JPH0316897A - Radio control helicopter - Google Patents

Abstract

PURPOSE:To stabilize flying by a method wherein the roller of a mixing damper- incorporated plate is incorporated in the curve type rail of a blade pitch control plate mounted between blade holders. CONSTITUTION:When a rapid air pressure is exerted on a blade 1a, a blade pitch control plate 2 connected to a blade holder 1 is pressed downward around the axis of a feathering. Pressurization by a curve type rail is pushed back by the roller of a mixing damper-incorporated plate 3, and a helicopter performs stable flying. Further, through vertical slide of a slide ring 7, the lever of a mixing damper-incorporated plate control link 6 is vertically moved, and an amount of the mixing damper-incorporated plate 3 fitted by means of pressurization transmitted from the blade pitch control plate 2 is limited. This constitution enables a helicopter to perform stable flying even when a rapid air pressure is exerted.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a direct type (non-stabilizer bar type) radio controlled helicopter.

[Conventional technology]

A conventional direct type radio control helicopter will be described below with reference to FIGS. 10 to 16, but illustrations and explanations of some overlapping parts will be omitted.

In FIG. 10, (15) is a helicopter, and (14) is a transmitter that remotely controls this helicopter (15), which is designed to transmit high frequencies (3MHz to 3QMHZ) of radio waves. And this transmitter 14) 2
The helicopter (15) can be remotely controlled by moving the control sticks S, S2 back and forth, left and right, respectively.

FIG. 1l shows the power transmission mechanism and control mechanism of a radio control helicopter.

In this FIG. 11, (16) is an engine, approximately 1~
It has an output of 1.2 horsepower and approximately 10,000 to 10 horsepower during flight.
1DDr. Force rotation of p, m,.

(17) is a cooling fan that provides cooling air to the engine;
Reduce engine heating.

(18) is a clutch, which is a centrifugal clutch, i.e., a speed reduction mechanism (19
), freewheel (20) and tail gear box (
21), the transmission of rotational torque is stopped and the rotational speed of the engine (16) is reduced to 6000~7000r,
p. It is forced to connect when it reaches m.

(19) is a speed reduction mechanism that uses multiple gears to reduce the rotational speed of the engine (16) to about 1/8 to 1/12 and transmits the rotational torque of this rotational speed to a part of the main rotor (26). , engine (1) in part of the tail lobe (27)
The rotational torque of approximately 1/2 of the rotational speed of 6) is transmitted. Reduction types that reduce the rotational speed of this engine (16) include a transmission type in which the reduction gears (spar and bevel gear) are housed in a case and integrated, a reduction type with a pair of spur gears or bevel gears, and a combination of a synchro belt and a spur gear. There are three types of reduction types.

(20) is a freewheel, which is installed between the reduction mechanism (19) and the mast (8), so that the rotation of the engine (16) is transmitted to a part of the main rotor, and the rotation of a part of the main rotor. is set so that the engine (16) is not transmitted to the engine (16) during flight.
) stops, a part of the main rotor (16〉) can maintain rotation.

The tail gear box (2l) transfers the rotational torque transmitted from the reduction mechanism (19) to a part of the main rotor (2
6) The direction of power transmission is changed so that the rotating surface of the tail rotor portion (27) is approximately perpendicular to the rotating surface of step 6).

(22) is the throttle control mechanism and the engine (
16) is controlled by the engine control servo, and the rotation speed of the engine (1G) and part of the main rotor (2
6) Increase or decrease the rotation speed. In addition, in the fixed pitch method,
Vertical operation is performed by increasing or decreasing the lift force only by increasing or decreasing the rotational speed of a part of the main rotor.

(24) is a collective pitch control mechanism that simultaneously increases or decreases the pitch angle of the blades (1a) of the main rotor part (26) of all the blades (3 blades in the case of Fig. 15). Vertical maneuvers are performed by increasing or decreasing the lift generated by the aircraft.

(25) is a cyclic pitch control mechanism that tilts either the front, rear, left or right of (13) upward, and at the same time the upper swath spray.
(12) also tilts the same part in the same direction to perform horizontal direction (front/back, left/right) maneuvers.

