Helicopter rotor system related vibration amplitude detecting system

Claim 2

A helicopter rotor system related vibration amplitude detecting system, comprising in combination; at least one vibration amplitude sensing device mounted to the helicopter in the vibrational sphere of the rotor system related vibration, said sensing device generating a signal which is indicative of the amplitude of the rotor system related vibration; a control unit having a housing including: first selector means; second selector means connected to the first selector means and connectable to each sensing device for selectively, electrically connecting each sensing device to said first selector means, said first selector means serving to selectively receive the generated signal from each sensing device; electrical control means for operating on the selected generated signal and producing an output signal within a selected frequency and amplitude range; display means for displaying indicia of the output signal; a receiving slot for a model module; and mounting means for a connector within the receiving slot; and a model module having a housing which is received within the receiving slot, said model module housing including: mounting means which engage the control unit mounting means for securing the model module to the control unit; a connector which engages the control unit connector for electrically connecting the model module to the second selector means; and electrical means selectively applied to the electrical control means by said second selector means for determining the selected frequency and amplitude range.

Claim 3

The combination as defined in claim 1, wherein the electrical means of said model module include variable resistors which are preset as a function of the dynamic rotor system of the helicopter.

Claim 4

The combination as defined in claim 2, wherein the electrical control means includes filter means, electrically connected to said first selector means for receiving the generated signal of a selected sensing device and to said second selector means for adapting the filter means to the dynamic rotor system of the helicopter.

Claim 5

The combination as defined in claim 3, wherein the electrical control means further includes: a scaling amplifier electrically connected to said second selector means and thereby to a variable resistor in the model module for controlling the gain thereof, said scaling amplifier receiving the output from said filter means; a full-wave rectifier circuit which receives the output from said scaling amplifier; and a damping and biasing circuit which receives the output from the rectifier circuit and drives the display means.

Claim 6

The combination as defined in claim 4, wherein the electrical control means further includes a transient squelch circuit electrically connected to the damping and biasing circuit for blocking signal transients when power is applied to the system which are caused by momentary instabilities of the system.

Claim 7

The combination as defined in claim 4, wherein the electrical control means further includes a square wave generator electrically connected to said first selector means for checking the operation of the control unit and model module.

Claim 8

A helicopter rotor system related vibration amplitude detecting system, comprising in combination: at least one vibration amplitude sensing device, mounted to the helicopter in the vibrational sphere of the rotor system related vibration, said sensing device generating a signal which is indicative of the amplitude of the rotor system related vibration; a control unit including: first and second selector means; said second selector means serving to selectively, electrically connect each sensing device to said first selector means, said first selector means serving to selectively receive the generated signal from each sensing device; electrical control means for operating on the selected generated signal and producing an output signal within a selected frequency and amplitude range; and display means for displaying indicia of the output signal; and a model module electrically connected to said second selector means and having fixed and variable resistors which are preset as a function of the dynamic rotor system of the helicopter and which are selectively applied to the electrical control means by said second selector means.

Claim 9

A helicopter rotor system related vibration amplitude detecting system, comprising in combination: at least one vibration amplitude sensing device, mounted to the helicopter in the vibrational sphere of the rotor system related vibration, said sensing device generating a signal which is indicative of the amplitude of the rotor system related vibration; a control unit including: first and second selector means; said second selector means serving to selectively, electrically connect each sensing device to said first selector means, said first selector means serving to selectively receive the generated signal from each sensing device; electrical control means for operating on the selected generated signal and producing an output signal within a selected frequency and amplitude range; and display means for displaying indicia of the output signal; and a model module electrically connected to said second selector means and having fixed and variable resistors which are preset as a function of the dynamic rotor system of the helicopter and which are selectively applied to the electrical control means by said second selector means.

Claim 10

The combination as defined in claim 7, wherein the electrical control means includes filter means, electrically connected to said first selector means for receiving the generated signal of a selected sensing device and to said second selector means for adapting the filter means to the dynamic rotor system of the helicopter.

