JP2900218B2 - Concrete floor finishing machine - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a finishing machine for a concrete casting floor, and more particularly to an improvement of a blade mounting structure in a concrete floor finishing machine.

[0002]

2. Description of the Related Art Conventionally, as this type of concrete floor finishing machine, there is, for example, a cast concrete floor finishing machine disclosed in JP-A-63-130860. This casting concrete floor finishing machine has a plurality of rotors in which a plurality of blades are equally and radially arranged, an airframe configured for a driver to board, and an engine mounted on a frame of the airframe. , A power transmission mechanism for transmitting power from the engine to each rotor, and two control rods for operating the rotor. The rotor shaft of each rotor is connected to a gear box so that the rotor shaft can be freely tilted at an appropriate angle with respect to the vertical axis, and the two control rods are respectively connected to the gear box via link mechanisms having universal joints. , So that the rotor shaft can be tilted in an arbitrary direction by the control stick.

[0003] In the casting concrete floor finishing machine constructed as described above, a driver on the body operates two control rods, and a rotor is connected via a link mechanism and a gear box connected to the control rods. Tilt the axis to the desired angle. And the processing surface (concrete casting surface) in the inclination direction
, And the aircraft is moved in the direction opposite to the rotation direction of the blade at the position where the pressure is increased, thereby finishing the floor surface.

In a non-boarding type concrete floor finishing machine having a configuration as shown in FIG. 14 in which a driver does not board, a tilt control of a rotor shaft is performed by wired or wireless remote control. The traveling and the finishing of the floor surface are performed according to the same principle as described above. In the figure, 1 is an airframe,
2 is a support plate of the fuselage 1, 3 is a drive motor for rotating the two rotors 10 in opposite directions, 13a to 13d are blades attached to each rotor so as to be adjustable in angle, 14 is a blade attachment member, and 15 is a blade attachment member. This is a bearing that pivotally supports an intermediate portion of the mounting member 14 on a base plate 18 fixed to the lower end of a rotating shaft 17 so as to be swingable around a radial axis. The base end 12 of the mounting member 14 is engaged with the circular groove 11 of the rotor 10, and the rotor shaft 1 is spline-connected to the rotating shaft 17.
By moving the rotor 10 up and down with 6, the angle of the blade can be adjusted. The rotating shaft 17 and the rotor shaft 16 are connected to the gimbal ring 2 on the base plate 18.
The rotation of the pulley 8 is made via the pulley 8.
Reference numeral 25 denotes a swing shaft supported on the support plate 2 so as to be tiltable in the X and Y directions, and rotatably supports the rotation shaft 17. 3
Drive motors 0 and 30a (30 not shown) incline the swing shaft 25 in the X direction through servo links 33 and 33a, and 35 and 35a drive the swing shaft 25 through servo links 38 and 38a. This is a drive motor for tilting in the Y direction.

[0005]

In the conventional concrete floor finishing machine as described above, the arrangement of the blades disposed on the left and right rotors, in particular, the pressing point for increasing the pressure exerted on the floor surface by the inclination of the blades. (Hereinafter referred to as a pressure action point) greatly affects the traveling properties of the aircraft, the movement controllability in the case of a non-boarding type, or the maneuverability and floor finishing performance in the case of a boarding type.

For example, as shown in FIG.
When the outer circles 13e to 13d of the left and right blades 13a to 13d are spaced apart from each other so as not to intersect with each other (see the rotation trajectory of the outer ends of the blades), the traveling performance is stabilized, but there is a gap between the left and right blade outer circles 13e. Therefore, an unfinished portion remains in this portion, and the body must be repeatedly moved many times, and the finishing time is extremely long. Therefore, normally, the left and right blades are arranged so that their outer circles 13e partially cross as shown in (b) or (c). In this case, if the crossing amount of the blade outer circumference circle 13e is small as in (b), a protruding portion 100 in which the concrete rises in a streak shape at the center portion occurs, and finishability is lost. Further, when the intersecting amount of the blade outer circle 13e is considerably increased as shown in (c), the above-mentioned protruding portion is not generated, but the traveling performance becomes unstable, and the movement control and the steering become difficult. Since the concrete surface has unevenness and inclination, the straightness of the aircraft is hindered, and the aircraft is rotated left or right. Correction rotation is added to correct this, but since the turning performance of the aircraft greatly depends on the position of the blade action point, this control and operation are extremely difficult. for that reason,
In particular, in the case of a boarding type, there is a problem that it takes a long time (about one year) for pilot training.

