Air vehicle

Abstract

To provide an air vehicle which can protect a sensor when the air vehicle is landed while reducing air resistance.SOLUTION: An air vehicle includes: a fuselage; a sensor which is provided protruding at a lower part of the fuselage and may capture images of at least the lower part of the fuselage; and a fairing part located behind the sensor and provided adjacent to the sensor. A lowermost part of the fairing part is located at a relatively lower position than the lowermost part of the sensor. The fairing part functions as a leg part which supports the fuselage when the air vehicle is landed.SELECTED DRAWING: Figure 1

Description

[Technical field]

[0001] The present invention relates to aircraft. [Background technology]

[0002] For example, Patent Document 1 discloses an unmanned aerial vehicle capable of vertical takeoff and landing. The unmanned aerial vehicle of Patent Document 1 has an optical sensor capable of detecting the presence and inclination of a takeoff and landing surface. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] JP 2020-37396 A Summary of the Invention [Problem to be solved by the invention]

[0004] In an aircraft such as an unmanned aerial vehicle, for example, a sensor capable of capturing an image of the surroundings of the aircraft may be provided protruding downward from the fuselage. In such an aircraft, since the sensor protrudes from the fuselage, there is a risk that the sensor may increase air resistance.

[0005] In addition, in such aircraft, dedicated legs are sometimes provided to support the fuselage in order to prevent the sensor from being damaged due to direct contact with the ground during landing. However, providing dedicated legs increases the air resistance of the legs and increases the weight of the aircraft.

[0006] Therefore, an object of the present invention is to provide an aircraft that can protect sensors during landing while suppressing air resistance. [Means for solving the problem]

[0007] In order to solve the above problem, an aircraft according to one embodiment of the present invention comprises: The torso and A sensor provided to protrude from a lower portion of the torso and capable of capturing an image of at least a portion below the torso; a fairing portion located rearward of the sensor and adjacent to the sensor; Equipped with The lowermost portion of the fairing portion is located relatively lower than the lowermost portion of the sensor, The fairing section functions as legs that support the fuselage when it lands. Effect of the Invention

[0008] According to the present invention, it is possible to protect the sensor during landing while suppressing air resistance. [Brief description of the drawings]

[0009] [Figure 1] FIG. 1 is a schematic plan view showing the configuration of an aircraft according to this embodiment. [Diagram 2] FIG. 2 is a schematic rear view showing the configuration of the aircraft according to this embodiment. [Diagram 3] FIG. 3 is an enlarged side view of the tail and its surroundings. [Figure 4] FIG. 4 is a side view illustrating an example of the configuration of the sensor. [Diagram 5] FIG. 5 is a partially enlarged perspective view showing the sensor and the fairing portion. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0010] Hereinafter, an embodiment of the present invention will be described in detail with reference to the accompanying drawings. The specific dimensions, materials, numerical values, etc. shown in the embodiment are merely examples for facilitating understanding of the invention, and do not limit the present invention unless otherwise specified. In this specification and drawings, elements having substantially the same functions and configurations are given the same reference numerals to avoid repeated explanations, and elements not directly related to the present invention are not shown.

[0011] Fig. 1 is a schematic plan view showing the configuration of an aircraft 1 according to this embodiment. Fig. 2 is a schematic rear view showing the configuration of an aircraft 1 according to this embodiment. The up-down direction in Fig. 1 is the front-rear direction of the aircraft 1, and the left-right direction in Fig. 1 is the left-right direction of the aircraft 1. The up-down direction in Fig. 2 is the up-down direction of the aircraft 1, and the left-right direction in Fig. 2 is the left-right direction of the aircraft 1. The aircraft 1 is, for example, an unmanned aircraft such as a drone.

[0012] The aircraft 1 comprises a fuselage 10, a main wing 12, a beam section 14, a horizontal rotor 16, a vertical rotor 18, a rear landing gear section 20, a tail section 22, a sensor 24 and a fairing section 26.

[0013] The fuselage 10 is formed into a cylindrical shape extending in the fore-aft direction of the aircraft 1. The front and rear ends of the fuselage 10 are formed into a tapered shape so that the outer diameter of the fuselage 10 becomes smaller. The main wings 12 extend roughly horizontally from the fuselage 10 in the left and right directions, approximately at the center of the fuselage 10 in the fore-aft direction.

[0014] The beam sections 14 are provided on each of the left and right main wings 12 and extend in the fore-and-aft direction of the aircraft 1. The horizontal rotors 16 are provided on the front and rear ends of the beam sections 14, for a total of four. The horizontal rotors 16 extend roughly horizontally and are rotatable around a rotation axis that extends in the up-down direction of the aircraft 1. The horizontal rotors 16 mainly generate lift for the aircraft 1. Although not shown, the aircraft 1 has a motor that rotates the horizontal rotors 16.