(23) is the direction (counter-torque) control mechanism, the first
As shown in Figure 2, when the main rotor part (26) rotates in the main rotor rotation direction A, a torque C is generated in the opposite direction to the main rotor rotation direction A, and this torque C
works to rotate the aircraft.

Therefore, a part of the tail rotor (27) is rotated to generate tail rotor thrust B in a direction that prevents the rotation of the aircraft body. The horizontal stabilizer (28) and vertical stabilizer (29) divide the wind into upper and lower and left and right directions, and are used to maintain the straight line of the aircraft. In addition, the inside of the main rotor part (26) near the tip of the blade (1a) [
On the feathering axis (on the extension of [5) in Figure 2 D],
For stable flight, weights such as lead are embedded.

FIG. 13 shows an example of control of the lower swashplate (13) by the servo (30).

First, the rotation axis d is adjusted according to the information transmitted from the transmitter (14).
The position of the rotating shaft d2, which is centered on 1 and connected to this via a rond, is D. When moving from to D1, the lower swash plate (13) simultaneously moves in the direction of the dashed line D, / and in the direction of D, l/, and the lower swash plate (13) tilts toward the D, / side, and this The upper swash plate (l2) placed at the top of the lower swash plate (13) also tilts in the same way. Then, according to this slope, upper swash play} (12
) and the blade holder (
1) and the blade (1a) connected to the blade holder (1), respectively, are tilted in the minus or plus direction.

The position of the rotating shaft d2, which is centered around the rotating shaft d1 and connected to this via a rond, is D. When moving from to D2, the lower wash plate (13) simultaneously moves in the direction of solid line D2' and in the direction of D2M, the lower wash plate (13) tilts toward D2', and this lower wash plate (13) moves in the direction of solid line D2' and D2M. The upper swash plate (12) arranged on the upper part of the plate (13) is also tilted in the same way, and according to this tilt, the blade holder (1) and the blade holder (1) connected to the upper swash plate (12) via rods are connected to the upper swash plate (12) through the rod. The blades (la) respectively connected to the blade holder (1) are tilted in a negative or positive direction. Then, the rotation axis d2 is connected to the rotation axis d1 via a rod at a position D. and D2 are opened so that they can be stopped at any position indicated by the broken line arrow and the solid line arrow, respectively.

The movement of the servo (30) at these positions can be sufficiently controlled by the transmitter (14). Therefore, it is possible to delicately control the flight of the radio-controlled helicopter.

16A to 16E show the operation of each part of the main rotor part (26) and the corresponding flight, respectively.

Figures 16A to 16C show the upper swash plate (12) and lower swash plate (13) when the helicopter is viewed from the left side, that is, at 270 degrees to the nose direction as shown in Figure 14. Blade (LA-11
a-2) The upper swash plate (12), the lower swash plate (13), and the blade (12) when the radio control helicopter is viewed from the front, that is, from the nose direction in Figure 14, are shown. -1,l
a-2> is shown. And part of the main rotor (2
6) The operation of each part and the pitch angle (±5°) at that time, in each direction of travel, Fr indicates the front shaft connected to the servo via the front part of the lower swash plate (13) and the rod, Le is a low wash plate (
The left part of 13) indicates the left axis connected to the servo via the rod, and R1 indicates the right axis connected to the servo via the rod.
e indicates the rear shaft connected to the servo via the rear part of the lower wash plate (13) and the rond.

Figure 16A shows the helicopter in a hovering state.At this time, the swash plates [upper swash plate (12) and lower swash plate (13)] are attached to the aircraft. One of the upper swash plates (12) is connected to the blade (la-1> via the shafts b1 and c1 by a rond, and the other is connected to the blade (la-1) through the shafts b2 and c2.
It is connected to the blade (la-2) by a rod through the blade holder (1), the mast (
8), the hub (l1) of the rotor blade, etc. are omitted as they are not relevant to the explanation]. Each of these blades (Ia-1la-2) is kept substantially parallel to the fuselage. At this time, the blades (la-L la-2) are not tilted to either the plus or minus side.
) and the pitch angle of the blade (1a) connected thereto.