SUMMARY OF THE INVENTION The present invention has been made to solve the above problems, and an object of the present invention is to provide a concrete floor finishing machine in which the operation and control of the body can be easily performed irrespective of a boarding type or a non-boarding type. It is.

[0008]

SUMMARY OF THE INVENTION A concrete floor finishing machine according to the present invention comprises a support plate and a plurality of rotary members rotatably supported in such a manner that their vertical axes can be inclined with respect to the support plate and rotatable in mutually opposite directions. Shaft and the lower part of the rotating shaft
A plurality of blades are supported via a plurality of attached mounting members.
In concrete floor finishing machine is lifting, the attachment portion
A swing support portion for supporting the blade is provided on the material;
The supporting portion has a width in a radial direction of the rotation axis of the blade.
And the center of rotation
The blade is swingably supported by a shaft extending in a tangential direction of the rotating circle.

[0009] A bent attachment member having the swing support portion attached to the tip thereof, and a bent portion of the attachment member being arranged in a radial direction.
A bearing portion pivotally supported around a shaft of the rotating shaft;
A base plate fixed to the lower end of the shaft and to which the bearing portion is attached, and coupled to the rotating shaft so as to be vertically slidable and rotatable.
The rotor plate and the base plate by the rotor shaft.
And a circular groove of the rotor that engages a base end of the mounting member so that an angle of the blade can be adjusted.

[0010]

With the above construction, each blade is provided with a degree of freedom of vertical swing by the support shaft, so that the blade is always in parallel with the concrete floor surface irrespective of the inclination of the rotating shaft, and the blade is in contact with the concrete floor. A distributed load will act. Therefore, the position of the pressure application point moves in the direction of the rotation center, so that the turning performance is improved, and the controllability of the traveling operation and the turning operation of the body is improved.

Further, the support shaft is constituted by a bearing at the distal end of the mounting member, and the base end of the mounting member is engaged with the circular groove of the vertically movable rotor to maintain the degree of freedom of swing. The angle of the blade can be changed as desired.

[0012]

FIG. 1 is a perspective view showing the entire structure of the present invention, partly in section, and FIG. 2 is an exploded perspective view of a main part thereof. In both figures, 1 is a fuselage, 2 is a support plate, 3 is a motor which is a drive source installed on the upper surface of the support plate 2, and 5 and 5a are blade drive mechanisms provided on both sides of the motor 3. The output shaft of the motor 3 projects substantially vertically from the lower surface of the support plate 2 and is connected to drive shafts 6 and 6a (however, 6a is not shown) via a transmission mechanism. It is connected to pulleys 8, 8a (8a not shown) of blade drive mechanisms 5, 5a located below the support plate 2 via 7, 7a. In this case, a transmission mechanism such as a chain or a gear mechanism may be used instead of the belts 7 and 7a. Numerals 9 and 9a are cylindrical members fixed to the support plate 2 and rotatably supporting the pulleys 8 and 8a via bearings below the support plate 2 as shown in FIG. Since the blade drive mechanisms 5 and 5a have almost the same structure,
Hereinafter, the blade drive mechanism 5 will be mainly described.

