JPH0490999A - Helicopter vibration insulating device - Google Patents

Abstract

PURPOSE:To adjust tracking to a state within a reference to damp vibration by automatically regulating the length of a pitch control rod mounted on the root part of a rotor blade. CONSTITUTION:An upper pitch control rod 1 is coupled to a rotor blade 12 and a lower pitch control rod 4 to a rotary scissor 6 by means of a pin. Threading in an opposite direction to each other is applied to the lower part of the rod 1 and the upper part of the rod 4, and the two rods are inserted in the screw hole of a connector 2 in a manner to be brought into a vertically linear state. Teeth formed in the outer periphery of the connector 2 are securely mounted on the shaft of a motor 5 through a gear 3, and when the motor 5 is run, a distance between points (a) and (b) is increased and decreased according to the direction of the running. A signal, by means of which the tracking state of the end of a blade 12 is indicated, is transmitted through an amplifier 7 and a controller 8 to the motor 5 as a signal by means of which a rotation direction and a rotation angle are indicated. By running the given motor 5 of a plurality of motors by a given amount, a distance between the points (a) and (b) is regulated. This constitution damps vibration due to tracking of the blade 12.

Description

DETAILED DESCRIPTION OF THE INVENTION (Industrial Application Field) The present invention relates to a vibration isolating device for vibration isolating a rotor (blade) by automatically adjusting the tracking (rotation locus) of a helicopter rotor blade.

(Prior Art) FIG. 5 is a side view showing one of the conventional helicopter rotor blade tracking adjustment devices.
The trunking of the wing tip is measured by rotating the
By repeating the process of adjusting the length of rotor blade 12 by shim adjustment and rotating rotor blade 12 again, tracking was maintained in an appropriate state.

[Problem B that the invention attempts to solve] Above is the conventional helicopter rotor blade tiger.

The king adjustment device had the following issues to solve.

In other words, in conventional tracking adjustment, tracking survey,
Stopping the landing rotor, adjusting the shims, etc. were all done by hand, which was time consuming and required skill. Also, if play occurs during flight and the adjustment goes out of order, it is impossible to readjust it during flight.
They were forced to fly in conditions with a lot of vibration. In view of the above problems, the present invention measures tracking while in flight, and if there is an unbalanced rotor blade, automatically adjusts the Rondo length of that rotor blade to bring the tracking within the standard and damp vibration. The purpose of the present invention is to provide a helicopter rotor vibration isolator that is capable of

(Means for Solving the Problems) As a means for solving the above problems, the present invention adjusts the length of the pitch control rod provided at the root of the rotor blade to maintain trunking of the rotor blade within a standard, In a helicopter rotor vibration isolator for vibration isolating a rotor blade, a pitch control rod is divided into two parts perpendicularly to the axis near the center in the axial direction, and each of the divided end sides is threaded in opposite directions to the left and right; It is equipped with a gear-shaped connector that is screwed onto both divided ends of the same control rod and has meshing teeth on its outer periphery, and a gear that meshes with the outer periphery of the connector and is rotated reciprocally by a motor. It is an object of the present invention to provide a helicopter rotor vibration isolator having the following characteristics.

[Effect]

Since the present invention is configured as described above, it has the following effects.

That is, the pinch control rod attached to the base of each rotor blade of a helicopter is divided into two parts perpendicularly to the axis, each divided end is threaded in opposite directions, and both are connected to a gear-shaped connector. Since it meshes with a gear with a motor and rotates it back and forth, the combined length of the pitch control rod can be expanded or contracted simply by giving a rotation command to the motor, allowing trunking adjustment even during flight.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS. 1 to 4.

Fig. 1 is an overhead view of a helicopter equipped with the helicopter rotor vibration isolator of this embodiment, Fig. 2 is an enlarged side sectional view of the area marked by enclosure H in Fig. 1, and Fig. 3 is an - (2) A sectional view taken in the direction of the arrows. FIG. 4 is a schematic diagram of the system for tracking adjustment according to this embodiment.

In FIGS. 1 to 3, an upper pitch control rod 1 is coupled to the base of the rotor blade 12 for every rotor blade 2, and a lower pitch control rod 4 is connected to a rotary scissor 6 at the bottom corresponding to the rotor blade 12. The lower part of the upper pitch control rod 1 and the upper part of the lower pitch control rod 4 are respectively threaded in opposite directions, that is, with left-handed threads and right-handed threads, so that the upper and lower parts of the upper pitch control rod 1 and the upper part of the lower pitch control rod 4 are connected to each other by pins. It is screwed in a straight line.

That is, for example, when the connector 2 is rotated clockwise, points a and b in FIG.
The distance is configured to lengthen and shorten in counterclockwise rotation (or vice versa). The connector 2 has a gear shape, and a gear 3 meshes with the teeth provided on the outer periphery.The gear 3 is fixed to the shaft of the motor 5, and when the motor 5 rotates, the gear 3 engages with the teeth provided on the outer periphery. The pitch of the rotor blade 12 is controlled by expanding and contracting between the points a and b.

As shown in the system block diagram of FIG. 4, the motor 5 receives a signal indicating the tracking state of the tip of the rotor blade 12, for example, a signal reflected by a strobe light from a reflector provided at the tip of the rotor blade 12. device 7 and controller 8
The signal is transmitted as a signal instructing the direction and angle of rotation, and a predetermined motor 5 of the plurality of motors is
By rotating the required amount, the distance between the points a and b,
That is, the combined length of the upper pitch control rod 1, the connector 2, and the lower pitch control rod 4 is adjusted. As a result, the tracking of the blade tip of the rotor blade 12 can be kept within the standard value, and vibrations caused by tracking of the rotor blade 12 are attenuated.

The above adjustments can be made regardless of when flying, hovering, or landing.
This can be done automatically and quickly during rotor rotation.

As described above, according to this embodiment, the tracking adjustment of the rotor blade of a helicopter can be performed during flight and landing.
This has the advantage that it can be carried out quickly and at any time, so a smooth flight without vibrations can be achieved at all times. Further, there is an advantage that tracking adjustment can be performed without requiring a special worker, and does not require a skilled person.

(Effects of the Invention) Since the present invention is configured as described above, it has the following effects.

That is, it is possible to correct the tracking of the rotor blades even while in flight, and a vibration-free helicopter can be obtained.

[Brief explanation of drawings]

FIG. 1 is an overhead view of a helicopter equipped with a helicopter rotor vibration isolator according to an embodiment of the present invention, FIG. 2 is an enlarged side view of a portion of enclosure H in FIG. 1, and FIG. 3 is a view of FIG. FIG. 4 is a system block diagram of the tracking adjustment according to the above embodiment, and FIG. 5 is a side view of a conventional rotor blade tracking adjustment device. 1... Upper pitch control rod 2... Connector,
3...Gear. 4...Lower hinch control rod 5...Motor, 6...Rotating scissors 7...Amplifier (AID conversion) 8...Controller (calculation H) 12...Rotor plate.

Claims (1)

[Claims] In a helicopter rotor vibration isolator that adjusts the length of the pitch control rod installed at the root of the rotor blade to maintain the tracking of the rotor blade within a standard and to isolate the vibration of the rotor blade, a pitch control rod that is divided into two parts perpendicularly to the axis and has left and right opposite threads on both divided ends;
A gear-shaped connector that is screwed onto both divided ends of the pitch control rod and has meshing teeth on its outer periphery, and a gear that meshes with the outer periphery of the connector and is rotated reciprocally by a motor. Characteristic helicopter rotor vibration isolation device.