The pitch angle remains the same no matter where the rotating blade (1a) is at any position 3606.

Also, as mentioned above, if the pitch angle of the blade for hovering is not set in advance by the hub (11) of the rotor blade, the lower swash play (13) is pushed vertically upward while keeping it horizontal. This pushed-up position gives the blade (1a) an optimal pitch angle for hovering.

FIG. 16B shows the helicopter in the forward movement state. Low wash play} (1
3) By moving the servo (30) connected to the rear shaft Re via the rond so as to push up the rear shaft Re, the swash plate [upper swash play] (12) and lower swash plate } (13)
) in the forward direction by, for example, 5 degrees as shown in the figure.

At this time, the blade <la-1) is tilted 5 degrees to the minus side, and the blade (Ia-2) is tilted 5 degrees to the plus side, and in Fig. 14, the blade (1a) is tilted minus 5 degrees at 270 degrees.
It has a pitch angle of 180°, and as it rotates to the right, it becomes 0° at 0°, plus 5° at 90°, and 0° at 180°.

Then, by gyro precession, the helicopter moves forward by orienting the plane of rotation of the rotor at 0 degrees, that is, toward the nose.

FIG. 16C shows the helicopter in a retracted state.

Lower swash plate (l3
) by moving the servo (30) connected to the front shaft Fr via a rod so as to push up the front shaft Fr of the swash plate [upper swash plate (12) and lower swash plate] (13)).
Tilt it backwards as shown in the figure. The blade at this time (
Ia-1) is tilted 5 degrees to the positive side, blade <Ia-2) is tilted 5 degrees to the negative side, and in FIG. 14, the blade (1a) has a pitch angle of +5 degrees at 270 degrees, Thereafter, as it rotates to the right, it becomes 0° at 0°, -5° at 90°, and 0° at 180°. Therefore, the balance of lift is disrupted, and a thrust force is generated in a direction of 180 degrees, that is, backward, causing the vehicle to move backward.

FIG. 16D shows the helicopter moving to the left, and is a view of the front of the helicopter, that is, a portion of the main rotor (26) viewed from the front. As shown by the solid line, by moving the servo (30) connected to this right shaft R1 via a rod so as to push up the right shaft R1 of the lower swash plate (13) ) and lower swash play} (13) Tilt E to the left as shown in the figure. At this time, blade (la-1) tilts 5 degrees to the plus side, and blade (la-2) tilts 5 degrees to the minus side. However, in Fig. 14, the pitch angle of the blade (1a) is +5° when the angle is O°, and as it rotates to the right, it becomes 0° at 90°.
At 180° it becomes -5°, and at 270° it becomes 0°. Therefore, the balance of lift is disrupted, thrust is generated in the direction of 270 degrees, that is, to the left, and the vehicle moves to the left.

11 12 FIG. 16E shows the helicopter moving to the right, and is a view of the front of the helicopter, that is, a portion of the main rotor (26) viewed from the front. Lower wash play as shown by the solid line}
In order to push up the left axis Le in (13),
By moving the servo (30) connected through the rod, the swash plate [upper swash plate] (12) and lower swash plate} (
13) ] to the right as shown in the figure. At this time, the blade (la-1> is a 5° blade (l
a-2) is tilted 5 degrees to the plus side, and in Fig. 14, when the blade (1a) is at O degrees, the pitch angle is minus 5 degrees, and as it rotates to the right, it becomes 0' 18 at 90 degrees.
At 0° it is plus 5°, and at 270° it is 0°. Therefore, the balance of lift is disrupted, and thrust is generated in the 90° direction, that is, to the right, causing the ship to move to the right.

In FIGS. 16A to 16C, the blade (
By combining the mechanism for reducing the pitch angle in 1a) with the mechanism for increasing and decreasing the pitch angle of the blade (1a) in Figures D and E, forward, backward, left and right flight is achieved. Furthermore, the first
Although Fig. 6 shows a two-blade main rotor, the same can be said of a three-blade main rotor as shown in Fig. 15.

