JP6243703B2 - Anemometer - Google Patents

Description

  The present invention relates to an anemometer that can easily adjust the center of gravity in the left-right direction.

  Anemometers that indicate the direction in which the wind blows are widely put into practical use. In particular, anemometers that are integrated with an anemometer by adding a propeller to the anemometer have been put into practical use in various fields. A general anemometer has a structure in which a vertical tail is attached to the rear of a substantially cylindrical fuselage. The vertical tail allows the front of the fuselage to face the wind direction, and the direction toward the front of the fuselage is adjusted. The wind direction is detected by the detection. In addition, a propeller is provided in front of the wind direction anemometer body, and the wind speed is detected by detecting the rotation speed of the propeller.

  Such an anemometer is generally used by being attached to a vertically built column or the like so that the body can rotate along a horizontal plane. At this time, if the center of gravity of the rotating part that rotates along the horizontal plane of the anemometer deviates from the axis that is the center of rotation, a force that causes the anemometer to rotate by a moment is generated in addition to the wind force that the anemometer receives. End up. In addition, a part of the friction between the rotating part of the anemometer and the fixed base that pivotally supports the rotating part is increased, and a load is applied to some bearings and the like. In the wind direction anemometer in such a state, the fuselage is difficult to rotate, and the detection accuracy of the wind direction tends to be low. Therefore, it is important to adjust the center of gravity of the anemometer. The same applies to an anemometer that is not integrated with an anemometer.

  Patent Document 1 listed below describes an anemometer that can adjust the position of the center of gravity. This anemometer includes a gravity center adjusting lever with weights on the upper and lower portions of the outer surface of the fuselage.

JP 2001-215241 A

  Although the specific configuration of the center of gravity adjustment lever is not described in Patent Document 1, a mechanism for adjusting the position of the center of gravity in the front-rear direction is provided because it is a center of gravity adjustment lever for leveling the body in the front-rear direction. It is thought that. However, the center of gravity is preferably adjusted in the front-rear and left-right directions. In this case, for example, it is conceivable to add a weight for adjusting the position of the center of gravity in the left-right direction to the anemometer of Patent Document 1. However, the addition of such a weight may break the balance in the front-rear direction. This is difficult.

  Therefore, an object of the present invention is to provide an anemometer that can easily adjust the center of gravity in the left-right direction.

  In order to solve the above problems, the present invention is an anemometer in which the front of the fuselage faces the wind direction, and a part of the fuselage is rotatable about an axis along the front-rear direction of the fuselage and has a center of gravity. Is a left-right balance adjusting unit that is eccentric with respect to the shaft.

  According to this anemometer, the center of gravity of the left-right balance adjusting unit rotates around the axis by rotating the left-right balance adjusting unit, which is a part of the body, about the axis along the front-rear direction of the body. Therefore, the center of gravity of the body in the left-right direction can be changed by rotating the left-right balance adjustment unit. Thus, by changing the center of gravity of the body in the left-right direction, it is possible to adjust the center of gravity in the left-right direction of the rotating part that rotates along the horizontal plane of the anemometer. Further, since the left / right balance adjusting unit is a part of the body, the left / right balance adjusting unit can be easily rotated from the outside. Therefore, the anemometer of the present invention can easily adjust the center of gravity in the left-right direction.

  Moreover, it is preferable that the said left-right balance adjustment part is the circular shape centering on the said axis | shaft in the cross section perpendicular | vertical to the said axis | shaft.

  According to such a configuration, the outer shape of the anemometer does not change even if the left / right balance adjustment unit is rotated about the axis. For this reason, it is possible to prevent the wind flow around the anemometer from changing before and after adjusting the center of gravity in the left-right direction.

  In this case, the left-right balance adjusting unit may include a frame and a weight provided on the inner peripheral surface of the frame and having a center of gravity located at a position away from the shaft.