[0015] The vertical rotor 18 is provided at the rear end of the fuselage 10. The vertical rotor 18 extends along a plane perpendicular to the central axis of the fuselage 10, and is rotatable around a rotation axis extending in the fore-and-aft direction of the aircraft 1. The vertical rotor 18 mainly generates a thrust for the aircraft 1. Although not shown, the aircraft 1 has a motor that rotates the vertical rotor 18.

[0016] The rear legs 20 are provided rearward of the center of the fuselage 10, extending diagonally downward to the left and diagonally downward to the right from the fuselage 10. In other words, as shown in Fig. 2, when the aircraft 1 is viewed from the rear, the rear legs 20 are provided in a shape resembling an upside-down V. The rear legs 20 are made of a material with relatively high rigidity, such as steel. The rear legs 20 support the fuselage 10 when the aircraft 1 lands on the ground.

[0017] The tail 22 is provided on the rear legs 20 and extends rearward from the rear legs 20. Since the rear legs 20 are provided in a V-shape extending downward from the fuselage 10, the tail 22 is also provided in a V-shape extending downward from the fuselage 10.

[0018] The aircraft 1 is capable of flight by the rotation of the horizontal rotors 16 and the vertical rotors 18. The main wings 12 and the tail 22 stabilize the attitude of the aircraft 1 during flight. The aircraft 1 is capable of, for example, vertical takeoff and vertical landing. Note that the aircraft 1 may also be configured to be capable of takeoff and landing by taxiing.

[0019] Fig. 3 is an enlarged side view of the tail 22 and its surroundings. As shown in Fig. 3, a wheel 30 is provided at the tip of the rear landing gear 20. The wheel 30 has a tire. When the aircraft 1 lands on the ground, the tire of the wheel 30 comes into contact with the ground.

[0020] Since the rear landing gear 20 has the wheels 30, the aircraft 1 can be moved horizontally on the ground more easily than in an embodiment not provided with the wheels 30. In addition, the wheels 30 can reduce the impact of the aircraft 1 when it lands.

[0021] The wheels 30 of the rear legs 20 may be omitted. This is because even if the wheels 30 are omitted, the rear legs 20 can still support the fuselage 10. If the wheels 30 are omitted, horizontal movement of the aircraft 1 on the ground may become more difficult, but the weight can be reduced and air resistance during flight can be suppressed.

[0022] 3, the tip of the rear landing gear 20 is located relatively lower than the tip of the tail 22. In other words, the tip of the rear landing gear 20 protrudes in a direction relatively farther away from the fuselage 10 than the tip of the tail 22. This ensures that the tail 22 is spaced apart from the ground when the aircraft 1 has landed on the ground.

[0023] Since the tail unit 22 does not come into contact with the ground and the rear legs 20 support the fuselage 10, it is possible to prevent the tail unit 22 from being unintentionally deformed due to the weight of the aircraft 1 and from being unable to fully function, for example, when the aircraft 1 lands.

[0024] Furthermore, because the tail unit 22 does not come into contact with the ground, damage caused by the tail unit 22 rubbing against the ground when the aircraft 1 moves horizontally on the ground can be prevented.

[0025] Furthermore, when the aircraft 1 is moved horizontally on the ground, a carrier that supports the fuselage 10 so that it can move horizontally may be disposed under the front end of the fuselage 10 to move the aircraft 1 horizontally. In this case, the aircraft 1 is moved horizontally with the fuselage 10 tilted backward so that the rear end of the fuselage 10 is lower in height than the front end. Even if the aircraft 1 is moved horizontally on the ground with the fuselage 10 tilted backward, there is a difference in height between the tip of the rear landing gear 20 and the tip of the tail 22, so that damage caused by the tail 22 rubbing against the ground can be reduced.

[0026] The rear landing gear 20 and the tail fin 22 may be formed so that their outer diameters are integrally streamlined.

[0027] Also, here, an example has been described in which the tail 22 is provided on the rear legs 20. However, the rear legs 20 and the tail 22 may be integrally configured, and the tail 22 itself may function as the rear legs 20.

[0028] 1 and 2, the sensor 24 is provided on the lower part of the fuselage 10. The sensor 24 protrudes downward from the fuselage 10. The sensor 24 is located forward of the center of the fuselage 10.