[Problem to be solved by the invention]

Now, in such a conventional direct-type radio-controlled helicopter, if it is subjected to sudden wind pressure due to gusts or enters turbulence during flight, the pilot visually confirms any abnormality in the flight condition, and then You must move the control sticks (Sl, S2) of the transmitter (l4) and perform the operations corresponding to each situation one after another until the flight is stable. There are many differences depending on the situation, and it is extremely difficult even for those with many years of experience and who have mastered the skill of piloting.
In some cases, expensive aircraft cannot escape destruction due to crashes. Furthermore, a gyro (a device that uses sensors or the like to detect flakiness on either side of the nose of the aircraft and automatically maintains stable flight) is expensive and cannot respond to all unexpected situations such as those mentioned above.

Therefore, not only is it difficult to maneuver, but the aircraft is also prone to crashing. 1,lj There is a risk of incurring major damage.

In view of this, the present invention aims to propose a radio-controlled helicopter that can fly stably without performing difficult operations even when subjected to sudden wind pressure.

[Means to solve the problem]

A first aspect of the present invention is a hub (11) of a rotor blade that is a part of a main rotor.
) and a plurality of blade holders (1) attached to the plurality of feathering bearings (llb) via a feathering shaft (5).
(2) and a mixing damper built-in plate (3) into which the mixing damper (3d) is compressed and fixed.
a blade pitch control plate, each having one end connected to a plurality of blade holders [1), and each having a roller (4a) of a lever part with a pole link (4) built into a notch (2c) at the other end. (2) The mixing damper built-in plate (
The rollers (3a) of 3) are hollowed out so that they can be respectively incorporated.

In addition to the first invention, the second invention provides a mast (8).
a slide ring (7) attached to the top of the slide ring (7) so as to slide up and down; and a plurality of feather rings each having one end connected to the slide ring (7) and the other end extending from the hub (11) of the rotor. Damper integrated control plate link (6) connected to the top of the bearing (llb)
The lever (6C) of the mixing damper built-in plate control link (6) is connected to the slide ring (7).
It was forced to move up and down in response to the slides.

[Effect]

According to the first invention described above, when the blade (1a) receives sudden wind pressure, the blade pitch control plate (2) connected to the blade (1) moves downward around the feathering axis (5). This pressurization is pushed back by the mixing damper built-in plate (3), allowing the helicopter (15) to fly stably.

Furthermore, according to the second invention, the slide ring (7) is
5 16 By sliding up and down, lever (6c) of mixing damper built-in plate control link (6)
) up and down to remove the mixing damper built-in plate (
3) is lifted by the pressure transmitted from the blade pitch control plate (2), thereby allowing the helicopter (15) to fly stably.

〔Example〕

Hereinafter, one embodiment of the present invention will be described in detail with reference to FIGS. 1 to 9.

FIG. 1 shows a portion (26) of the main rotor.

In Fig. 1, (8) is the mast, which is provided with a rod insertion groove (8C) as shown in Fig. 9B, and the shaft mounting screw is attached to the top end of the mast (8) as shown in Fig. A. It is provided in the center as shown by the broken line. And Figure 6 B, D
As shown in the figure, one end of the mast (8) on the side of the rotor blade hub attachment screw hole (8e) is inserted into the center of the rotor blade hub (11), and the rotor blade hub attachment screw of the mast (8) is inserted into the center of the rotor blade hub (11). Make sure that the hole (8e) and the mast connection screw hole (lid) of the rotor hub (l1) overlap.

Then, they are fixed by screws and nuts passed through these two screw holes, respectively.

(12) is the upper swash plate, the mast (8) passes through the center, one end of the push rod (4C) is attached to this side, and the other end of this push rod (4C) is connected via the ball link (4d). It is connected to one end of the lever part (4) with a ball link.The rotational torque of the mast (8) is transmitted by the upper swash plate movable lever (12a) connected to the side. The rotational torque of (8) is transmitted by the upper swash plate movable lever (12a), and the upper swash plate (12) rotates in the same way as the mast (8), and the lower swash plate (13) moves up and down. , the lever part with ball link (4) is moved up and down.