  The anemometer preferably further includes a front / rear balance adjustment unit having a weight movable along the front / rear direction of the body. By having the front-rear balance adjusting unit, the center of gravity in the front-rear direction can be adjusted independently of the center of gravity in the left-right direction. In this case, the center of gravity in the front-rear direction can be adjusted directly from the outside of the anemometer if the adjustment portion of the front-rear balance adjustment unit is exposed.

  The left / right balance adjusting unit and the front / rear balance adjusting unit are preferably arranged at positions where the rotation shafts rotating in order to face the wind direction sandwich each other in the front / rear direction. By arranging the left / right balance adjustment unit and the front / rear balance adjustment unit in the front / rear direction, the weight of these adjustment units is distributed back and forth with respect to the rotation axis. Therefore, even if these adjusting parts are heavy, an anemometer that can easily balance the weight in the front-rear direction can be realized.

  In the anemometer described above, a propeller for detecting the wind speed is preferably provided at the tip of the body. In this case, the anemometer can be an anemometer.

  Furthermore, in this case, it is preferable that the left-right balance adjusting portion is a portion including the tip portion of the body. When a propeller is provided, a mechanism for pivotally supporting the propeller and a mechanism for measuring the rotation of the propeller are provided inside the body. In this case, the part including the tip of the fuselage is generally detachable, and the mechanism is installed in the fuselage with the part including the tip removed, or a shaft that supports the propeller. Is attached to the mechanism. Therefore, if the left / right balance adjustment part is a part including the tip part, a part of the trunk that can be removed to provide a mechanism for supporting the propeller in the fuselage and the right / left balance adjustment part are provided. It becomes possible to serve as well. Therefore, it can suppress that a trunk is subdivided into many parts.

  As described above, according to the present invention, an anemometer that can easily adjust the center of gravity in the left-right direction is provided.

It is a perspective view which shows the anemometer which concerns on embodiment of this invention. It is the figure which looked at the body tip part from the back side. It is sectional drawing of the perpendicular direction along the central axis of the rear-end part vicinity of a fuselage | body.

  Hereinafter, preferred embodiments of the anemometer according to the present invention will be described in detail with reference to the drawings. In this embodiment, an anemometer and an anemometer in which the anemometer and the anemometer are integrated will be described as an example.

  First, an outline of the anemometer of the present embodiment will be described.

  FIG. 1 is a perspective view showing an anemometer according to an embodiment of the present invention. As shown in FIG. 1, the anemometer 1 includes a fuselage 10, a propeller 40, upper and lower tails 21 and 22, and a fixed base 50 as main components. Note that FIG. 1 shows a state in which the propeller 40 is removed for easy understanding.

  The body 10 includes a body main body 11, a body front end 12 and a body support 13 connected to the body main body 11. A portion composed of the body main body 11 and the body tip 12 has a streamlined shape extending in the front-rear direction of the anemometer 1. The outer shape is a circle centered on a central axis AXc extending in the front-rear direction in a cross section perpendicular to the front-rear direction. In addition, the outer diameter of the outer shape gradually increases from the front tip toward the rear, and gradually decreases from the maximum diameter point toward the rear. The maximum point of this diameter is located closer to the front, and the outer shape of the portion composed of the body main body portion 11 and the body tip portion 12 has a curved surface bulging outward as a whole. By setting it as such a shape, the Karman vortex which arises when an airflow flows around the fuselage | body 10 is suppressed, and unnecessary air resistance is made small.

  Further, the body main body 11 has a structure in which the front is opened and the inside is hollow, and the cavity is sealed at the rear part where the diameter is sufficiently small. Further, a screw hole 11H indicated by a broken line into which a set screw 31 described later is screwed is formed at the rear end portion of the body main body portion 11.

  The body front end portion 12 is a portion including the front end portion of the body 10 and is engaged with the body main body portion 11 so as to be rotatable with respect to the body main body portion 11 about the central axis AXc. The body distal end portion 12 is restricted from rotating relative to the body main body portion 11 by fixing a fixing nut 14 provided in front of the body distal end portion 12 to a fixing member (not shown). Further, the body main body 11 side of the body front end 12 is open, and the cavity in the body main body 11 and the body front end 12 are in a state where the body front end 12 is engaged with the body main body 11. A space having a predetermined size is formed by the cavity.

