 53 fixed to the duct 21, and a plurality of arm portions 54 extending downward from the base portion 53 and branching in the second direction D2 to rotatably support the first end portions 45 of the louver units 40, 40A.

[0057] This makes it possible to support the first ends 45 of multiple louver units 40, 40A while suppressing an increase in the weight of the first support portion 51.

[0058] (7) According to the seventh embodiment, the aircraft 1 is the aircraft 1 of (5) or (6), wherein the second support portion 52 has an inner circumferential surface capable of fixing a plurality of actuators 60 and includes an actuator support portion 57 that is ring-shaped and elongated in the second direction D2.

[0059] This makes it possible to support multiple actuators 60 without complicating the shape of the second support portion 52. (8) According to the eighth aspect, the thrust vectoring device 30 is a thrust vectoring device 30 for an aircraft 1 having an aircraft body 10 and a plurality of ducted fans 20 that generate thrust for the aircraft body 10 by pushing the sucked air downward from the lower opening 21b of the duct 21, and comprises a plurality of louver units 40, 40A having a plurality of louvers 41 that extend in a first direction D1 and are spaced apart in a second direction D2 that intersects the first direction D1, and a base portion 42 that supports the plurality of louvers 41, a frame portion 50 that supports the plurality of louver units 40, 40A so as to be rotatable about an axis L2 that extends in the first direction D1 and supports the plurality of louver units 40, 40A in a state that is arranged in series in the second direction D2, and an actuator 60 that can adjust the angle of the plurality of louver units 40, 40A about the axis L2.

[0060] This makes it possible to increase the lateral force generated when deflecting the thrust by the ducted fan 20 while suppressing the enlargement of the thrust deflection device 30.

[0061] According to this disclosure, it is possible to increase the lateral force generated by thrust deflection while keeping the size of the device under control.

[0062] 1. Aircraft 10. Airframe 20. Ducted fan 21. Duct 21a. Upper opening 21b. Lower opening 22. Fan 23. Fixed arm 24. Propeller 25. Prime mover 26. Hub 27. Blade 28. Central projection 30. Thrust vectoring device 40, 40A. Louver unit 41. Louver 41a. Outer louver 41b. Inner louver 42. Base 43. First bracket 44. Second bracket 45. First end 46. Second end 47. Notch 50. Frame 51. First support 52. Second support 53. Base 54. Arm 55. Bearing 56. Base 57. Actuator support 60. Actuator 70. Rotating shaft

Claims

1. An aircraft comprising: an aircraft body; a plurality of ducted fans having fans in a duct and generating thrust for the aircraft by pushing the drawn-in air downward from the lower opening of the duct; a thrust deflection device covering the lower opening from below and capable of changing the direction of travel of the air pushed out from the ducted fans, wherein the thrust deflection device comprises a plurality of louver units having: a plurality of louvers extending in a first direction intersecting the axis of the duct and spaced apart in a second direction intersecting both the axis of the duct and the first direction; a base portion supporting the plurality of louvers; a frame portion supporting each of the plurality of louver units so as to be rotatable around an axis extending in the first direction; and an actuator capable of adjusting the angle of the plurality of louver units around the axis, wherein the frame portion supports the plurality of louver units such that, when viewed from below, the axes of each of the plurality of louver units do not intersect within the duct.

2. The aircraft according to claim 1, wherein the louver unit comprises two outer louvers positioned on the outermost side of the plurality of louvers in the second direction, and an inner louver positioned between the two outer louvers and closer to the duct than the outer louvers in the axial direction of the duct.

3. The aircraft according to claim 2, wherein the ducted fan further comprises a central projection that protrudes downward along the axis of the duct, and the outer louvers positioned closest to the axis of the duct in the second direction comprises a notch to avoid the central projection.

4. The flying body according to claim 2, wherein the outer louver positioned furthest from the axis of the duct in the second direction can be positioned outside the inner circumferential surface of the duct in the radial direction centered on the axis of the duct.

5. The aircraft according to claim 1, wherein the frame portion comprises a first support portion that rotatably supports the first end of the louver unit in the first direction, and a second support portion that supports the actuator and supports the second end of the louver unit in the first direction via the actuator.

6. The aircraft according to claim 5, wherein the first support portion comprises a base fixed to the duct, and a plurality of arm portions extending downward from the base and branching in the second direction to rotatably support the first end of the louver unit.

7. The aircraft according to claim 5, wherein the second support portion has an inner circumferential surface capable of fixing a plurality of actuators and comprises an actuator support portion that is ring-shaped and elongated in the second direction.

8. A thrust vectoring device for an aircraft having an aircraft body and a plurality of ducted fans that generate thrust for the aircraft by pushing inhaled air downward from a lower opening of a duct, comprising: a plurality of louver units having a plurality of louvers extending in a first direction and spaced apart in a second direction intersecting the first direction, and a base portion that supports the plurality of louvers; a frame portion that supports the plurality of louver units so as to be rotatable about an axis extending in the first direction and supports the plurality of louver units in a state where they are arranged in series in the second direction; and an actuator that can adjust the angle of the plurality of louver units about the axis.

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