JPH057038Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a radio-controlled model helicopter, particularly to an improvement of its stabilizer drive mechanism.

[Prior Art] A model helicopter is well known in which a drive source and a receiver are mounted on a small model helicopter, and the drive source is controlled and radio-controlled by a command signal transmitted from a user's transmitter. A small engine was used to drive the helicopter's rotor.

However, in recent years, devices using an electric motor as the driving source have been proposed, and for example, Japanese Utility Model Publication No. 58-2395 shows a toy in which a rechargeable dry cell battery and a small electric motor are mounted on a helicopter body.

Therefore, with this type of conventional device, it is possible to obtain a relatively quiet model helicopter driven by an electric motor, and the model helicopter is gaining popularity as a hobby that is widely accepted, especially in urban areas.

Regardless of whether the model helicopter is driven by an engine or an electric motor, there is a need to make this type of model helicopter smaller and lighter, and improvements have been made to the mechanisms of various parts to meet these demands.

An important issue in model helicopters is to increase the stability of the aircraft, and for this purpose the weight distribution of each part must be extremely carefully considered.

In a model helicopter, the maneuverability of the aircraft is easily affected by the quality of the stabilizer drive mechanism that controls the angle of the rotor, and since this stabilizer drive mechanism is located at the top of the aircraft, it is particularly compact, lightweight, and has reliable control. It is desired to have responsiveness.

In each of the above methods, conventional model helicopters are equipped with a stabilizer drive mechanism similar to that of actual practical helicopters, and the structure is too complex to be applied to model helicopters, resulting in poor control. It lacked stability, tended to be large compared to the overall aircraft, and was a factor in increasing the weight of the upper part of the aircraft.

In particular, in recent electric motor-driven model helicopters as described above, there has been a particular demand for this type of reduction in size and weight, and there has been a particular demand for improvements in the stabilizer drive mechanism described above.

Figure 4 shows a conventional stabilizer drive mechanism for a model helicopter.
The rotor shaft 10, which is rotatably supported perpendicularly to the fuselage body, is driven by the driving force from the rotor shaft 10. Rotation of the rotor shaft 10 is transmitted to the rotor blade 12 through a Hiller-type head, which includes a gimbal plate 14 and a gimbal head 16.

That is, the gimbal head 16 is connected to the horizontal shaft 18 fixed to the upper end of the rotor shaft 10.
so that it is rotatably supported along the central axis of
Support screws 20 are screwed into both ends of the horizontal shaft 18 from the outside of the gimbal head 16 (only the screws at the top and front in the figure are shown).

Then, the aforementioned cylindrical gimbal head 1
The gimbal plate 14 is fixed to the bottom of the rotor 6, and rotor blades 12 are fixed to both ends of the gimbal plate 14, respectively.

Further, the aforementioned rotor shaft 10 is connected to a main shaft 24 driven by a motor via a center hub 22.

As described above, the rotor blade 12 is tilted by the rotation of the gimbal head 16 about the support screw 20, and this tilt determines the direction of movement of the aircraft.

In order to control the inclination of the rotor blade 12, a stabilizer 25 is provided on the gimbal head 16 in the Hiller type head, as is well known. That is, in the figure, a stabilizer shaft 26 is provided passing through the upper part of the gimbal head 16, and stabilizers (control wings) are fixed to both ends of the stabilizer shaft 26.

In the figure, the stabilizer shaft 26 is provided with a stopper 28 to prevent it from moving in the axial direction with respect to the gimbal head.
The stabilizer shaft is provided so that it can only rotate (in the direction of arrow 100).

In order to drive this stabilizer, the tilt of the swash plate is transmitted from a well-known swash plate to the stabilizer shaft 26 via a control rod 30 and a control lever 32, although not shown in detail. A movable joint 34 is provided between the control rod 30 and the control lever 32, and the well-known tilting of the swash plate is converted by the control rod 30 into an up-and-down movement of the movable joint. Rotation of the stabilizer shaft 26 by rotation of the control lever 32 (arrow 100)
transmitted to.

Therefore, the stabilizer 25 provided at the tip of the stabilizer shaft 26 moves the stabilizer in any direction depending on the direction of inclination of the swath plate, and the unbalance of resistance that occurs when the stabilizer rotates at this time causes the rotor blade to move. 12 is tilted in a predetermined direction by the gimbal head moving mechanism, thereby allowing the aircraft to turn in any direction.