  The fuselage support part 13 extends downward and perpendicular to the central axis AXc in the vicinity of the center in the front-rear direction of the part composed of the fuselage main body part 11 and the fuselage front end part 12, and is integrated with the fuselage main body part 11. ing. The body support portion 13 has a cylindrical shape.

  Further, a shaft 15 extends from the inner side to the outer side of the body 10 at the front end of the body 10 (the front end of the body front end portion 12). Specifically, the shaft 15 extends from the inside of the screw hole of the fixing nut 14 provided in front of the body front end portion 12 to the outside of the body 10. The shaft 15 is configured to rotate around the central axis AXc. A screw hole is formed at the tip of the shaft 15. When the shaft 15 and the propeller 40 are fitted, the screw 41 is inserted into the screw hole of the shaft 15 and tightened, whereby the propeller 40 is attached to the shaft 15. Fixed. Accordingly, when the propeller 40 rotates, the shaft 15 rotates together with the propeller 40. Although not particularly illustrated, a member that supports the shaft 15, a member that is driven by the rotation of the shaft 15, and the like are disposed in the space in the body 10.

  On the other hand, on the rear side of the fuselage main body 11, an upper tail 21 that extends above the fuselage 10 and a lower tail 22 that extends below the fuselage 10 are provided. That is, the upper tail 21 and the lower tail 22 are vertical tails. The upper tail 21 and the lower tail 22 of the present embodiment have substantially symmetrical shapes with respect to the central axis AXc. In addition, the upper tail 21 and the lower tail 22 viewed from the side face each have a curved shape in which the height of the tail increases as it goes rearward, but the increase in the height decreases as it goes rearward. ing. Further, the rear portions of the upper tail blade 21 and the lower tail blade 22 have a curved shape toward the center axis AXc while being rounded from a position farthest from the center axis AXc, and a straight shape perpendicular to the center axis AXc. It is not. The upper tail 21 and the lower tail 22 having such a curved outer shape are less likely to be attached with frost than the straight tail.

  The fixed base 50 is a member for fixing the anemometer 1 to a support or the like. The fixed base 50 is pivotally supported by the body support portion 13, and the body 10 is rotatable about the rotation axis AXr with respect to the fixed base 50. Hereinafter, a portion that rotates together with the body 10 with respect to the fixed base 50 is referred to as a rotating portion. In addition to the fuselage 10, the rotating portion includes the upper tail 21, the lower tail 22, the propeller 40, members in the fuselage 10, and the like. Further, a fixing member (not shown) for fixing the fixing base 50 itself to a column or the like is provided on the side of the fixing base 50 opposite to the side on which the body support portion 13 is pivotally supported.

  By the way, it is preferable that the weight applied to the fixed base 50 from the body support portion 13 is equally applied to the boundary surface between the body support portion 13 and the fixed base 50. By adding the weight in this way, it is possible to prevent an excessive load from being applied to a part of the boundary surface between the body support portion 13 and the fixed base 50, and the body 10 of the anemometer 1 is rotated by the wind. Friction when rotating around AXr can be reduced. This has the same tendency even when a bearing is used. In order to uniformly apply to the boundary surface between the trunk support portion 13 and the fixed base 50, the center of gravity of the rotating portion of the anemometer 1 may be positioned on the rotation axis AXr. In order for the center of gravity of the rotating part to be located on the rotation axis AXr, when the anemometer 1 is viewed from the front-rear direction (when viewed along the central axis AXc), the center of gravity of the rotating part on the axis of rotation AXr When the wind direction anemometer 1 is viewed from the horizontal direction, the center of gravity of the rotating portion in the front-rear direction may be positioned on the rotation axis AXr. Thereby, unnecessary rotation of the anemometer 1 due to the moment can be suppressed. In the present embodiment, the rotation axis AXr is orthogonal to the center axis AXc. For this reason, the center of gravity in the left-right direction of the rotating portion is the same even if it is located on the center axis AXc when viewing the anemometer 1 along the rotation axis AXr.