Reference numeral 10 denotes a rotor disposed below the support plate 2 and a circular groove 11 is provided on the outer periphery thereof. A base of an arm 12 connected to an L-shaped mounting member 14 is provided in the circular groove 11. The ends are slidably fitted. The bent portion of the mounting member 14 is pivotally attached to a bearing portion 15 mounted on the lower surface of a base plate 18 described later by a pin, and the blade 1 is moved around the pin by the vertical movement of the rotor 10 described later.
3a to 13d are tilted to change the angle of the blade. Further, a bearing 5 is provided at the tip of the mounting member 14.
The mounting member 52 attached to the blades 13a to 13d is pivotally connected to a substantially central convex portion 53 of a mounting member 52 by a support shaft 54 extending in a tangential direction of a rotating circle. For this reason, each blade is supported so as to be able to swing up and down around the support shaft 54. Thus, the swing support portion 50 of each blade is configured. A rotor shaft 16 having a spline formed on the outer peripheral surface is integrally attached to the rotor 10.

Reference numeral 17 denotes a rotary shaft having a spline nut provided on the inner peripheral surface thereof and having a rotor shaft 16 fitted therein so as to be slidable up and down. The rotary shaft 17 is disposed in the cylindrical member 9. A plate-shaped base plate 18 is fixed, and the lower end of the rotating shaft 17 that can be inclined in the X and Y directions is supported by a gimbal mechanism described below.

That is, reference numeral 20 denotes a gimbal ring which is a main component of the gimbal mechanism, and is disposed above the base plate 18 so as to surround the lower end of the rotating shaft 17. Reference numerals 21a and 21b denote gimbal X-axis bearings which are suspended from the lower surface of the pulley 8 (see FIGS. 2 and 3). Thus, the rotating shaft 17 is supported so as to be swingable around the X axis. Reference numerals 23a and 23b denote gimbal Y-axis bearings that stand upright on the upper surface of the base plate 18 to pivotally support a shaft 24 in the Y-axis direction coupled to the gimbal ring 20, and to rotate the rotary shaft 17 via the gimbal ring 20. It is swingably supported around the Y axis.

Reference numeral 25 denotes a cylindrical swinging shaft whose lower portion is located inside the cylindrical member 9 and is swingably supported by the support plate 2 via a spherical bearing (not shown, but a spherical bearing 80 which is abbreviated in FIG. 5). The upper end of the rotary shaft 17 is rotatably supported inside the lower end of the swing shaft 25 via a bearing 26.
The upper end of the rotor shaft 16 penetrating the rotating shaft 17 is connected to an adjusting screw 28 screwed into the upper end of the swing shaft 25 via a thrust bearing 27. 29 is an angle adjustment unit. Note that the angle adjustment unit 29 is manually rotated, but may be rotated by a motor.

Reference numeral 30 (see FIG. 2) denotes an X-axis servomotor mounted on the support plate 2 via a bracket 31, and as shown in FIG.
It is connected to a Y-shaped servo link 33 rotatably fixed to the swing shaft 25 by 4a and 34b. Reference numeral 35 denotes a Y-axis servomotor mounted on the support plate 2 via a bracket 36. The servomotor 35 is oscillated by a spherical bearing 39 provided orthogonal to the spherical bearings 34a and 34b of the servo link 33 via a servo lever 37. It is connected to an I-shaped servo link 38 rotatably fixed to the driving shaft 25. In addition,
The oscillating shaft 25a is also provided with an X-axis servomotor 30a, a Y-axis servomotor 35a and the like having the same configuration as described above.

In this embodiment configured as described above,
When the motor 3 is driven, the rotation is transmitted to the pulley 8 by the belt 7 and rotates the pulley 8. The rotation of the pulley 8 is transmitted to the base plate 18 via the gimbal X-axis bearings 21a and 21b, the gimbal ring 20, and the gimbal Y-axis bearings 23a and 23b. The rotation of the base plate 18 is transmitted to the rotor 10 via a rotor shaft 16 spline-coupled to a rotation shaft 17 integral with the base plate 18, and rotates the rotor 10 integrally, and the rotor 10 and the base plate 18 each have an arm. 12, the mounting member 14 held by the bearing portion 15, and the blades 13a-1
Rotate 3d. The other blade drive mechanism 5a
The blades 13a to 13d of the blade driving mechanism 5 rotate in the same manner,
The direction is opposite to 3d.