Therefore, in the conventional device, by tilting the swash plate toward the elevator and the aileron, the tilt of the swash plate is controlled by the control rod 30 and the control lever 3.
2 to the stabilizer shaft 26, the stabilizer tilts according to the tilt direction of the swash plate at this time, and the air resistance that the stabilizer receives at this time allows the rotor blade 12 to direct the aircraft in any direction. .

[Problems to be Solved by the Invention] However, as described above, the conventional stabilizer mechanism has a control rod 30 and a control lever 32 on the outside of the gimbal head 16.
The structure consists of a structure in which the stabilizer shaft 26 is driven by arranging the In aircraft with low stability, there is a problem in that the stabilizer mechanism has a large effect on maneuverability.

In particular, there is a strong demand for electric motor-driven model helicopters to be lighter and smaller.
There is a problem in that a helicopter with good characteristics cannot be obtained with the stabilizer drive mechanism having the complicated structure.

The present invention was developed in view of the above-mentioned conventional problems, and its purpose is to provide a radio-controlled model helicopter with an improved stabilizer drive mechanism that can provide reliable maneuverability with a small and simple mechanism. There is a particular thing.

[Means for Solving the Problems] In order to achieve the above object, the present invention includes a cylindrical gimbal head to which a gimbal plate to which a rotor blade is attached is fixed, and a stabilizer drive mechanism attached to this gimbal head. In a radio-controlled model helicopter that adjusts the traveling direction of the aircraft by controlling the drive of a stabilizer, the cylindrical gimbal head has a shape with a cut groove of a predetermined width at the center of the upper end, and the stabilizer drive mechanism , a stabilizer shaft having a stabilizer attached to both ends thereof and passing through the gimbal head in a direction perpendicular to the kerf; and a stabilizer shaft disposed within the kerf to fix the stabilizer shaft in the longitudinal direction of the shaft and to be rotatable. a control lever having one end fixed to the fixed plate and extending in a direction perpendicular to the stabilizer axis; and a control lever provided at the other end of the control lever to transmit driving force from the swash plate to the control lever. A movable joint.

[Embodiments] Preferred embodiments of the present invention will be described below based on the drawings.

FIGS. 2 and 3 show a front view and a plan view, with the external cover removed, of a radio-controlled model helicopter incorporating the stabilizer drive mechanism according to the present invention, and the rotor blades are not shown in both figures.

In these embodiments, the helicopter uses a motor as its driving source, and includes a built-in rechargeable dry cell battery and a DC motor.

The main parts of the stabilizer drive mechanism in the above embodiment are shown in the perspective view of FIG.

The helicopter body 40 has upper and lower bearings 42, 4.
A main shaft 24 is rotatably supported by 4, and is rotationally driven in a fixed direction by a DC motor, which will be described later.

A center hub 22 is firmly fixed to the upper end of the main shaft 24, and as shown in FIG.
This allows for relative and smooth sliding between the two. That is, the ball-shaped slider 46 is loosely engaged with the cylindrical groove 16a provided on the lower side of the gimbal head 16, and the two are relatively rotatably connected by the support pin 48. As a result, the gimbal head 16 is connected to the main shaft 24. It can freely and smoothly rotate in a direction determined by a support pin 48 at its upper end.

The rotor blade 12 is fixed to the tip of the gimbal head 16 via the gimbal plate 14 in the same manner as in the past, and thereby the rotor blade 12 is tilted in the direction determined by the orientation of the stabilizer to achieve the desired vertical movement. and a turning action can be given to the helicopter body.

As described above, according to this embodiment, the gimbal head 16 and the center hub 22 can be moved relative to each other by the ball-shaped slider 46, and as a result, the conventional simple support screw 20 and horizontal shaft 18 can be moved.
Compared to the support mechanism according to the present invention (see FIG. 4), the gimbal head can be rotated very smoothly and with less friction.

In FIG. 1, the gimbal head 16 has a groove 16b formed in the upper end thereof by hollowing out the center of the head, unlike the conventional gimbal head 16. In the present invention, a stabilizer drive mechanism is incorporated in this groove 16b. There is. That is, a stabilizer shaft 26 is rotatably provided passing through the gimbal head 16, and stabilizers 50 are fixed to both ends of the stabilizer shaft 26.

The stabilizer shaft 26 passes through the stabilizer fixing plate 52 within a groove 16b provided in the gimbal head 16 of the stabilizer shaft 26. A control lever 54 is firmly screwed to the stabilizer fixing plate 52, thereby integrally connecting the control lever 54, the stabilizer fixing plate 52, and the stabilizer shaft 26.

In this embodiment, the control lever 5
A movable joint 56 is provided at the other end of the control rod 5, and as shown in FIG.
8 is connected to the swash mechanism.