[0029] 4 is a side view illustrating an example of the configuration of the sensor 24. The sensor 24 is formed in a cylindrical shape with a hemispherical tip. The sensor 24 has a base portion 40, a first support portion 42, a second support portion 44, and a camera 46.

[0030] The base unit 40 is fixed to the fuselage 10. The first support unit 42 is connected to the base unit 40. The first support unit 42 is rotatable relative to the base unit 40 around a first rotation axis C10 that extends in the vertical direction of the aircraft 1. In other words, the first support unit 42 is rotatable in the azimuth direction. The second support unit 44 is connected to the first support unit 42. The second support unit 44 is rotatable relative to the first support unit 42 around a second rotation axis C12 that extends in the horizontal direction of the aircraft 1. In other words, the second support unit 44 is rotatable in the elevation direction.

[0031] A camera 46 is mounted on the second support portion 44. The camera 46 is, for example, a visible camera or an infrared camera. Note that, although four cameras 46 are illustrated in Fig. 4, the number of cameras 46 is not limited to four, and may be one, two, three, or five or more.

[0032] The sensor 24 is configured to be able to image at least the area below the fuselage 10 by the camera 46. The sensor 24 is able to change the imaging direction of the camera 46 by rotating the first support part 42 at a predetermined azimuth angle and rotating the second support part 44 at a predetermined elevation angle. The sensor 24 can image not only the area below the fuselage 10, but also the surroundings of the aircraft 1, such as the area in front of the aircraft 1, the area to the left or right of the aircraft 1, or the area diagonally below and in front of the aircraft 1, depending on the attitude of the first support part 42 and the second support part 44. The sensor 24 protrudes downward from the fuselage 10, and thus can also image areas other than the area below the fuselage 10, such as the area in front of the aircraft 1.

[0033] For example, while flying, the aircraft 1 can capture images of the ground located below the fuselage 10 using the sensor 24, store the captured information, use the captured information to control the aircraft 1, and transmit the captured information to a specified destination.

[0034] 1 and 2, the fairing portion 26 is located rearward of the sensor 24 and adjacent to the sensor 24. The fairing portion 26 is located forward of the center of the fuselage 10. The fairing portion 26 is fixed to the lower part of the fuselage 10.

[0035] Fig. 5 is a partially enlarged perspective view showing the sensor 24 and the fairing portion 26. As shown in Fig. 5, the sensor 24 and the fairing portion 26 are configured so that their outer diameters are integrally streamlined. More specifically, the width of the fairing portion 26 in the left-right direction gradually decreases from the front end portion to the rear end portion of the fairing portion 26. The height of the fairing portion 26 in the up-down direction with respect to the lower surface of the fuselage 10 gradually decreases from the front end portion to the rear end portion of the fairing portion 26.

[0036] Because the sensor 24 and the fairing portion 26 are configured to be integrally streamlined, even if the sensor 24 protrudes from the fuselage 10, the air hitting the sensor 24 during flight can be straightened, thereby suppressing air resistance caused by the sensor 24.

[0037] The fairing portion 26 is made of a material with a relatively high rigidity, such as steel. The lowermost portion of the fairing portion 26 is located relatively lower than the lowermost portion of the sensor 24. In other words, the fairing portion 26 protrudes relatively downward from the sensor 24. As a result, the fairing portion 26 functions as a leg that supports the fuselage 10 when the aircraft 1 lands. More specifically, since the fairing portion 26 is located forward of the center of the fuselage 10, the fairing portion 26 functions as a nose leg. As a result, when the aircraft 1 lands on the ground, the sensor 24 is separated from the ground.

[0038] 5, wheels 52 are provided on a lower portion 50 of the fairing portion 26. The wheels 52 protrude downward from the bottom surface of the fairing portion 26. The wheels 52 have tires. When the aircraft 1 lands on the ground, the tires of the wheels 52 come into contact with the ground.

[0039] Since the fairing portion 26 has the wheels 52, the aircraft 1 can be moved horizontally on the ground more easily than in an embodiment not provided with the wheels 52. In addition, the wheels 52 can reduce the impact of the aircraft 1 when it lands.

[0040] The wheels 52 of the fairing portion 26 may be omitted. This is because even if the wheels 52 are omitted, the fairing portion 26 can still support the fuselage 10.

[0041] Since the sensor 24 does not come into contact with the ground and the fairing portion 26 supports the fuselage 10, it is possible to prevent the sensor 24 from being unintentionally deformed by the weight of the aircraft 1, for example, when the aircraft 1 lands, and thereby prevent the sensor 24 from being unable to fully function.

[0042] Furthermore, because the sensor 24 does not come into contact with the ground, it is possible to prevent damage to the sensor 24 caused by rubbing against the ground when the aircraft 1 is moved horizontally on the ground.

