JP2018175621A - Shuttlecock - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a shuttlecock capable of improving a rotation number.SOLUTION: There is provided a shuttlecock comprising: a base part; and a skirt part provided on an end surface of the base part, in which the skirt part comprises: plural feather shafts which are arranged in a toric state on the end surface and one end in an axial direction of each feather shaft is fixed to the end surface; and plural ribs for connecting adjacent feather shafts, the all ribs in a range between prescribed positions of the feather shafts and the other end are oblique to the feather shafts.SELECTED DRAWING: Figure 1

Description

  The present invention relates to a shuttlecock.

  As shuttlecocks for badminton, those using waterfowl feathers (natural feathers) (natural shuttlecocks) for feathers (natural shuttlecocks) and those using artificial feathers artificially manufactured from nylon resin etc. (artificial shuttles There is a cock).

  Further, as artificial shuttlecocks, those which imitate natural feathers, and those in which wing portions (hereinafter also referred to as skirt portions) are formed in a lattice shape of a cross are known. However, such artificial shuttlecocks have not obtained a characteristic flight trajectory like a natural shuttlecock. One of the causes is that the number of revolutions at the time of flight is lower than that of the natural shuttlecock.

  Therefore, for example, in Patent Document 1, the rotational speed is improved by changing the aperture ratio of the skirt portion in accordance with the circumferential position in the lattice-like artificial shuttlecock.

Patent No. 432454 gazette

  However, in the above-described shuttlecock, there is a possibility that the flight distance and the deceleration characteristic may be deteriorated due to the heavy weight and the deterioration of the aerodynamic characteristic, and the designability may be lowered. Thus, there is a possibility that the characteristics other than the rotational speed may be adversely affected.

  The present invention has been made in view of such circumstances, and an object of the present invention is to improve the rotational speed without affecting other characteristics.

  A main invention for achieving the above object is a shuttlecock comprising a base portion and a skirt portion provided on an end surface of the base portion, the skirt portion being plurally arranged in an annular shape on the end surface A plurality of wing shafts each having one end in the axial direction fixed to the end face, and a plurality of ribs connecting the adjacent wing shafts, and a predetermined position of the wing shaft It is a shuttlecock characterized in that all the ribs in the range between the other end and the other are provided obliquely to the wing axis.

  Other features of the present invention will become apparent from the description of the present specification and the drawings.

  According to the shuttlecock of the present invention, the number of revolutions at the time of flight can be improved.

It is a side view of shuttlecock 1 of this embodiment. It is a perspective view of shuttlecock 1 seen from the front. It is a perspective view of shuttlecock 1 seen from the back. It is a front view of shuttlecock 1 seen from the front. It is a side view of shuttlecock 100 of a comparative example. It is a perspective view of shuttlecock 100 seen from the front. It is a perspective view of shuttlecock 100 seen from the back. It is a front view of shuttlecock 100 seen from the front. FIG. 14 is a side view of the shuttlecock 1 of the third embodiment. FIG. 20 is a side view of the shuttlecock 1 of the fourth embodiment. It is a perspective view of shuttlecock 1 of Example 4 seen from the front. It is a perspective view of shuttlecock 1 of Example 4 seen from the back. It is a front view of shuttlecock 1 of Example 4 seen from the front.

=== Overview ===
At least the following matters will be made clear by the present specification and the description of the drawings.

A shuttlecock comprising: a base portion; and a skirt portion provided on an end face of the base portion, wherein the skirt portion is a plurality of wing axes arranged in an annular shape on the end face, each in an axial direction Has a plurality of wing axes fixed at one end to the end surface, and a plurality of ribs connecting the adjacent wing axes, and the rib in the range between the predetermined position of the wing axis and the other end is A shuttlecock is characterized in that all are provided obliquely to the wing axis.
According to such a shuttlecock, the number of revolutions at the time of flight can be improved.

In the shuttle cock, the first blade portion and the second blade portion having a smaller aperture ratio than the first blade portion are alternately arranged in the circumferential direction of the skirt portion using the ribs in the range. It is desirable that it is formed of
According to such a shuttlecock, the number of rotations can be further improved.

The shuttlecock, wherein the nth (n is a natural number) from the other end in the region on one side in the circumferential direction of the skirt portion with respect to the wing axis and the circumferential direction with respect to the wing axis It is desirable that the n-th rib from the other end in the other side region of the wing be connected to a different position in the axial direction of the wing axis.
According to such a shuttlecock, the number of rotations can be improved, and breakage can be suppressed.