Therefore, as is clear from the description of FIG. The control lever 54 and the stabilizer shaft 26 can be coupled within the cut groove 16b. Further, with this internally incorporated mechanism, the stabilizer 26 is prevented from moving in the axial direction by the stabilizer fixing plate 52, and there is also the advantage that there is no need to provide a conventional stopper or the like.

FIG. 2 shows a transmission mechanism from the stabilizer drive mechanism to the swash plate. As is clear from the figure, a non-rotating fixed side swash plate 60 is loosely engaged with the main shaft 24, and this fixed side swash plate 60 is loosely engaged with the main shaft 24. A swash plate 60 is supported so as to be tiltable in any direction.

As is well known, a rotating side swath plate 6 is disposed above the stationary side swath plate 60.
2 is provided, and this swash plate 6
2 rotates together with the main shaft 24 along the inclined surface of the stationary side 60, and as a result, the inclination applied to the stationary side swash plate 60 is directly applied to the stabilizer drive mechanism by the rotating side swash plate 62. In order to enable the rotation side swash plate 62 and the main shaft 24 to rotate synchronously, a swash plate drive arm 64 is fixed to the main shaft 24, and the rotation side swash plate 62 is attached to the drive arm 64. link 66
By coupling with the rotation side swash plate 62, the rotation of the main shaft 24 can be transmitted to the rotating side swash plate 62.

Therefore, as described above, when the rotating swash plate 62 rotates along the inclination of the stationary swash plate 60, the stabilizer drive mechanism moves the stabilizer 50 to the desired direction around the support pin 48 along this inclined surface. gives the rotation angle of, which results in
Air resistance caused by the rotational position of the stabilizer 50 causes the rotor blade 12 to change its blade angle in any direction via the gimbal head 16, thereby giving the aircraft desired vertical movement and turning action.

In order to give the fixed side swash plate 60 a desired inclination, the fuselage 40 is provided with an elevator servo motor 68 (FIG. 2) and an aileron servo motor 70 (FIG. 3).

Main shaft 72 of the elevator servo motor 68
converts the rotation of the servo motor 68 into a predetermined rotational motion via a predetermined reduction mechanism, and this is transmitted to the elevator rod 74.
The fixed side swash plate 60 is moved up and down by the vertical movement of 4.
can be tilted. Therefore, this elevator servo motor 68 is connected to the swash plates 60, 6.
2 gives an inclination of the fuselage 40 with respect to the machine axis direction, thereby giving a motion to move the fuselage forward.

On the other hand, the aileron servo motor 70 in FIG.
This rotational motion is transmitted as a tilt to the stationary swash plate 60 via the aileron rod 78, and this tilt gives the fuselage 40 a lateral tilt. Therefore, this swash plate 6
A tilt of 0.62 allows the aircraft to turn to the right or to the left.

In this embodiment, the main shaft 24 that rotates the rotor blade 12 is rotationally driven by a main motor 80 provided within the fuselage 40 .

In the embodiment, the main motor 80 is arranged so that its main shaft is vertical, and its main shaft pinion 82 protrudes from the lower part of the machine body and engages with a large gear 84 fixed to the main shaft 24.

As is clear from Figure 3, in this invention,
The main motor 80 is provided at a position offset from the rotation axis of the main shaft 24, and due to this offset, an effective space is formed within the fuselage 40.
You can save enough space to install other parts. In the embodiment, by providing the main motor 80 at a position shifted from the main shaft 24 in this manner, the above-mentioned elevator servo motor 68 is arranged substantially parallel to the main motor 80.

Conventionally, this type of main motor 80 is provided coaxially with the rotation axis of the rotor blade of the aircraft body.
As a result, extra space is required to arrange other parts within the fuselage 40, and the overall capacity of the helicopter body increases.However, according to the present invention, the main motor 80 The shift allows effective use of space.

Also, as is clear from FIG. 2, the pinion 82 fixed to the main shaft of the main motor is connected to the large gear 84.
A predetermined rotational driving force can be applied to the main shaft 24 with one deceleration, and conventionally, such a transmission mechanism used at least a two-stage gear mechanism,
According to this embodiment, since the desired reduction ratio is obtained using a single-stage reduction gear as shown in the figure, there is an advantage that the device can be downsized and the structure can be simplified.

Further, as is clear from the embodiment, such a one-stage reduction gear mechanism is provided at the bottom of the fuselage 40, and the reduction gear mechanism is provided at a position that almost protrudes from the aircraft body 40 to the bottom, so that the device can be made compact. There is an advantage of doing so.