  Next, adjustment of the center of gravity in the front-rear direction and the left-right direction of the rotating part in the anemometer 1 will be described.

FIG. 2 is a view of the body front end portion 12 viewed from the rear side along the central axis AXc. In the present embodiment, the body front end portion 12 is a left-right balance adjusting unit that adjusts the center of gravity of the rotating portion in the left-right direction. The trunk | drum front-end | tip part 12 has the cowl 12a as a frame, and the weight 12b provided on the cowl 12a. The cowl 12a has an outer shape in a cross section perpendicular to the central axis AXc that is a circle centered on the central axis AXc. The rearmost end of the cowl 12a (trunk main body portion 11 side), the end face 12a ₁ are formed perpendicular to the center line AXc. Further, as shown in FIG. 1, the tip portion 12 has a diameter that decreases from the rear toward the front, so that the diameter of the inner wall surface 12a ₂ of the cowl 12a that contacts the end surface 12a ₁ also decreases toward the front. Further, on the distal end side of the inner wall surface 12a ₂ cowl 12a, are formed in contact with the inner wall surface 12a ₂ is a plane perpendicular 12a ₃ with respect to the central axis AXc. Then, has an opening 12H is formed in the center of the surface 12a _3, the shaft 15 shown in FIG. 1, extends fuselage from the opening 12H. Further, the weight 12b is the center of gravity C of the center axis is provided on the inner wall surface 12a ₂ of the cowl 12a unevenly distributed with respect AXc, Thus the body tip 12 is eccentric to the center axis AXc. The weight 12b may be provided by making a part of the cowl 12a thick. In this case, since the cowl 12a and the weight 12b can be integrally formed, it is not necessary to arrange the weight 12b on the inner peripheral surface of the cowl 12a later.

  Adjustment of the center of gravity in the left-right direction of the rotating portion by the left-right balance adjusting unit is performed as follows. When the cowl 12a of the body front end portion 12 is strongly pressed against the body main body portion 11 by the fixing nut 14, and the body front end portion 12 cannot rotate about the central axis AXc, the fixing nut 14 is loosened. Then, with the trunk tip 12 being rotatable, the trunk tip 12 is rotated about the central axis AXc. By this rotation, the center of gravity C of the body front end portion 12 rotates around the central axis AXc, and the center of gravity in the left-right direction of the rotating portion of the anemometer 1 moves. Then, when the anemometer 1 is viewed from the front-rear direction (when viewed along the central axis AXc), the body front end 12 is stopped at a position where the horizontal center of gravity of the rotating portion is located on the rotational axis AXr. In order to set the center of gravity in the left-right direction of the anemometer 1 to such a position, first, the fixed base 50 is supported horizontally. Therefore, since the rotation axis AXr is also horizontal, the rotating part including the body 10 and the like can rotate along the vertical plane. Then, the orientation of the rotating part is adjusted so that the center axis AXc of the body 10 faces the vertical direction and the front of the body 10 is on the upper side. If the left-right direction is not balanced in this state, the rotating part including the body 10 etc. will tilt to the left or right. For example, when the center of gravity of the rotating part in the left-right direction is positioned on the right side of the center axis AXc, the rotating part is inclined to the right side. In that case, the body front end portion 12 of the left / right balance adjustment unit is rotated. Specifically, since the center of gravity C of the body tip 12 is eccentric with respect to the center axis AXc, the body tip 12 is rotated so that the center of gravity C is on the left side, and the center axis with respect to the rotation axis AXr at the horizontal position. The AXc may be in a vertical state. Thereafter, the rotational position of the body front end portion 12 is fixed by the fixing nut 14.