In the shuttle cock, it is desirable that the nth rib of the one side region is continuous with the other rib of the other side region via the wing shaft.
According to such a shuttlecock, the strength can be increased, and the productivity of the mold can be improved.

In the shuttle cock, it is preferable that a rib larger in width than each rib in the range is provided obliquely to the wing axis at the one end side than the range.
According to such a shuttlecock, it can be made easy to recognize that the rib is oblique to the wing axis, and it is possible to further improve the number of rotations.

In the shuttle cock, it is desirable that the rib closest to the base portion be orthogonal to the wing axis.
According to such a shuttlecock, weight reduction can be achieved, and each wing shaft becomes difficult to twist.

  In the shuttle cock, it is preferable that the predetermined position is a midpoint of the wing axis.

  According to such a shuttlecock, the number of revolutions can be improved.

=== Embodiments ===
<Structure of Shuttlecock of This Embodiment>
The structure of the shuttlecock 1 of the present embodiment will be described with reference to the drawings. In the following description, the side on which the base portion 2 of the shuttlecock 1 is provided is referred to as the front side, and the opposite side is referred to as the rear side. FIG. 1 is a side view of the shuttlecock 1 of the present embodiment. FIG. 2 is a perspective view of the shuttlecock 1 viewed from the front. FIG. 3 is a perspective view of shuttlecock 1 viewed from the rear. FIG. 4 is a front view of shuttlecock 1 viewed from the front.

  The shuttlecock 1 is an artificial shuttlecock, and includes a base portion 2 and a skirt portion 10.

  The base portion 2 is configured, for example, by covering a thin skin on a cork base. The base portion 2 has a hemispherical shape with a diameter of 25 mm to 28 mm at the front side portion, and has a flat end face 2A at the rear end. In the present embodiment, not the natural cork but the cork formed by solidifying cork particles is used as the cork of the base portion 2.

  The skirt portion 10 is formed of a plastic (for example, nylon resin), and provided so as to extend rearward from the end surface 2A of the base portion 2 (in order to increase the diameter). The skirt portion 10 of the present embodiment has a wing shaft 11, a transverse rib 12 (corresponding to a rib), a longitudinal rib 13, and a longitudinal rib 14.

  The wing shafts 11 are linear members constituting the skirt portion 10, and a plurality (16 in the present embodiment) of the wing shafts 11 are provided on the end face 2A of the base portion 2 so as to be annularly arranged. Each of the wing shafts 11 is fixed at its front end (corresponding to one end) in the axial direction to the end face 2A of the base 2 and approaches the rear end as it separates from the base 2 (end face 2A) The spacing between each other is increasing.

  The lateral rib 12 is a part that connects the adjacent wing shafts 11 to each other. In the present embodiment, the lateral ribs 12 include lateral ribs 12A, lateral ribs 12B, and lateral ribs 12C.

  A plurality of lateral ribs 12A are provided on the rear end (corresponding to the other end) side of the axial middle point (point C shown in FIG. 1) of the wing shaft 11. In other words, a plurality of lateral ribs 12A are provided in the range between the center point and the rear end of the wing shaft 11. The plurality of lateral ribs 12A are provided side by side in the axial direction of the wing shaft 11. Further, as shown in FIGS. 1 to 4 (in particular, FIG. 1), the plurality of lateral ribs 12A are all provided obliquely to the wing shaft 11. A portion of the skirt portion 10 on the rear side of the point C is a portion particularly susceptible to air when the shuttlecock 1 flies, and therefore, as in the present embodiment, the plurality of lateral ribs 12A are wing axis By arranging at an angle to 11, the shuttlecock 1 can be easily rotated during flight. Thereby, the improvement of rotation speed can be aimed at (refer the below-mentioned Example). Further, since the lateral ribs 12A are oblique to the wing shaft 11, the n-th (n is a natural number) lateral ribs 12A from the rear end are not continuous in the region sandwiching the wing shaft 11. For example, with respect to the wing shaft 11 in the center of FIG. 1, the rearmost (first from the rear end) lateral rib 12A in the right side (one side in the circumferential direction) of the figure and the left side (in the circumferential direction) The rearmost lateral rib 12A of the region on the other side) is connected to a different position in the axial direction of the wing shaft 11. However, the rearmost lateral rib 12A in the right side region of the figure is continuous with the third lateral rib 12A from the rear end of the left side region in the figure. Thus, it is desirable that the transverse rib 12A be continuous via the wing shaft 11. This can increase the strength and improve the productivity of the mold.