Claim 11

The combination as defined in claim 8, wherein the electrical control means further includes: a scaling amplifier electrically connected to said second selector means and thereby to a variable resistor in the model module for controlling the gain thereof, said scaling amplifier receiving the output from said filter means; a full-wave rectifier circuit which receives the output from said scaling amplifier; and a damping and biasing circuit which receives the output from the rectifier circuit and drives the display means.

Claim 12

The combination as defined in claim 9, wherein the electrical control means further includes a transient squelch circuit electrically connected to the damping and biasing circuit for blocking signal transients when power is applied to the system which are caused by momentary instabilities of the system.

Claim 13

The combination as defined in claim 9, wherein the electrical control means further includes a square wave generator electrically connected to said first selector means for checking the operation of the control unit and model module.

Claim 14

A helicopter rotor system related vibration detecting system, comprising in combination: at least one vibration amplitude sensing device mounted to the helicopter in the vibrational sphere of the rotor system related vibration, said sensing device including two accelerometers mounted with their sensitive axes at right angles and generating a signal which is indicative of the amplitude of the rotor system related vibration; a control unit having a housing including: a first multi-position switch; a connection for each sensing device for electrically connecting each sensing device to said first multi-position switch, said first multi-position switch serving to selectively receive the generated signal from each sensing device; electrical control means for operating on the selected generated signal and producing an output signal within a selected frequency and amplitude range; display means for displaying indicia of the output signal; a receiving slot for a model module; mounting means and a connector within the receiving slot; and a plurality of second multi-position switches; and a model module having a housing which is received within the receiving slot, said model module housing including: mounting means which engage the control unit mounting means for securing the model module to the control unit; a connector which engages the control unit connector for electrically connecting the model module to the plurality of first and second multi-position switches; and a plurality of resistors preset as a function of the dynamic rotor system of the helicopter and selectively applied to the electrical control means by respective ones of the plurality of first and second multi-position switches for determining the selected frequency and amplitude range.

Claim 15

A helicopter rotor system related vibration detecting system, comprising in combination: at least one vibration amplitude sensing device mounted to the helicopter in the vibrational sphere of the rotor system related vibration, said sensing device including two accelerometers mounted with their sensitive axes at right angles and generating a signal which is indicative of the amplitude of the rotor system related vibration; a control unit having a housing including: a first multi-position switch; a connection for each sensing device for electrically connecting each sensing device to said first multi-position switch, said first multi-position switch serving to selectively receive the generated signal from each sensing device; electrical control means for operating on the selected generated signal and producing an output signal within a selected frequency and amplitude range; display means for displaying indicia of the output signal; a receiving slot for a model module; mounting means and a connector within the receiving slot; and a plurality of second multi-position switches; and a model module having a housing which is received within the receiving slot, said model module housing including: mounting means which engage the control unit mounting means for securing the model module to the control unit; a connector which engages the control unit connector for electrically connecting the model module to the plurality of first and second multi-position switches; and a plurality of resistors preset as a function of the dynamic rotor system of the helicopter and selectively applied to the electrical control means by respective ones of the plurality of first and second multi-position switches for determining the selected frequency and amplitude range.

Claim 16

The combination as defined in claim 12, wherein the electrical control means includes a tuned band-pass filter, electrically connected to said first multi-position switch for receiving the generated signal of a selected sensing device and to certain ones of said plurality of second multi-position switches for adapting the tuned band-pass filter to the dynamic rotor system of the helicopter.

Claim 17

The combination as defined in claim 13, wherein the electrical control means further includes: a scaling amplifier, electrically connected to certain ones of said plurality of first and second multi-position switches and thereby to a variable resistor in the model module for controlling the gain thereof, said scaling amplifier receiving the output from said tuned band-pass filter; a full-wave rectifier circuit which receives the output from said scaling amplifier; and a damping and biasing circuit which receives the output from the rectifier circuit and drives the display means.

Claim 18

The combination as defined in claim 14, wherein the electrical control means further includes a transient squelch circuit electrically connected to the damping and biasing circuit for blocking signal transients when power is applied to the system which are caused by momentary instabilities of the system.

Claim 19

The combination as defined in claim 14, wherein the electrical control means further includes: a third multi-position switch; and a square wave generator elevtrically connected to said third multi-position switch for checking the operation of the control unit and model module.