(1) is a blade holder to which a plurality of parts are attached via a feathering shaft [Fig. 5-1 (5)].

As shown in FIG. 3C, the mixing damper holder (male) (3C) is inserted into the hole of the mixing 17 1 damper assembly plate (3).
female) (3b) and this mixing damper holder (
By inserting the mixing damper holder (3b) into the mixing damper (3d) fixed in the hole of the mixing damper assembly plate (3), the mixing damper presser (female (3b) and The mixing damper (3[]) is compressed and fixed by the mixing damper holder (male) (3C), and the feathering shaft is inserted into the hole of the mixing damper installation plate (3) as shown in Fig. 5A. (5) is fitted, and the blade pitch control plate (3a) is inserted into the curved rail (2b) of the blade pitch control plate (2) as shown in Fig. 2A and C. (2) is penetrated by the feathering shaft (5) and also by the mixing damper presser (female) (3b) of the mixing damper built-in plate (3), and assembled with the mixing damper built-in plate (3). Mixing damper built-in plate (
3) and plaid pitch control play } (2
) is prevented from moving through the feathering axis, and the feathering axis (5) is fixed to the blade as shown in Figure 2B.
is inserted and connected to the blade pitch control plate bearing (1b) of the blade holder (1) via the double ball bearing part (2a) of the blade pitch control plate (2) as shown in Figure 2D. At the same time, as shown in Fig. 2C, the roller (4a) of the lever part with ball ring (4) is assembled into the notch (2C) of the blade pitch control plate (2), and at the same time, as shown in Fig. 4. A lever component rotating shaft (1C) with a ball link is inserted.A mixing damper (5a) and a mixing damper (5b) are fitted into the other side of the attachment part of the blade holder (1), and this part becomes the second part. As shown in Figures 6 and 7, it is inserted into the feathering bearing (llb) of the hub (11) of the rotor, and is inserted into the hole at the tip of the feathering shaft and the feathering shaft of the hub (11) of the rotor. flapping axis (
IIC) is attached by a screw and a nant passed through the hole. At this time, the mixing damper built-in plate 19 20 (3) is inserted into the mixing damper built-in plate fixing notch (3e) as shown in FIG. 3B.
la) is fixed by.

(7) is a slide ring, which is inserted into the shaft mounting hole [Fig. 9-1 (8d)] provided at the tip of the mast (8).
Inserted and fixed shaft} (8a), Figure 6D
As shown in the figure, the shaft (8a) is fixed by a spring (7C) fitted into the mounting groove (7b) of the shaft (8a). Plate control links (6) incorporating mixing bolts are attached to three link rod connection portions (7a) on the side of this slide ring (7) at equal intervals along the blade holder (1). Then, the slide ring (10) is rotated around the slide ring rotating shaft (10a).
9), and the rod (8C) arranged in the rod insertion groove (8C) provided in the mast (8) as shown in Fig. 9.
The slide ring (7) is connected to one end of the rod (8b), and further connected to the upper part of the other end of the rod (8b). and,
The mixing damper built-in plate control link (6) connected to this slide ring (7) is
As shown in FIGS. 8A and 8B, there is a link rod (6a) attached to one end of the link rod connecting portion (7a) of the slide ring (7), and a spring (6a) disposed on the link rod (6a). 6f), a link rod slide pipe (6e) arranged on this link rod (6a), a link lever (6b), and a lever for incorporating the mixing damper (
6C> and the ring rond slide amount limiting plate (6g) attached to the other end of the link rod connection part (7a)
From. And the slide ring lever (10)
The slide ring rotation axis (10) is controlled by the servo (30).
a) When lifted upwards around the axis, the slide ring (9) is lifted upwards;
) and this rod (8b) connected via
8b> is lifted upward. Then, the link rod (6a) attached to the link rod connection part (7a) on the side surface of this slide ring (7) is lifted upward, and the link lever (
6b), and at the same time push up the link lever 2l 22 at the other end fixed to the rotating shaft (6d) and the mixing damper built-in plate lever (6C) provided at this other end.
) moves downward. That is, as shown in FIG. 6D, when the slide ring (7) reaches the position indicated by the broken line, the lever (6C) for the mixing damper assembly plate moves to the x2 position. Therefore, at the position of the slide ring (7) shown by the solid line, the link rod (6a) and the link lever (6b) connected to this link rod are in the position and shape shown by the broken line, and therefore the mixing damper The assembly plate lever (6C) moves to the X1 position. In addition, the position of the mixing damper built-in plate lever (6C) is between the above-mentioned x1 and x2, and the link rod (6a)
It can be freely positioned by the spring (6f) placed on the link rod and the link rod slide pipe (6e) which lifts the slide ring upward and compresses this spring (6f). The position of this mixing damper built-in plate lever (6C) (a position further above x1) is limited by the link rod sliding amount limit plate (6g).