In this case, when the concrete is soft, if the pressure of the blades 13a and 13d in contact with the processing surface is too high, the processing surface will be roughened, and it is necessary to reduce the pressure. In addition, when the concrete gradually hardens, it is necessary to increase the pressure because a very low pressure has no effect. As described above, it is necessary to adjust the pressure of the blades 13a to 13d in contact with the processing surface depending on the condition of the processing surface. For this purpose, the angle adjustment unit 2
9, the angle adjusting screw 28 is moved up and down, and the rotor shaft 16 and the rotor 10 connected thereto are moved up and down. At this time, since the base plate 18 is held at a fixed position, the arm 12 engaging with the circular groove 11 of the rotor 10 rotates about the pin of the bearing portion 15 by the vertical movement of the rotor 10, so that the mounting member 14 , The contact positions and contact areas of the blades 13a to 13d with the processing surface change, and the pressure applied to the processing surface can be adjusted.

Next, the operation when the body 1 is moved will be described. Before that, the principle of movement of the body 1 will be described.

2 and 5, when the X-axis servo motor 30 is rotated in the forward or reverse direction and the servo link 33 is rotated in the A or B direction in FIG. 5, the swing shaft 25 connected thereto is rotated. Is the support, that is, A around the gimbal mechanism.
Or tilt in the B direction. The gimbal mechanism includes a gimbal ring 20, gimbal X-axis bearings 21a and 21b, and gimbal Y-axis bearings 23a and 23b at a lower end of a rotating shaft 17 supported coaxially with a swing shaft 25. Therefore, the rotor shaft 16 and the base plate 18 tilt in the A or B direction, and change the tilt angle in the A or B direction of the blades 13a to 13d connected thereto.

When the Y-axis servo motor 35 is rotated in the forward or reverse direction, and the servo link 38 is rotated in the C or D direction, the swing shaft 25 is rotated about the gimbal mechanism.
Or tilt in the D direction. Therefore, the rotor shaft 16 and the base plate 18 tilt in the C or D direction, and change the tilt angle in the C or D direction of the blades 13a to 13d connected thereto.

This will be described in more detail with reference to FIG. In addition,
In FIG. 6, arrow 30 / A indicates the X-axis servomotor 30.
13 when the swing shaft 25 is tilted in the direction A due to
The pressure applied to the processing surface a and the arrow 30 / B indicate the pressure applied to the processing surface of the blade 13c when the swing shaft 25 is inclined in the B direction. An arrow 35 / C indicates the pressure applied to the processing surface of the blade 13b when the swing shaft 25 is tilted in the C direction by the Y-axis servo motor 35, and an arrow 35 / D indicates the tilt shaft 25 also tilted in the D direction. This shows the pressure applied to the processing surface of the blade 13d when the blade 13d is pressed. The broken arrows indicate the direction of action of the reaction force in each of the above cases, that is, the propulsive force of the airframe 1, and the blade drive mechanism 5a also performs the action according to the above.

Next, the movement of the body 1 will be described with reference to FIG. In the case where the rotors 10 and 10a rotate in directions opposite to each other in the two blade drive mechanisms 5 and 5a, as shown in FIG. 7A, the pressure on the processing surfaces of the inner blades 13c and 13a is changed by the pressure of the other blades. When further increased, the fuselage 1
It moves in the direction opposite to the rotation direction of c, 13a, and therefore in the direction of the reaction force (for example, forward).

Further, as shown in FIG. 2B, if the pressure on the processing surfaces of the outer blades 13a and 13c is made higher than the pressure of the other blades, the airframe 1 increases the pressure due to the reaction force. Blades 13a, 13c
Move in the opposite direction (for example, backward) to the rotation direction of.