  FIG. 3 is a cross-sectional view in the direction along the central axis AXc near the rear end of the body 10. In FIG. 3, the upper tail 21 and the lower tail 22 are omitted. As described above, the screw hole 11H is formed in the rear end portion of the body main body 11. The screw hole 11H may be formed directly in the body main body 11 or may be formed by press-fitting a cylindrical screw receiver in which the screw hole 11H is formed into the rear end of the body main body 11. good. A structure in which a screw receiver is used is preferable if the body body 11 is made of resin and the screw receiver is made of metal because the strength of the thread in the screw hole 11H can be secured. A set screw 31 is screwed into the screw hole 11H. The set screw 31 may be a slotted set screw or a hexagon socket set screw. However, if the set screw 31 is a slotted set screw, a flat-blade screwdriver is used when the entire set screw 31 is positioned in the screw hole 11H. A hexagon socket set screw is preferable because it may not enter the screw hole 11H. The set screw 31 acts as a weight, and the center of gravity in the front-rear direction of the anemometer 1 moves by moving the position of the set screw 31 back and forth. Accordingly, in the present embodiment, the set screw 31 is a front-rear balance adjusting unit.

  Adjustment of the center of gravity in the front-rear direction of the rotating portion by the front-rear balance adjusting unit is performed as follows. First, the fixed base 50 is supported horizontally. Therefore, since the rotation axis AXr is also horizontal, the rotating part including the body 10 and the like can rotate along the vertical plane. Then, the orientation of the rotating part is adjusted so that the central axis AXc of the body 10 faces the horizontal direction. In this state, when the center of gravity of the rotating portion in the front-rear direction is not on the rotation axis AXr, the front or rear of the body 10 is lowered downward. For example, when the center of gravity of the rotating portion in the front-rear direction is located in front of the rotation axis AXr, the front of the body 10 is lowered downward. In that case, the set screw 31 that is the front-rear balance adjusting unit is moved rearward. Conversely, when the center of gravity of the rotating portion in the front-rear direction is located behind the rotation axis AXr, the rear of the body 10 is lowered downward. In that case, the set screw 31 that is the front-rear balance adjusting unit is moved forward. In this way, the position of the set screw 31 is adjusted until the body 10 can be kept horizontal. Since the left / right balance adjustment unit and the front / rear balance adjustment unit are thus independent, the anemometer 1 of the present embodiment can independently adjust the front / rear direction center of gravity in addition to the left / right direction center of gravity.

  Thus, after the center of gravity in the horizontal direction and the center of gravity in the front-rear direction of the rotating part are positioned on the rotation axis AXr, the wind direction anemometer 1 has a vertical column or the like so that the fuselage 10 can rotate along the horizontal plane. Used fixed to. In use, the rotating portion rotates due to the action of the upper tail 21 and the lower tail 22, and the front of the fuselage 10 faces the wind direction. At this time, the direction of the body 10 is detected by a sensor (not shown) provided on the fixed base 50, and the wind direction is detected. Further, when the propeller 40 rotates together with the shaft 15, the rotational speed of the shaft 15 is detected by the sensor disposed in the body 10, and the wind speed is detected.

  According to the anemometer 1 of the present embodiment, the left / right balance center that is a part of the fuselage 10 is rotated about an axis along the longitudinal direction of the fuselage 10, thereby changing the center of gravity of the fuselage 10 in the horizontal direction. The center of gravity in the left-right direction of the rotating part can be adjusted. Therefore, the center of gravity in the left-right direction can be easily adjusted from the outside. If a clearance for inserting a tool such as a spanner is provided outside the fixing nut 14, the center of gravity in the left-right direction can be adjusted without disassembling the assembled anemometer 1, and the fixing nut 14 can be fastened again. It becomes possible.

  Further, since the cowl 12a of the left / right balance adjusting unit has a circular cross section with the center axis AXc as the center, the outer shape of the anemometer 1 does not change even if the left / right balance adjusting unit is rotated about the axis. For this reason, it is possible to prevent the wind flow around the anemometer 1 from changing before and after adjusting the center of gravity in the left-right direction.

  In the above embodiment, the left / right balance adjustment unit and the front / rear balance adjustment unit are disposed at positions where the rotation axis AXr is sandwiched in the front / rear direction, so that the weight of the weight 12b and the set screw 31 is based on the rotation axis AXr. Is distributed back and forth. Therefore, even when the weight 12b and the set screw 31 are heavy, it is possible to easily balance the weight in the front-rear direction.