  In addition, although the horizontal rib 12A of this embodiment is provided in the back side from the middle point of the wing shaft 11, it is not restricted to this, You may provide the horizontal rib 12A also in front of the middle point. Specifically, the rotational speed can be improved by providing a plurality of lateral ribs 12A in a range from the rear end to about 2/3 of the length of the wing shaft 11.

  The transverse rib 12B is provided at a position closer to the base portion 2 (forward than the point C) than the plurality of transverse ribs 12A. Similarly to the lateral rib 12A, the lateral rib 12B is also provided obliquely with respect to the wing shaft 11. The lateral rib 12B is formed thicker than the lateral rib 12A. As a result, it is possible to emphasize (make it easy to recognize) that the blade shaft 11 is oblique to the wing shaft 11, and to further improve the number of rotations.

  The transverse rib 12C is provided at a position closest to the base portion 2 (that is, before the transverse ribs 12A and the transverse ribs 12B). The lateral rib 12C is provided to be orthogonal to the wing axis 11. That is, as shown in FIG. 4, the lateral ribs 12 C are formed in an annular shape, and connect the wing shafts 11 with each other while being orthogonal to the wing shafts 11. As a result, the length of the ribs is shortened as compared with the case where the lateral ribs 12C are provided obliquely, and weight reduction can be achieved. Moreover, the rigidity of the shuttlecock 1 can be further enhanced, and each wing shaft 11 can be made difficult to twist.

  The longitudinal rib 13 is provided substantially parallel to the wing shaft 11 between the adjacent wing shafts 11 (for example, at an intermediate position). The longitudinal ribs 13 are provided to intersect the plurality of transverse ribs 12A.

  A plurality of longitudinal ribs 14 (two in this embodiment) are provided between adjacent transverse ribs 12A so as to intersect the transverse ribs 12A.

  Further, a first blade H1 and a second blade H2 are formed in the skirt 10 by the respective ribs described above.

  The first blade portion H1 is configured by a wing shaft 11, a plurality of ribs 12A, and a longitudinal rib 13.

  On the other hand, in addition to the structure of the 1st blade part H1, the 2nd blade part H2 is provided with the longitudinal rib 14, and is comprised. That is, the second blade portion H2 is a region in which the number of ribs is larger than that of the first blade portion H1 (a region in which the density of the ribs is large). In other words, the second blade H2 has a smaller aperture ratio than the first blade H1.

  The first blade portion H1 and the second blade portion H2 are alternately arranged in the circumferential direction of the skirt portion 10. A boundary (boundary) between the first blade portion H1 and the second blade portion H2 is between the wing shaft 11 and the adjacent wing shaft 11 (longitudinal rib 13). By forming such a sparse and dense region of the blades in the skirt portion 10, the number of rotations can be improved more than in the case where the entire configuration is uniform (when the aperture ratio is the same).

  In the outer peripheral shape of the skirt portion 10 (see FIG. 4), the boundary of the longitudinal rib 13 is at the bottom of the valley recessed on the central axis side (inner side) of the shuttlecock 1, and the boundary of the wing shaft 11 is on the outer side. It is on the top of a mountain that has come out. In the rear end shape of the skirt portion 10 (see FIG. 1), the border of the wing shaft 11 is the bottom of the valley on the base 2 side (the top of the mountain in the opposite side in the circumferential direction) There are no valleys on the side of the base 2 between the wing shafts 11 (such as the position of the longitudinal ribs 13). In this case, since the stress is dispersed, the durability is improved.

<< Example >>
The skirt portion 10 of the shuttlecock 1 of the present embodiment was created by a 3D printer, and the number of rotations was measured. Moreover, as a comparative example, the shape of a skirt part formed the thing of the lattice-shaped conventional structure (skirt part 110 of shuttlecock 100 mentioned later), and compared rotation speed with the thing of this embodiment.

<Configuration of Shuttlecock 100 of Comparative Example>
The shuttlecock 100 of the comparative example will be described with reference to the drawings. Here too, the side on which the base portion 2 is provided is referred to as the front side, and the opposite side is referred to as the rear side.

  FIG. 5 is a side view of shuttlecock 100 of the comparative example. FIG. 6 is a perspective view of shuttlecock 100 viewed from the front. FIG. 7 is a perspective view of shuttlecock 100 viewed from the rear. FIG. 8 is a front view of shuttlecock 100 as viewed from the front.