Further, as shown in FIG.
If the pressure on the processing surface of the blade 13d of the zero and the blade 13b of the rotor 10a on the opposite side of the blade 13d is increased as compared with the other blades, the reaction force causes the body 1 to move rightward, and (d) As shown in the drawing, if the pressure on the processing surface of the blade 13b of the rotor 10 and the blade 13a of the rotor 10a on the opposite side to the blade 13b is increased, the body 1 moves to the left due to the reaction force.

Further, as shown in FIG.
If the pressure on the working surfaces of the inner blade 13c and the outer blade 13c of the rotor 10a is increased, the reaction force causes the body 1 to turn clockwise, and as shown in FIG. Outer blade 13a and rotor 10
If the pressure on the processing surface of the blade 13a inside a is increased, the body 1 turns counterclockwise due to the reaction force.
In addition, besides the above, as illustrated in, for example, FIGS. 8C to 8G, various kinds of blades 13a to 13d of both rotors 10 and 10a that increase the pressure applied to the processing surface can be appropriately selected. Can be applied.

Next, the improvement of the controllability of the running operation and the turning operation of the aircraft according to the present invention will be described.

In the present invention, as shown in FIGS. 1 and 2, the blades 13a to 13d are oscillated by an oscillating support portion 50 comprising a bearing portion 51 provided on the mounting member 14 and a support shaft 54 for the mounting member 52. A degree of freedom of movement 55 is provided.

Here, the traveling direction and the turning direction of the aircraft are apparent from the description of FIG. 7 and FIG.
It depends on the radial positions (pressure application point positions) of the two sets of blades where the pressure on the floor surface increases due to the inclination of the left and right rotation shafts 17 and 17a.

Referring to FIG. 9, reference numeral 1 denotes a body frame, and left and right rotation shafts 17 and 17a are arranged symmetrically with respect to the body weight center position G at a distance of L / 2. 80, 80a are tiltable rotary shafts 17, 1
7a (actually, as shown in FIG.
5, 25a). The rotation directions of the rotating shafts 17 and 17a are opposite.
With this configuration, for example, the pressure of the blade 13d is increased by the inclination of + X1 of the rotating shaft 17, and at the same time, the + X2 of the rotating shaft 17a is increased.
By increasing the pressure of the blade 13b with the inclination of, both blades receive a + X reaction force, and the body moves in the + X direction. The same applies to the turning operation, for example, the rotating shafts 17 and 17a.
The aircraft turns counterclockwise with an inclination of -Y1 and + Y2, respectively. Generally, the inclination angle of the rotating shafts 17 and 17a is set to a maximum of 2 ° in any direction.

FIG. 15 shows the distribution of the load acting on the blade in the conventional example. (A) shows the arrangement of the rotating shafts 17 and 17a and the blades 13a and 13c. W is the body weight concentrated on the machine body center position G, B is the blade width, and R1 is the turning radius of the inner end of the blade.

If the inclination of the rotating shafts 17 and 17a is 0 °, all the blades have a load distribution of W / 8 as shown in FIG. Here, assuming that the rotating shaft 17 is inclined in the -Y1 direction so that, for example, the blade 13a bears a load of W / 8.times.1.4 and the blade 13c bears a load of W / 8.times.0.6, respectively. The load distribution is as shown in the figure.

FIG. 4D shows the position of the load center of gravity and the load value of both blades. The difference between the product of the load center of gravity position and the load value indicates the pressure increase value for moving the airframe and the point of action. The load difference (pressure increase value) between both blades is W / 8 ×
1.4−W / 8 × 0.6 = W / 10, and the point of action is as shown in equation (1).

[0035]

(Equation 1)

FIG. 10 shows the load distribution of the blade in the present invention. (A) Figure shows rotating shafts 17, 17a and blade 1
The arrangement of 3a and 13c is shown. Each blade has a swing support 5
0 gives a swing degree of freedom 55. Note that W,
B and R1 are the same as in FIG.