Now, if a radio-controlled helicopter having the main rotor part (26) described above encounters a gust of wind in the direction opposite to the nose direction, that is, a tailwind, or a place where the airflow is turbulent, during flight, wind pressure will be applied to the blades (1a). As a result, force due to wind pressure is also applied to the blade holder (1) which is connected and fixed to this blade (1a). At this time, the wind pressure applied to the blade (1a) causes a gust of wind to blow from below almost perpendicularly to this blade, that is, from the bottom to the top as shown in Fig. In this case, there is an arrow N2 at the rear of the blade (1a).
A force in the direction shown by is applied, and this blade (1a)
In conjunction with this, the blade holder (1) to which the blade holder (1) is connected and fixed tries to rotate about the feathering shaft (5) in the direction shown by arrow N3. On the other hand, the blade (1
The pitch angle in a) is from the transmitter (14) to the servo (30).
By controlling the lower swash plate (1
3) is moved up and down, and in conjunction with this, the upper swash plate (12) moves up and down, and one end of this upper swash plate (12) is connected to the upper swash plate (12), extending vertically, and the other end is attached with a ball link. It is determined by the up and down movement of the push rod (4C) connected to the blade holder (1) via the lever part (4).

Therefore, the push rod (4C) is fixed except for the vertical movement of the lower swashplate (13) by the transmitter ({4), and the blade holder (
1) tries to rotate in the direction shown by arrow N3 around the feathering shaft (5).The force that causes the feathering shaft (5) to rotate in the direction shown by arrow N3 is exerted by the lever part with ball link (4) and the feathering shaft (5) on the blade holder (1). It joins the blade pitch control plate (2) and the mixing damper built-in plate (3) that are incorporated through the plate. As shown in Figure 2D, one end of the blade pitch control plate (2) is connected to the blade pitch control plate bearing (1b) of the blade holder (1), and the other end is connected to the lever part with ball link (4). They are connected via rollers (4a). This lever component with a ball link (4) is forced to rotate by a ball bearing (↓d) arranged on a rotating shaft (IC) of the lever component with a ball link attached to the blade holder (1). [Push rod (4C) is a ball ring (4b)
) so that the force is not transmitted below the push rod (4C).

Therefore, the bearing for the blade pitch control plate (
1b) as an axis to push down one end of the blade pitch control plate (2), thereby connecting the ball link via the roller (4a) built into the notch (2C) of the blade pitch control plate (2). Push down the lever part (4).