  The shuttlecock 100 of the comparative example includes a base portion 2 and a skirt portion 110. The base unit 2 is the same as that of the above-described embodiment, and thus the description thereof is omitted.

  The skirt portion 110 of the comparative example has a wing shaft 111, a transverse rib 112, and a longitudinal rib 113.

  A plurality of (here, 16) wing shafts 111 are provided on the end face 2A of the base portion 2 so as to be annularly arranged in the same manner as the wing shaft 11 of the present embodiment (shuttlecock 1). The axial front end of each of the wing shafts 111 is fixed to the end face 2A of the base portion 2, and the distance from each other increases with distance from the base portion 2 (end face 2A).

  The lateral rib 112 is a part that connects the adjacent wing axes 111 with each other. In this comparative example, as the lateral ribs 112, a plurality of lateral ribs 112A provided on the rear end side of the axial mid point of the wing shaft 111 and a position closer to the base portion 2 than the lateral ribs 112A are provided. Side rib 112B.

  A plurality of vertical ribs 113 are provided between adjacent wing shafts 111. The plurality of longitudinal ribs 113 are orthogonal to the plurality of lateral ribs 112A. A plurality of longitudinal ribs 113 and a plurality of transverse ribs 112A intersect with a cross and are formed in a lattice shape.

  The first blade portion H11 and the second blade portion H12 are formed in the skirt portion 110 of the comparative example by these respective ribs. The second wing portion H12 is a region in which the number of longitudinal ribs 113 is larger than that of the first wing portion H11 (that is, at narrow intervals), and the density of the rib is large. In other words, the second blade H12 has a smaller aperture ratio than the first blade H11.

  The first blade portions H11 and the second blade portions H12 are alternately arranged in the circumferential direction of the skirt portion 110. The boundary (boundary) between the first blade portion H11 and the second blade portion H12 is between the wing shaft 111 and the adjacent wing shaft 111 (longitudinal rib 113).

  In the outer peripheral shape (see FIG. 8) of the skirt portion 110 of the comparative example, the boundary between adjacent wing axes 111 (vertical ribs 113) is the bottom of the valley recessed on the central axis side (inner side) of shuttlecock 100. And the border of the wing shaft 111 is at the top of the mountain that protrudes outward. Further, in the rear end shape of the skirt portion 10 (see FIG. 5), the boundary between the adjacent wing shafts 111 is at the bottom of the valley recessed to the base 2 side, and the boundary between the wing shafts 111 is the base 2 It is on the top of the mountain which jumped out to the side (back side) away from.

  That is, in the case of shuttlecock 100 of the comparative example, the boundary between adjacent wing shafts 11 is a valley on the side of base portion 2 (front side), and a valley on the central axis side (inner side) of shuttlecock 1 It has become. In this case, stress concentrates on the site and it is likely to be broken. In addition, by cutting the end (rear end) of the skirt portion 110, it is possible to further adjust the area ratio of coarse and dense, but also in this case, stress is concentrated on the cut portion and it becomes easier to break. . When the rear end of the skirt portion 110 is broken or scattered, the target function (the function to improve the rotational speed) is lost.

  On the other hand, in the shuttlecock 1 of the present embodiment, as described above, the boundary between the first blade portion H1 and the second blade portion H2 is on the top of the mountain (feather shaft 11) projecting outward, and the relevant portion is It is a valley on the base 2 side. In other words, between adjacent wing shafts 11 (such as the position of the longitudinal rib 13), the valley does not form a valley on the base portion 2 side, and when viewed from the side as shown in FIG. The shaft 11 is connected approximately linearly in an oblique direction. For this reason, as described above, the n-th (n is a natural number) lateral ribs 12A from the rear end in the region sandwiching the wing shaft 11 are not continuous. With such a configuration, concentration of stress on a portion between adjacent wing shafts 11 can be suppressed, and breakage is less likely to occur (suppression of breakage) than shuttlecock 100 of the comparative example. it can.

<Configuration of Shuttlecock 1 of Example>
The shuttlecock 1 of the following Examples 1-4 was created as an Example.

  Example 1 is a shuttlecock 1 shown in FIGS. 1 to 4.

  In the second embodiment, one vertical rib 14 is formed on the second blade H2 of the shuttlecock 1 according to the first embodiment (see the second blade H2 in FIG. 9). That is, the difference in aperture ratio between the first blade H1 and the second blade H2 is larger than that in the first embodiment.

  In the third embodiment, the shape of the lateral rib 12B in the shuttlecock 1 of the second embodiment is changed.

