Active vibration control systems

Claim 2

An active vibration control system for reducing vibration of a structure subject to primary vibration forces transmitted through a primary vibratory load path from a source of repetitive vibration, and secondary vibration forces, the system comprising a plurality of actuators connected at or across parts of the structure capable of relative motion at an exciting frequency, a first control loop comprising sensors for sensing forces in the primary vibratory load path and providing signals to a control unit incorporating time domain control logic for providing first actuator demand signals, a second control loop including a plurality of sensors for sensing said secondary vibration forces on the structure and providing signals to a control unit incorporating frequency domain control logic for providing second actuator demand signals, and summing means for summing the first and second actuator demand signals and providing resultant actuator demand signals for operating the actuators to reduce vibration of the structure.

Claim 3

A system as claimed in claim 1, wherein said primary vibratory load path comprises a plurality of mechanical struts interconnecting parts of the structure.

Claim 4

A system as claimed in claim 1 wherein said actuators are located in said primary vibratory load path.

Claim 5

A system as claimed in claim 2 wherein said actuators are integral with said mechanical struts.

Claim 6

A system as claimed in claim 1, wherein said parts of the structure comprise a gearbox and fuselage of a helicopter.

Claim 7

An active vibration control system for reducing vibration of a helicopter fuselage, said vibration resulting from primary vibration forces transmitted through a primary vibratory load path and secondary vibration forces from other sources, including a plurality of actuators connected at or across parts of the structure capable of motion at an exciting frequency, a first control loop comprising sensors for sensing forces in the primary vibratory load path and providing signals to a control unit incorporating time domain control logic for providing first actuator demand signals, a second control loop including a plurality of sensors for sensing said secondary vibration forces in the fuselage and providing signals to a control unit incorporating frequency domain control logic for providing second actuator demand signals, and summing means for summing said first and second actuator demand signals and providing resultant actuator demand signals to reduce vibration transmitted through the primary vibratory load path and said secondary vibrations in the fuselage.

Claim 8

An active vibration control system for reducing vibration of a helicopter fuselage, said vibration resulting from primary vibration forces transmitted through a primary vibratory load path and secondary vibration forces from other sources, including a plurality of actuators connected at or across parts of the structure capable of motion at an exciting frequency, a first control loop comprising sensors for sensing forces in the primary vibratory load path and providing signals to a control unit incorporating time domain control logic for providing first actuator demand signals, a second control loop including a plurality of sensors for sensing said secondary vibration forces in the fuselage and providing signals to a control unit incorporating frequency domain control logic for providing second actuator demand signals, and summing means for summing said first and second actuator demand signals and providing resultant actuator demand signals to reduce vibration transmitted through the primary vibratory load path and said secondary vibrations in the fuselage.