At the same time, this force is applied to the rollers (3a) of the mixing damper integrated plate (3), which are integrated into the curved rails (2b) of the blade pitch control plate (2).
The force applied to this roller (3a) is transmitted to the mixing damper holder (female) (3b) and mixing damper holder (male) (3C) of the mixing damper built-in plate (3), and the force applied to the mixing damper holder (female) ) <3b) and mixing damper presser foot (male) (3C) and further compresses the incorporated mixing damper (3d) [
One end of the mixing damper built-in plate (3) is fixed by fitting the mixing damper built-in plate rotation stopper roller (lla) of the hub (11) of the rotating shaft into the mixing damper built-in plate fixing notch (3e)]. As the applied force attenuates, the elasticity of the mixing damper (3d) gradually pushes up the plate pitch control plate (2) via the roller (3a), and the notch of the blade pitch control plate (2) Push up the lever part (4) with a ball link through the roller (4a) built into the lever part (2C), and push up the lever part rotation shaft (1c) with a ball link that passes through the lever part (4) with a ball link. When the blade holder (1) is pushed up through the blade holder (1) and the applied force is completely removed, the blade (1a) returns to the pitch angle it was in before it was hit by the gust of wind.Therefore, the blade holder (1a) is pushed up by the amount of the harmful wind such as the gust of wind. The pitch angle of the blade (1a) is automatically increased/decreased, and when the wind disappears or the blade (1a) reaches a rotational position where it is not exposed to the wind, the blade (1a) returns to the pitch angle before receiving the wind, thereby achieving stable flight. is intimidated by

Furthermore, by moving the slide ring lever (10) up and down by the servo (30) using the transmitter (14), the mixing damper built-in plate lever (6c) of the mixing damper built-in plate control link (6) is moved to the link lever rotation axis. By moving up and down centering on (6c), the mixing damper built-in plate (
3) Limit the amount that can be raised. Therefore, the mixing damper (3) of the mixing damper built-in plate [3]
If the blade (1a) is subjected to such strong wind pressure that the elasticity of step d) alone cannot guarantee a stable flight, the mixing damper is removed using the mixing damper built-in plate lever (6C) of the mixing damper built-in plate control link (6). The mixing damper mounting plate (3) can be pushed down by the mixing damper mounting plate (3) by holding down the mixing damper mounting plate (3), or by positioning the mixing damper mounting lever (6c) shown in FIG. is lifted to the top, and the mixing damper built-in plate lever (6
c) 27 28 In either case, the mixing damper built-in plate (3) is prevented from lifting any further.
The force that tries to lift the mixing damper assembly plate (3) upward is suppressed by the lever (6c) for the mixing damper assembly plate, and a force in the opposite direction to this force, that is, a force that pushes the mixing damper assembly plate (3) back downwards. This occurs via the mixing damper (3d), and as a result, the mixing damper built-in plate (3) is pushed back downwards, and the blade pitch control plate (2) is Push down the curved rail (2b).

And this blade pitch control plate (2
) and a lever part (4) with a ball link that is connected via the roller (4a) incorporated in the notch (2c) of the ball link 1 and bar part (4). It is pushed downward by the rotation of the ball bearing (1d) disposed on the lever component rotation shaft (1c) with a ball link around the lever component rotation shaft (IC) with a ball link. Therefore, the plaid holder (
1) and the pitch angle of the blade (1a) connected to this blade holder (1) is reduced to prevent the aircraft from flying unstable due to lifting due to wind pressure.

Incidentally, in the above-described embodiment, the radio-controlled helicopter can similarly achieve stable flight even if the main rotor part (26) has a plurality of blades, such as two blades or three blades.

According to the above-mentioned radio-controlled helicopter, when it receives sudden wind pressure, the mixing damper built-in plate and the blade pitch control plate arranged on the plate automatically increase or decrease the pitch angle according to the wind pressure, and the wind pressure disappears. If stable flight cannot be achieved even with this, the pitch angle of the blade is reduced by controlling the mixing tamper built-in plate control link with the transmitter. Therefore, not only is it difficult to maneuver, but the risk of suffering major damage due to the aircraft crashing is avoided.

29 [Effects of the Invention] According to the first invention described above, the blade holders attached to the plurality of feathering bearings and the plurality of feathering bearings extending from the hub of the rotor blades of a part of the main rotor and the plurality of blade holders , one end of each blade is connected to a plurality of blade holders via a feathering shaft, and a blade pitch control plate is installed in a notch of the other end, each of which has a roller of a lever part with a ball link attached thereto, and furthermore, this plate pitch control plate By incorporating the rollers of the mixing damper assembly plate into the curved rails, the pressure from the sudden wind pressure applied to the blades is transmitted to the mixing damper assembly plate, and the pressure is attenuated by the elasticity of the mixing damper. At the same time, when the pressure is no longer applied, the pitch angle of the blade is returned to its original value to stabilize flight.