2 and 3, the fuselage 40 is provided with a tail pipe 86, and a tail rotor hub 88 is provided at the tail end of the tail pipe 86. Although not shown, a well-known tail rotor is fixed to this hub 88.

As is well known, in order to change the inclination of the tail rotor hub 88, a tail pitch plate 92 is provided at the tip of the tail rotor shaft 90 and is movable in the axial direction.
is provided.

In order to rotationally drive the tail rotor shaft 90,
A tail rotor drive wire 94 made of piano wire or the like is extended within the tail pipe 86, and a bevel gear 96 is provided at the tip of this wire 94 within the fuselage 40.
A large bevel gear 98 provided at 4 interlocks with the bevel gear 96, and the rotation of the main shaft 24 is transmitted to the wire 94, and at the tail end of the tail pipe 86, the bevel gear pair 98, 100 again connects this to the tail rotor shaft 90. Driving force is being transmitted.

In order to move the tail pitch plate 92 in the axial direction of the tail rotor shaft 90 to change the pitch angle of the tail rotor, the tail pipe 86 is provided with a tail pitch wire 102 along the pipe 86, and one end of the tail pitch wire 102 is provided along the pipe 86. Main shaft 10 of a tailpitch servo motor 104 provided in the fuselage 40
6. This tail pitch wire 102 is connected to the tail pitch plate 92 via a link mechanism 108, and this plate 92 is moved along the axial direction of the tail rotor shaft 90, thereby arbitrarily changing the pitch angle of the tail rotor. can do.

As mentioned above, in this type of motor-driven helicopter, four motors must be built into the fuselage 40 as described above, and for this reason,
The above-described shift arrangement of the main motor 80 is extremely effective in increasing overall space efficiency.

As mentioned above, the model helicopter shown in this embodiment uses four motors to control the rotation of the rotor, the tilt of the swash plate for driving the stabilizer, and the tail pitch angle.
A rechargeable dry battery is provided as a driving source for this purpose, and in this embodiment, this rechargeable dry battery is used for the
It is provided below 0 in consideration of weight distribution.
FIG. 2 shows a dry battery pack with such weight distribution, and the rechargeable dry batteries in this example have a total of 7
There are built-in books, four on the front side of the fuselage 40 and three on the tail end. That is, the first dry battery pack 110 in FIG. 2 contains four dry batteries, and the second dry battery pack 112 similarly contains three dry batteries.

Therefore, by using the dry batteries distributed at the front and rear of the fuselage 40, the weight balance of the helicopter itself is maintained well, making it possible to obtain a more stable fuselage than conventional motor-driven model helicopters. .

[Effects of the invention] As explained above, according to the radio-controlled model helicopter according to the invention, it is possible to configure a stabilizer drive mechanism that can reliably drive the stabilizer with a small number of parts, and the helicopter airframe is It is possible to obtain a smaller size and a good weight balance.

[Brief explanation of the drawing]

Fig. 1 is a partial perspective view showing the stabilizer drive mechanism, which is a feature of the present invention, and Figs. 2 and 3 are front views showing the internal configuration of a radio-controlled model helicopter incorporating the stabilizer drive mechanism of Fig. 1. FIG. 4 is a partial perspective view showing a stabilizer drive mechanism of a conventional model helicopter. 12... Rotor blade, 14... Gimbal plate, 16... Gimbal head, 22... Center hub, 25, 50... Stabilizer, 26...
... Stabilizer shaft, 46 ... Ball-shaped slider, 4
8...Support pin, 54...Control lever,
56... Movable joint, 60... Fixed side swash plate, 62... Rotating side swash plate.

Claims (1)

[Claims for Utility Model Registration] A cylindrical gimbal head to which a gimbal plate to which a rotor blade is attached is fixed; a stabilizer drive mechanism attached to the cylindrical gimbal head; In the radio-controlled model helicopter that performs adjustment, the cylindrical gimbal head has a shape with a cut groove of a predetermined width at the center of the upper end, and the stabilizer drive mechanism has stabilizers attached to both ends, and the gimbal head a stabilizer shaft penetrating through the kerf in a direction perpendicular to the kerf; a fixing plate disposed within the kerf that fixes the stabilizer shaft in the longitudinal direction of the shaft and rotatably holds the stabilizer shaft; one end of which is fixed to the stabilizer shaft; A control lever fixed to the plate and extending in a direction perpendicular to the stabilizer axis; and a movable joint provided at the other end of the control lever and transmitting driving force from the swath plate to the control lever. A radio-controlled model helicopter.