Wing structure of an underwater vehicle

Abstract

To provide a wing structure for an underwater vehicle that can suppress wingtip vortices. [Solution] The wing structure 3 of the underwater vehicle 1 according to one embodiment includes a wing 4 that protrudes from the hull 2 ​​of the underwater vehicle 1 and is symmetrical with respect to the centerline 40 in the thickness direction, and an end plate 5 that is pointed forward and symmetrical with respect to the centerline 40 of the wing 4, provided at least at the rear of the tip 43 of the wing 4 so as to be perpendicular to the wing 4. With this configuration, the end vortex generated from the tip 43 of the wing 4 toward the rear is diffused by the end plate 5, so that the end vortex can be suppressed.

Description

Technical Field

[0001] The present disclosure relates to a wing structure of an underwater vehicle.

Background Art

[0002] Conventionally, unmanned or manned underwater vehicles have been known. An underwater vehicle includes a hull and a plurality of wings protruding from the hull. For example, the plurality of wings serve to control the attitude of the hull. See, for example, Patent Document 1.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] By the way, in the wing structure of an underwater vehicle in which wings protrude from the hull, wing tip vortices may occur from the tip of the wing toward the rear. When the hull is located behind the wing, the wing tip vortices may affect the hull such as causing vibration. Alternatively, even when there is no hull behind the wing, the wing itself may vibrate due to the wing tip vortices.

[0005] Therefore, an object of the present disclosure is to provide a wing structure of an underwater vehicle that can suppress wing tip vortices.

Means for Solving the Problems

[0006] The present disclosure provides a wing structure of an underwater vehicle including wings protruding from the hull of the underwater vehicle, the wings being symmetric with respect to the center line in the thickness direction, and wing tip plates provided at least at the rear part of the tip of the wings so as to be orthogonal to the wings, the wing tip plates being symmetric with respect to the center line of the wings and tapering forward.

Effects of the Invention

[0007] This disclosure provides a wing structure for an underwater vehicle that can suppress wingtip vortices. [Brief explanation of the drawing]

[0008] [Figure 1] This is a perspective view of the wing structure of an underwater vehicle according to one embodiment. [Figure 2] This is a perspective view of the wing structure of the first modified underwater vehicle. [Figure 3] This is a perspective view of the wing structure of the underwater vehicle in the second modified example. [Figure 4] This is a perspective view of the wing structure of the underwater vehicle in the third modified example. [Modes for carrying out the invention]

[0009] Figure 1 shows a wing structure 3 of an underwater vehicle 1 according to one embodiment. The wing structure 3 includes a wing 4 protruding from the hull 2 ​​of the underwater vehicle 1 and a wingtip plate 5 provided at least at the rear of the tip 43 of the wing 4. The portion of the hull 2 ​​surface to which the wing 4 is attached may be flat or curved. Note that the hull 2 ​​is a concept that includes not only the main body from bow to stern, but also structures that protrude from the main body in directions different from the longitudinal direction of the vessel.

[0010] In this embodiment, the wing 4 is located within the forward 3 / 4 region when the hull 2 ​​is divided into four equal parts along its length. However, the wing 4 may also be located at the stern.

[0011] The wing 4 is symmetrical with respect to the center line 40 in the thickness direction of the wing 4. In this embodiment, the wing 4 protrudes laterally from the hull 2. That is, the wing 4 is a horizontal wing, and the direction of protrusion of the wing 4 is perpendicular to the length direction of the hull 2. However, the wing 4 may protrude upward or downward from the hull 2, or diagonally upward or diagonally downward from the hull 2.

[0012] Furthermore, in this embodiment, the wing 4 is pivotable around a pivot axis 46 that extends in the direction of projection of the wing 4. However, the wing 4 may be a fixed wing fixed to the hull 2.

[0013] In this embodiment, the wing 4 has a leading edge 41 perpendicular to the longitudinal direction of the hull 2, and a trailing edge 42 that slopes toward the leading edge 41 as it moves away from the hull 2. The end of the leading edge 41 opposite to the hull 2 ​​is the front end 44 of the tip 43, and the end of the trailing edge 42 opposite to the hull 2 ​​is the rear end 45 of the tip 43.