If the inclination of the rotating shafts 17 and 17a is 0 °, all the blades have a load distribution of W / 8 as shown in FIG. Here, similarly to the conventional example, the rotating shaft 17
Is tilted in the −Y1 direction, and for example, W
Assuming that a load of W / 8 × 0.6 is shared between the blades 13c and /8×1.4, respectively, since each blade has a swing degree of freedom 55, as shown in FIG. Then, the load distribution becomes evenly distributed in each blade.

The load center of gravity and the load value of the two blades at this time are as shown in FIG. 4D, and the difference between the product of the load center of gravity and the load value indicates the pressure increase value for moving the fuselage and the point of action. It will be. Load difference between both blades (pressure increase value)
Is W / 10, and the point of action is as shown in equation (2).

[0039]

(Equation 2)

From the above equations (1) and (2), it can be seen that the swing degree of freedom 55 moves the point of action of the pressure increase value toward the center of rotation.

In FIG. 15 and FIG.
7 has been described in the -Y direction, but + Y1, ±
Regarding the inclination in the X1 direction, the rotation axis 17a ± Y
The same applies to the inclination in the directions of 2, ± X2.

The traveling controllability and controllability of the aircraft are the most important points of the attitude of the aircraft, the heading controllability (turning controllability) for controlling the orientation of the aircraft. Excellent operability and controllability.

The heading controllability can be evaluated by the turning performance at a fixed position. In FIG. 11 (a), the rotating shaft 17,
17a is tilted in the directions of -Y1 and + Y2, and turned left. At this time, each blade forms the action point rotating circles 60 and 60a having the radius R2 as shown in FIG. Assuming that the body weight W is received by a circle of action point rotation, W1 and W2 shown in FIG.
Required by (5).

[0044]

(Equation 3)

(Equation 4)

(Equation 5)

Assuming that the resistance coefficient K of the blade on the ready-mixed concrete (K is a coefficient proportional to the peripheral speed), the reaction forces F1 and F2 from the floor surface can be obtained by equations (6) and (7).

[0046]

(Equation 6)

(Equation 7)

(D) As shown in the figure, the torques T1 and T2 around the machine center of gravity generated by the reaction forces F1 and F2 are obtained by the equations (8) and (9).

[0048]

(Equation 8)

(Equation 9)

In equation (10), the sum of T1 and T2 is the turning force. In the equation, K is a constant that is proportional to the peripheral speed, and thus the turning force is determined by the effect equation represented by the equation (11).

[0050]

(Equation 10)

[Equation 11]

Here, when L = 2 and R2, which is dimensionless, is R, and takes a range of 0 to 1, equation (11) becomes
Rewritten to 2). Effect formula of this turning force (12)
FIG. 12 is a graph in which is plotted for each value of R = 0 to 1.

[0052]

(Equation 12)

In FIG. 12, when the radius of action = 0 indicates that the turning force is 0, and when R = 1, R2 = L / 2, and the point of action passes directly below the center of gravity of the machine. Does not generate force. Then, when R = 0.577, the maximum turning force is generated.

R = 0.57 for generating the maximum turning force
Design 7 aircrafts. In the conventional example, R1 = 100 m
Assuming that m and B = 150 mm, the radius of action R2
Is calculated, and the distance L between the axes is calculated by the equation (14). The radius of action R2 = 185.7 mm The distance L between the axes L = 643.7 mm is shown in FIG.

[0055]

(Equation 13)

[Equation 14]

Although the configuration shown in FIG. 16 has the maximum turning performance of the airframe, the areas to be finished by the two sets of right and left blades do not overlap, so that an unfinished area is generated, which is unsuitable as a floor finishing machine. It will be.

If the amount of overlap is small, as shown in FIG. 17, streaks 100 are formed at the center of the finished surface formed by the left and right blades, and a good finished surface cannot be obtained. FIG. 13 shows an example of machine dimensions in which a sufficient amount of overlap is secured to obtain a good finished surface as a floor finishing machine.

