JPH03258692A - Vibration suppresser device for rotary wing plane - Google Patents

Abstract

PURPOSE:To suppress vibration by detecting vibration of a rotary wing plane and outputting a signal for suppressing airframe vibration based on the signal, to an unbalance motor. CONSTITUTION:An accelerometer or a rate gyro 4 detects vibration of a rotary wing plane shown with an arrow (a) and inputs to a computing device 2. The computing device 2 extracts a frequency elements, which causes airframe vibration, on the basis of the input, and outputs a command signal to an unbalance motor 3. The unbalance motor 3 generates equivalent opposite-phase vibration shown with an arrow (b) to the vibration occurring base on the command to offset airframe vibration. It is thus possible to reduce vibration.

Description

[Detailed description of the invention] [Industrial application field] The present invention relates to a vibration reduction device for a rotary wing aircraft.

[Conventional technology]

The conventional vibration reduction device for a rotary-wing aircraft, as shown in FIG. 2, has insufficient image reduction, has difficulty adjusting parameters, and cannot respond to changes in flight conditions.

[Problem to be solved by the invention]

The vibrations of a rotary-wing aircraft originate from the blades and are transmitted to the aircraft body via the engine transmission. Conventionally, as mentioned above, the vibrations have been suppressed by a dynamic vibration absorber attached to the aircraft body, which in principle cannot be reduced to zero, so there is a lower limit to its effectiveness. Furthermore, dynamic vibration absorbers require adjustment of their resonant frequency, which is difficult.

Furthermore, it is necessary to adapt to changes in flight conditions.
Normally this is not possible.

The present invention seeks to solve the above-mentioned drawbacks of conventional rotary-wing aircraft vibration reduction devices.

[Means to solve the problem]

The rotary-wing aircraft vibration reduction device of the present invention includes a rotary-wing aircraft vibration sensing device, an unbalanced motor that suppresses the vibration of the aircraft, and a signal from the sensing device that is input and outputs a command signal to the unbalanced motor based on the signal. It is equipped with a computing device that performs

[Effect]

In the present invention, vibrations generated by a rotary-wing aircraft are sensed by a sensing device, and this signal is input to a calculation device.

The calculation device calculates a command signal based on the signal from the sensing device, outputs this command signal to the unbalanced motor, and causes the unbalanced motor to generate an opening force in the opposite phase to the vibration of the rotary wing machine. Reduce aircraft vibration.

In the present invention, as described above, the unbalanced motor generates an equivalent force in opposite phase in accordance with the vibrations of the rotary-wing aircraft that occur, thereby effectively suppressing vibrations during flight.

〔Example〕

An embodiment of the present invention will be described with reference to FIG.

1 is a rotary wing aircraft body equipped with blades 8, and an engine transmission 7 for rotating the blades 8 is mounted above the aircraft body 1. 4 is transmission 7
accelerometer or rate gyro installed in the The connection between the transmission 7 and the fuselage 1 includes the fuselage 1.
A plurality of unbalanced motors 3 are installed which are driven by receiving electric power from a power supply device 9 inside. Each unbalanced motor 3 has its central axis 3 as shown in FIG. 1(b).
A mass 5 that is movable in the axial direction of the support shaft 6 is attached to the support shaft 6 which is rotatable around a and is arranged in the radial direction from the central axis 3a to the peripheral portion 3b.

The output of the accelerometer or rate gyro 4 is input to a calculation device 2 in the aircraft body 1, and the calculation device 2 extracts the frequency that causes vibration of the aircraft based on this input, and sends a command signal to the unbalanced motor. It is designed to output to 3.

In this embodiment, the vibration of the rotary-wing aircraft shown in the center part a of FIG. Based on this input, the arithmetic device 2 extracts a frequency component that causes body vibration, and outputs a command signal to the unbalanced motor 3. In response to the command signal, the plurality of unbalanced motors 3 driven by the electric power of the power supply device 9 generate vibrations shown by the arrows, which are equivalent to the vibrations of the rotorcraft that are occurring and are in the opposite phase, thereby suppressing the vibrations of the aircraft. cancel out In this case, by controlling the phase of the rotating masses 3 of the plurality of unbalanced motors 3, it is possible to adjust the phase of the vibrations generated by the motors 3 and make it in the opposite phase to the vibrations of the aircraft.
Furthermore, by controlling the radial position of the mass 5, the vibration force generated by the motor can be adjusted and made equal to the vibration force of the aircraft body.

In addition, the unbalanced motor 3 is installed at the joint between the engine transmission 7 and the fuselage 1, which is in the middle of the path where the vibration is transmitted from the blade, which is the source, to the fuselage. This can be effectively reduced.

〔Effect of the invention〕

As described above, according to the present invention, it is possible to automatically cancel and reduce vibrations of a rotary wing aircraft using an unbalanced motor while the rotary wing aircraft is in flight.

[Brief explanation of drawings]

FIG. 1(a) is an overall view of one embodiment of the present invention, FIG. 1(b)
) is an explanatory diagram of the unbalanced motor of the same embodiment, and FIG. 2 is an explanatory diagram of a conventional vibration reduction device for a rotary-wing aircraft. DESCRIPTION OF SYMBOLS 1--Airframe, 2--Arithmetic unit, 3--Unbalanced motor, 4--Accelerometer or rate gyro, 5--Mass, 7--Engine transmission, 8--Blade.

Claims (1)

[Claims] A rotary wing aircraft vibration sensing device, an unbalanced motor that suppresses the vibration of the aircraft, and an arithmetic device that receives a signal from the sensing device and outputs a command signal to the unbalanced motor based on the signal. Rotorcraft vibration reduction device.