[0014] However, contrary to this embodiment, the trailing edge 42 may be perpendicular to the longitudinal direction of the hull 2, and the leading edge 41 may be inclined to approach the trailing edge 42 as it moves away from the hull 2. Alternatively, both the leading edge 41 and the trailing edge 42 may be inclined to approach each other as they move away from the hull 2.

[0015] In this embodiment, the tip 43 of the wing 4 is parallel to the longitudinal direction of the hull 2. However, the tip 43 may be inclined with respect to the longitudinal direction of the hull 2. The aspect ratio Ra (Ra = S / L) is the ratio of the area S of the wing 4 to the square of the protruding length L of the wing 4. 2 For example, the aspect ratio Ra is between 0.8 and 0.9. If the aspect ratio Ra is between 0.8 and 0.9, the wing 4 can be made into a planar shape suitable for the underwater vehicle 1.

[0016] With respect to the protruding length L of the wing 4, if the portion of the hull surface 2 to which the wing 4 is attached is curved, the protruding length L of the wing 4 is the average length from the surface of the hull 2 ​​to the tip 43 of the wing 4.

[0017] The endplate 5 is perpendicular to the wing 4. Furthermore, the endplate 5 is symmetrical with respect to the centerline 40 of the wing 4 and tapers towards the front. In other words, the leading edge 51 of the endplate 5 is located on the centerline 40 of the wing 4.

[0018] In this embodiment, the center of the rear edge 52 of the endplate 5 coincides with the rear end 45 of the tip 43 of the wing 4, and the rear edge 52 is inclined to tilt backward from the center toward both sides. In other words, the rear ends of the endplate 5, which are both ends of the rear edge 52, are located behind the rear end 45 of the tip 43 of the wing 4. However, the center of the rear edge 52 of the endplate 5 may be located behind the rear end 45 of the tip 43 of the wing 4.

[0019] The ratio R1 (R1 = B / C) of the length B from the rear end 45 of the tip 43 of the wing 4 to the front end 51 of the wing end plate 5 with respect to the length C of the tip 43 of the wing 4 is, for example, 0.2 or more and 0.5 or less. Also, the ratio R2 (R2 = H / L) of the width H of the wing end plate 5 in the thickness direction of the wing 4 to the protruding length L of the wing 4 is, for example, 0.2 or more and 0.4 or less.

[0020] In the wing structure 3 having the configuration described above, since the wing tip vortices generated from the tip 43 of the wing 4 toward the rear are diffused by the wing end plate 5, the wing tip vortices can be suppressed.

[0021] Wing tip vortices are likely to occur when the wing 4 takes an angle of attack, so the wing end plate 5 has a great effect when the wing 4 is swingable as in this embodiment. In particular, when the wing 4 extends laterally from the hull 2 as in this embodiment, the wing 4 can be used as a rudder for controlling the depth of the hull 2.

[0022] When the hull 2 is located behind the wing 4 as in this embodiment, the wing tip vortices generated from the tip 43 of the wing 4 may affect the hull 2 such as vibration. On the other hand, if the wing tip vortices are suppressed by the wing end plate 5, vibrations of the hull 2 caused by the wing tip vortices can be reduced.

[0023] Also, if the ratio R1 of the length B from the rear end 45 of the tip 43 of the wing 4 to the front end 51 of the wing end plate 5 with respect to the length C of the tip 43 of the wing 4 is 0.2 or more and 0.5 or less, the increase in the resistance value due to the addition of the wing end plate 5 can be suppressed while supporting the wing end plate 5 with sufficient strength.

[0024] Furthermore, if the ratio R2 of the width H of the wing end plate 5 in the thickness direction of the wing 4 to the protruding length L of the wing 4 is 0.2 or more and 0.4 or less, the increase in the resistance value due to the addition of the wing end plate 5 can be suppressed while reducing the risk of vibration generation of the wing end plate 5 itself due to the size of the wing end plate 5.

[0025] <Modification Example> The present disclosure is not limited to the above-described embodiment, and various modifications are possible without departing from the gist of the present disclosure.

[0026] For example, as shown in the first modified wing structure 3A in Figure 2, the end plate 5 may extend forward, and the front end 51 of the end plate 5 may coincide with the front end 44 of the tip 43 of the wing 4.