Further, according to the second invention described above, there is provided a slide ring attached to the upper part of the mast so as to slide up and down, and a plurality of slide rings each having one end connected to the slide ring and the other end extending from the hub of the rotor blade. A damper built-in control plate is connected to the top of the feather ring bearing, and the levers of the mixing damper built-in plate control link are forced to move up and down in response to the slide of the slide ring. The mixing damper built-in plate limits the amount of lift, reduces the pitch angle, and forces stable flight.

[Brief explanation of drawings]

The construction drawing is a perspective view showing an embodiment of the present invention, and FIGS. 2 to 9
15 is a perspective view showing a conventional example, and FIGS. 10 to 14 and 16 are diagrams showing the conventional example. (1) is a blade holder, (1a) is a blade, (2
) is the blade pitch control plate, (2a) is the double ball bearing part, (2b) is the curved rail,
(2C) is a notch, (3) is a mixing damper built-in plate, (3a) is a roller, (3b) is a mixing damper holder (female), (3C) is a mixing damper holder (male), ( 3[1] is the mixing damper, (3
e) is a notch for fixing the mixing damper built-in plate, (4) is a lever part with a ball link, (4a) is a roller (4b) is a pole link, (4C) is a push rod, (5) is a feathering shaft, (5a) ), (5b)
is the mixing damper, (6) is the mixing damper built-in plate control link, (6a) is the link rod, (6b) is the link lever, (6c) is the lever for the mixing damper built-in plate, (6d) is the link lever rotation shaft, ( 6e) Slide pipe for link rod,
(6f) is a spring, <6g) is a link rod sliding amount limiting plate, (7) is a slide ring, (7a) is a link rod connection part, (7b> is a spring mounting groove, (7C) is a spring, (8) is the mast, (8a) is the shaft, (8b) is the rod, (8C) is the rod insertion groove, (8d) is the shaft attachment hole, (8e) is the rotor hub attachment screw hole, (
9) is a slide ring, (10) is a slide ring lever, (11) is a rotor hub, (lla) is a mixing damper built-in plate rotation stop roller, (llb)
> is the feathering bearing, (lie) is the flapping shaft of the feathering shaft, (12) is the upper swashplate, (12a) is the upper swashplate movable lever, (13) is the lower swashplate, (
14) is a transmitter, (15) is a helicopter, (16) is an engine, (17) is a cooling fan, (18) is a clutch,
(19) is a reduction mechanism, (20) is a freewheel, (2
1) is a tail gearbox, (22) is a throttle control mechanism, (23) is a direction/reverse torque) control mechanism, (24) is a collective pitch control mechanism, (25) is a cyclic control mechanism, (26)
) is part of the main rotor, (27) is the tail rotor part,
(28) is a horizontal stabilizer, (29) is a vertical stabilizer, and (30) is a servo.

Claims (1)

[Claims] 1. Blade pitch is controlled between a plurality of feathering bearings extending from the hub of the rotary blade of the main rotor portion and a plurality of blade holders attached to the plurality of feathering bearings via the feathering shaft. A control plate and a mixing damper built-in plate are respectively disposed, and the mixing damper is compressed and fixed to the mixing damper built-in plate, one end of each of which is connected to the plurality of blade holders, and a ball is connected to the notch of the other end. A radio control helicopter characterized in that the rollers of the mixing damper incorporating plate are respectively incorporated into the curved rails of the blade pitch control plate in which the rollers of the linked lever component are incorporated. 2. A slide ring is attached to the top of the mast so as to slide up and down, and a damper-incorporated plate control link is connected at one end to the slide ring, and the other end of the damper-incorporated plate control link is connected to the rotor blade. It is connected to the upper part of a plurality of feather ring bearings extending from the hub of the damper, and the levers of the damper-incorporated plate control link are configured to move up and down respectively in response to the slide of the slide ring. The radio-controlled helicopter according to claim 1.