In the configuration of FIG. 13, the difference in the turning force due to the difference in the method of supporting the blade between the conventional example and the present invention will be examined. Rotational axis distance L = 400 mm, R1 = 100 mm,
Assuming that B = 150 mm, the radius of action R2 is determined by the equations (1) and (2), and R is further determined. Conventional example R = 0.929 The present invention R = 0.875 Substituting these into equation (12) gives 0.127 (point A in FIG. 12) in the conventional example and 0.205 (point B in FIG. 12) in the present invention, which indicates that the turning performance has been greatly improved.

[0059]

As described above, according to the present invention, since the supporting portion of the blade is constituted by the swinging support portion which provides the degree of freedom of swinging up and down, the turning torque can be further increased, and the turning torque can be increased. A concrete floor finishing machine with improved operability and controllability with improved performance can be obtained. In addition, since the angle of the blade can be changed while maintaining the degree of freedom of swing, the blade angle can be freely set according to the hardness of the concrete floor surface.

[Brief description of the drawings]

FIG. 1 is an overall configuration diagram of an embodiment of the present invention.

FIG. 2 is an exploded perspective sectional view of a main part of FIG.

FIG. 3 is a cross-sectional view showing an attached state of a pulley and a cylindrical member of FIG.

FIG. 4 is an explanatory view of the rotation shaft tilting mechanism of FIG. 1;

FIG. 5 is an explanatory diagram of an operation of moving the body.

FIG. 6 is an explanatory diagram of an operation of moving the body.

FIG. 7 is an explanatory diagram of the operation of the body movement.

FIG. 8 is an explanatory diagram of an operation of moving the body.

FIG. 9 is an explanatory diagram of an operation of moving the body.

FIG. 10 is a load distribution diagram of a blade according to the present invention.

FIG. 11 is an explanatory diagram of the turning performance of the aircraft.

FIG. 12 is a characteristic diagram of turning torque.

FIG. 13 is an explanatory diagram showing an example of a body size according to the present invention.

FIG. 14 is an overall configuration diagram of a conventional example.

FIG. 15 is a load distribution diagram of a blade in a conventional example.

FIG. 16 is an explanatory diagram showing an example of the body dimensions when the turning performance is maximized.

FIG. 17 is an explanatory view showing the occurrence of a central projection on the finished surface.

FIG. 18 is an explanatory diagram showing an arrangement of blades.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Airframe 2 Support plate 3 Motor 5, 5a Blade drive mechanism 6 Drive shaft 7 Belt 8 Pulley 9, 9a Cylindrical member 10, 10a Rotors 13a to 13d Blade 14 Mounting member 16 Rotor shaft 17 Rotating shaft 18 Base plate 20 Gimbal ring 25 Rocking Active shaft 30, 30a, 35, 35a Servo motor 33, 33a, 38, 38a Servo link 50 Swing support 51 Bearing 52 Mounting member 53 Convex 54 Support shaft 55 Swing freedom

──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int.Cl. ⁶ , DB name) E04G 21/01 E04F 21/24

Claims (2)

(57) [Claims] 1. A support plate, a plurality of rotation shafts which are supported so that their vertical axes can be inclined with respect to the support plate, and which are rotatable in mutually opposite directions, and are radially mounted below the rotation shafts .
Multiple blades are supported via multiple mounting members
In the concrete floor finishing machine to be provided, a swing support portion for supporting the blade is provided on the mounting member.
The swing support portion is in the radial direction of the rotation axis of the blade.
At the center of the width at
A concrete floor finishing machine characterized in that the blade is swingably supported by a shaft extending in a tangential direction of a rotating circle having a center of rotation as a rotation center . 2. A bent attachment member having the swing support portion attached to a tip thereof, and a bent portion of the attachment member swingable about a radial axis.
A bearing portion which is supported at the lower end of the rotating shaft,
A base plate that, vertically slidable and is rotated communicatively coupled to said rotary shaft
And the rotor shaft has, vertically in the lower than the base plate by the rotor shaft
A rotor brought into motion, the proximal end portion of the mounting member and a circular groove of said rotor engaging the concrete floor finishing machine according to claim 1, wherein the adjustably configure the angle of the blade .