  FIG. 9 is a side view of the shuttlecock 1 of the third embodiment. In the third embodiment, one longitudinal rib 14 is formed more than in FIG. 1 (the second embodiment), and a transverse rib 12B 'is formed. The lateral rib 12B 'is configured by adding a film on the rear side of the lateral rib 12B such that the width increases in a curvilinear manner as the distance from the base portion 2 increases.

  In the fourth embodiment, ribs (longitudinal ribs 14) are added to the first blade portion H1 and the second blade portion H2 of the shuttlecock 1 of the third embodiment (FIG. 9).

  FIG. 10 is a side view of the shuttlecock 1 of the fourth embodiment. FIG. 11 is a perspective view of the shuttlecock 1 of the fourth embodiment viewed from the front. FIG. 12 is a perspective view of the shuttlecock 1 of the fourth embodiment viewed from the rear. FIG. 13 is a front view of the shuttlecock 1 of the fourth embodiment viewed from the front.

<Method of measuring rotational speed>
In the measurement of the number of revolutions, the front side of each shuttle was directed vertically downward, and a wind of 5-10 m / s in wind velocity was applied from below to measure the number of revolutions when the shuttle was suspended. In addition, the measurement of the rotation speed of each shuttle was performed in the state which does not provide the base part 2. FIG.

<Measurement result>
The measurement results of the rotational speeds of the comparative example and the example are shown in Table 1.

From Table 1, in shuttlecock 1 (Example 1) of the above-mentioned embodiment, compared with shuttlecock 100 of a comparative example, rotation speed has improved 40% or more.

  Further, in Example 2 in which the difference in density (difference in aperture ratio) is increased, the number of rotations is further improved, and in Example 3 in which the shape of the horizontal rib 12B is changed, the number of rotations is further improved. In Example 4, the rotation speed was almost the same as in Example 3.

  From the above results, it can be confirmed that the rotational speed can be improved as compared with the lattice-shaped one (comparative example) by providing the plurality of transverse ribs 12A all at an angle to the wing axis 11 as in Examples 1 to 4 The

=== Others ===
The above embodiments are for the purpose of facilitating the understanding of the present invention, and are not for the purpose of limiting the present invention. It goes without saying that the present invention can be modified and improved without departing from the gist thereof, and the present invention includes the equivalents thereof.

Reference Signs List 1 shuttlecock 2 base portion 2A end surface 10 skirt portion 11 wing shaft 12, 12A, 12B, 12B ', 12C lateral rib (rib)
13 Longitudinal Ribs 14 Longitudinal Ribs 100 Shuttlecocks 110 Skirts 111 Feather Shafts 112, 112A, 112B Horizontal Ribs 113 Longitudinal Ribs H1 First Wing H2 Second Wing H11 First Wing H12 Second Wing

Claims (7)

And the base
A skirt portion provided on an end face of the base portion;
A shuttlecock with
The skirt portion is
A plurality of wing axes arranged in an annular shape on the end face, and a plurality of wing axes each having an axial end fixed to the end face;
A plurality of ribs connecting the adjacent wing axes;
Have
All the ribs in the range between the predetermined position and the other end of the wing shaft are provided obliquely to the wing axis,
Shuttlecock that is characterized. A shuttlecock according to claim 1, wherein
A first blade portion and a second blade portion having an aperture ratio smaller than that of the first blade portion are alternately formed in the circumferential direction of the skirt portion using the ribs in the above range,
Shuttlecock that is characterized. The shuttlecock according to claim 1 or 2, wherein
The n-th (n is a natural number) rib from the other end in a region on one side in the circumferential direction of the skirt portion with respect to the wing axis;
The nth rib from the other end in the region on the other side of the circumferential direction with respect to the wing axis is connected to a different position in the axial direction of the wing axis,
Shuttlecock that is characterized. A shuttlecock according to claim 3, wherein
The n-th rib of the one side region is continuous with the other rib of the other side region via the wing axis.
Shuttlecock that is characterized. The shuttlecock according to any one of claims 1 to 4, wherein
A rib having a larger width than each rib of the range is provided obliquely to the wing axis at the one end side than the range.
Shuttlecock that is characterized. The shuttlecock according to any one of claims 1 to 5, wherein
The rib closest to the base is orthogonal to the wing axis,
Shuttlecock that is characterized. The shuttlecock according to any one of claims 1 to 6, wherein
The predetermined position is a midpoint of the wing axis,
Shuttlecock that is characterized.