[0043] Furthermore, when the aircraft 1 is moved horizontally on the ground, a carrier that supports the fuselage 10 so that it can move horizontally may be disposed under the rear end side of the fuselage to move the aircraft 1 horizontally. In this case, the aircraft 1 is moved horizontally with the fuselage tilted forward so that the front end side of the fuselage 10 is lower in height than the rear end side. Even if the aircraft 1 is moved horizontally on the ground with the fuselage 10 tilted forward, there is a difference in height between the tip of the sensor 24 and the bottom surface of the fairing part 26, so that the occurrence of damage caused by the sensor 24 rubbing against the ground can be reduced.

[0044] As described above, the aircraft 1 of this embodiment includes the fuselage 10, the sensor 24 that is provided to protrude from the lower part of the fuselage 10 and is capable of capturing an image of at least the area below the fuselage 10, and the fairing portion 26 that is located rearward of the sensor 24 and adjacent to the sensor 24. The lowermost part of the fairing portion 26 is located relatively lower than the lowermost part of the sensor 24. The fairing portion 26 functions as a leg that supports the fuselage 10 when the aircraft lands.

[0045] As a result, even if the aircraft 1 of this embodiment is equipped with the sensor 24 protruding from the fuselage 10, the fairing portion 26 can suppress the air resistance of the sensor 24. In addition, even when the aircraft 1 of this embodiment lands, the fairing portion 26 functions as a landing gear, thereby protecting the sensor 24.

[0046] Therefore, according to the aircraft 1 of the present embodiment, it is possible to protect the sensor 24 during landing while suppressing air resistance.

[0047] In addition, in the aircraft 1 of this embodiment, the fairing portion 26 functions as a landing gear, so that the number of parts can be reduced compared to an embodiment in which a dedicated landing gear is provided, and it is possible to suppress an increase in the weight of the aircraft 1.

[0048] Moreover, the aircraft 1 of this embodiment further includes rear landing gear 20, which is provided rearward of the center of the fuselage 10, extending diagonally downward to the left and diagonally downward to the right from the fuselage 10 and supports the fuselage 10 when it lands. In the aircraft 1 of this embodiment, a tail 22 is provided on the rear landing gear 20 to stabilize the attitude during flight.

[0049] As a result, the aircraft 1 of this embodiment can suppress the increase in weight of the aircraft 1 and can suppress the air resistance of the aircraft 1 compared to an embodiment in which a dedicated landing gear is provided in a position separate from the tail 22.

[0050] Furthermore, in the aircraft 1 of this embodiment, a fairing section 26 functioning as a nose landing gear section is provided forward of the center of the fuselage 10, and rear landing gear sections 20 are provided rearward of the center of the fuselage 10. As a result, in the aircraft 1 of this embodiment, an increase in the weight of the aircraft 1 can be suppressed, while the fuselage 10 can be stably supported on the ground.

[0051] Although the embodiment of the present invention has been described above with reference to the attached drawings, it goes without saying that the present invention is not limited to such an embodiment. It is clear that a person skilled in the art can think of various modified or altered examples within the scope of the claims, and it is understood that such examples also naturally belong to the technical scope of the present invention.

[0052] For example, in the above embodiment, an unmanned aerial vehicle has been described as an example of the aircraft 1. However, the aircraft 1 is not limited to an unmanned aerial vehicle and may be a manned aircraft. [Explanation of symbols]

[0053] 1 aircraft 10. Torso 20 Hind leg 22 tail fin 24 Sensors 26 Fairing section 50 Lower 52 wheels

Claims

1. The torso and A sensor provided to protrude from a lower portion of the torso and capable of capturing an image of at least a portion below the torso; a fairing portion located rearward of the sensor and adjacent to the sensor; Equipped with The lowermost portion of the fairing portion is located relatively lower than the lowermost portion of the sensor, The fairing portion functions as a leg portion that supports the fuselage when the aircraft lands.

2. The aircraft of claim 1 , wherein the sensor and the fairing portion are integrally configured to be streamlined.

3. The aircraft of claim 1 , further comprising wheels beneath said fairing portion.

4. and further comprising rear legs extending diagonally downward to the left and diagonally downward to the right from the fuselage rearward of the center of the fuselage, the rear legs supporting the fuselage when the aircraft lands, 4. An aircraft according to claim 1, wherein the rear landing gear is provided with a tail for stabilizing the aircraft's attitude during flight.

5. 5. The aircraft according to claim 4, wherein the tip of the rear landing gear is located relatively lower than the tip of the tail.

Images