  Further, in the anemometer 1, the left / right balance adjustment portion is a portion including the tip portion of the fuselage 10, so that the mechanism such as the shaft 15 that pivotally supports the propeller 40 can be removed for installation in the fuselage 10. The body part to be used can also serve as the left / right balance adjustment unit.

  As mentioned above, although the wind direction anemometer 1 of the said embodiment was demonstrated to the example about the anemometer of this invention, this invention is not limited to the wind direction anemometer 1 of the said embodiment.

  For example, in the present invention, an anemometer is not an essential requirement. That is, all the members used only for detecting the wind speed such as the propeller 40 and the shaft 15 from the wind direction anemometer 1 of the above-described embodiment may be omitted, and an anemometer that simply detects the wind direction may be used. However, it is preferable that the anemometer of the present invention is provided with a member necessary for an anemometer such as a propeller because the anemometer becomes an anemometer as in the above embodiment.

  In the above embodiment, the outer shape of the left / right balance adjusting unit on the surface perpendicular to the central axis AXc, that is, the outer shape on the surface perpendicular to the central axis AXc of the cowl 12a is a circle centered on the central axis AXc. The present invention is not limited to this. For example, a protrusion or the like may be provided on the outer surface of the cowl 12a so that the cowl 12a can be easily rotated around the central axis AXc.

  In the present invention, the front-rear balance adjusting unit is not essential. However, it is preferable to have the front-rear balance adjustment unit because the center of gravity in the front-rear direction can be adjusted. Even when the front-rear balance adjustment unit is provided, the front-rear balance adjustment unit may be provided on the same side in the front-rear direction as the left-right balance adjustment unit with respect to the rotation axis AXr.

  Further, the left / right balance adjustment unit may not be provided at a position including the tip of the body 10, and may be provided on the rear side of the body 10, for example.

  As described above, according to the present invention, an anemometer capable of easily adjusting the center of gravity in the left-right direction is provided, and can be used in fields such as an anemometer including an anemometer.

DESCRIPTION OF SYMBOLS 1 ... Wind direction anemometer 10 ... Body 11 ... Body main part 12 ... Body front-end | tip part 12a ... Cowl (frame)
12b ... Weight 13 ... Body support part 14 ... Fixing nut 15 ... Shaft 21 ... Upper tail 22 ... Lower tail 31 ... Set screw 40 ... Propeller 50 ...・ Fixed base AXc ・ ・ ・ Rotation axis AXr ・ ・ ・ Center axis

Claims (6)

An anemometer with the front of the fuselage facing the wind direction,
A part of the body is a left-right balance adjustment unit that is rotatable about an axis along the front-rear direction of the body and whose center of gravity is eccentric with respect to the axis .
A front / rear balance adjustment unit having a weight movable along the front / rear direction of the body;
The wind direction, wherein the left / right balance adjustment unit and the front / rear balance adjustment unit are disposed at positions where rotation axes that rotate in front of the fuselage to face the wind direction sandwich each other in the front / rear direction. Total. The anemometer according to claim 1 , wherein a propeller for detecting a wind speed is provided at a front end portion of the body. 3. The anemometer according to claim 2 , wherein the left-right balance adjustment unit is a portion including the tip portion of the body. An anemometer with the front of the fuselage facing the wind direction,
A part of the body is a left-right balance adjustment unit that is rotatable about an axis along the front-rear direction of the body and whose center of gravity is eccentric with respect to the axis .
Propeller for detecting the wind speed is provided at the tip of the fuselage,
The anemometer, wherein the left / right balance adjustment portion is a portion including the tip portion of the body . The anemometer according to claim 4 , further comprising a front-rear balance adjustment unit having a weight movable along the front-rear direction of the body. 6. The left / right balance adjusting unit includes a frame and a weight provided on an inner peripheral surface of the frame and having a center of gravity located at a position away from the shaft . An anemometer according to item 1 .

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