[0027] Furthermore, in Figure 1, the lines extending away from each other from the front end 51 of the wingtip plate 5 were straight lines, but the lines extending away from each other from the front end 51 of the wingtip plate 5 may be concave curves, as in the second modified wing structure 3B shown in Figure 3, or they may be convex curves.

[0028] Furthermore, as shown in the third modified wing structure 3C in Figure 4, the wingtip plate 5 may be triangular in shape.

[0029] <Summary> In a first aspect, the present disclosure provides a wing structure for an underwater vehicle, comprising a wing projecting from the hull of the underwater vehicle and symmetrical with respect to a centerline in the thickness direction, and a forward-pointing end plate provided at least at the rear of the tip of the wing so as to be perpendicular to the wing, and symmetrical with respect to the centerline of the wing.

[0030] With the above configuration, wingtip vortices generated from the wingtip towards the rear are diffused by the wingtip plate, thus suppressing wingtip vortices.

[0031] In a second embodiment, in the first embodiment, for example, the wing may protrude laterally from the hull.

[0032] In a third embodiment, in the first or second embodiment, the wing may be pivotable about a pivot axis extending in the direction of the wing's projection. Since wingtip vortices are easily generated when the wing takes an angle of attack, wingtip plates are highly effective when the wing is pivotable. In particular, when the wing extends laterally from the hull, the wing can be used as a rudder to control the depth of the hull.

[0033] In a fourth embodiment, in any of the first to third embodiments, the wing may be located within the forward 3 / 4 region when the hull is divided into four equal parts in the longitudinal direction. When the hull is located aft of the wing, wingtip vortices generated from the wingtips may affect the hull with vibrations and other effects. In contrast, if wingtip vortices are suppressed by wingtip plates, vibrations and other effects on the hull caused by wingtip vortices can be reduced.

[0034] In a fifth embodiment, in any of the first to fourth embodiments, the aspect ratio, which is the ratio of the area of ​​the wing to the square of the protruding length of the wing, may be 0.8 or more and 0.9 or less. With this configuration, the wing can be made into a planar shape suitable for an underwater vehicle.

[0035] In a sixth aspect, in any of the first to fifth aspects, the ratio of the length from the trailing end of the wingtip to the leading end of the endplate to the length of the wingtip may be 0.2 or more and 0.5 or less. This configuration allows the endplate to be supported with sufficient strength while suppressing the increase in drag associated with the addition of the endplate.

[0036] In a seventh aspect, in any of the first to sixth aspects, the ratio of the width of the end plate in the thickness direction of the wing to the protruding length of the wing may be 0.2 or more and 0.4 or less. This configuration makes it possible to suppress the increase in drag value associated with the addition of the end plate while reducing the risk of vibration of the end plate itself due to the size of the end plate. [Explanation of Symbols]

[0037] 1 Underwater vehicle 2 hull 3,3A,3B,3C Wing structure 4 wings 40 center line 43 Tip 45 Rear end 46. ​​Oscillating axis 5. Wing end plates 51 Front end

Claims

1. A wing protruding from the hull of the underwater vehicle, symmetrical with respect to the centerline in the thickness direction, A wingtip plate is provided at least at the rear of the tip of the wing so as to be perpendicular to the wing, and is symmetrical with respect to the centerline of the wing, and is pointed forward. A wing structure for an underwater vehicle equipped with the following features.

2. The wing structure for an underwater vehicle according to claim 1, wherein the wing protrudes laterally from the hull.

3. The wing structure for an underwater vehicle according to claim 1 or 2, wherein the wing is pivotable about a pivot axis extending in the direction of the wing's projection.

4. The wing structure for an underwater vehicle according to claim 1 or 2, wherein the wing is located within the front 3 / 4 region when the hull is divided into four equal parts in the longitudinal direction.

5. The wing structure for an underwater vehicle according to claim 1 or 2, wherein the aspect ratio, which is the ratio of the area of ​​the wing to the square of the protruding length of the wing, is 0.8 or more and 0.9 or less.

6. The wing structure for an underwater vehicle according to claim 1 or 2, wherein the ratio of the length from the rear end of the wing tip to the front end of the wing end plate to the length of the wing tip is 0.2 or more and 0.5 or less.

7. The wing structure for an underwater vehicle according to claim 1 or 2, wherein the ratio of the width of the end plate in the thickness direction of the wing to the protruding length of the wing is 0.2 or more and 0.4 or less.

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