Tooling Structure: Interface between Cutting Edge and Machine Tool

A high-speed spindle can be very sensitive to rotating mass unbalance which has harmful effect on many types of rotating machinery. Therefore, the balancing procedure is certainly needed to reduce vibration in all high-speed rotating systems. In this study, an active balancing program using influence coefficient method and an active balancing device of an electro-magnetic type with both simple and reliable structures were applied to the developed high-speed spindle system. A gain scheduling control using influence coefficients of the reference model was proved to be effective in balancing the spindle system although its characteristics were changed. The stability of reference influence coefficients was verified by experiments with frequency response functions. The active balancing experiment of the manufactured spindle system using an active balancing program and device was also performed efficiently during the operation. As a result, controlled unbalance responses after balancing work were below the vibration limit at all rotating speed ranges including critical speeds.

Development of the active balancing device for high-speed spindle system using influence coefficients

Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass. The electronics housing cavity contains an electronics control system which receives sensor outputs and electrically controls and drives the first motor and the second motor such that the first imbalance mass and the second imbalance mass are driven at a vibration canceling rotation frequency greater than the operational rotation frequency wherein the helicopter rotary wing hub periodic vibrations are reduced.

Helicopter vibration control system and rotary force generator for canceling vibrations

A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, a distributed force generation data communications network link, the distributed force generation data communications system network link linking together at least the first nonrotating body circular force generator and the rotating hub mounted vibration control system wherein the rotating hub mounted vibration control system and the first nonrotating body circular force generator communicate force generation vibration control data through the distributed force generation data communications network, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hubrotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.

Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations

A balancer assembly 10 which automatically provides balancer limits, which achieves a balancing state while substantially minimizing short term vibration increases and which provides for multi-plane balancer dithering.

Method and apparatus for balancing

An electromagnetically actuated machine balancer (110) including a plurality of peripherally placed magnetic circuits and a power driver which selectively interrupts the magnetic flux (1210) through the circuits, thereby moving unbalanced rotors (350-351) in a desired manner to compensate for machine unbalance. The balancer assembly (110) includes a remote stationary microprocessor based controller (140), operating under stored computer program control and adapted to control assembly (110) in a manner which is specified by the stored program and certain environmental and measured parameters.

Electromagnetically actuated rotating machine unbalance compensator

Elektromagnetisch betätigter Unwuchtkompensator einer rotierenden Maschine

PROBLEM TO BE SOLVED: To provide a method and an apparatus for selectively, relatively quickly and efficiently balancing a rotary machine and a similar type apparatus. SOLUTION: The electro-magnetically operated machine balancing apparatus (110) includes a powered driver for correcting the unbalance of the machine by moving unbalanced rotors (350 to 351) by a required method by selectively intercepting a plurality of magnetic circuits arranged in the peripheral direction and the magnetic flux (1210) passing the magnetic circuits. The balancing apparatus assembly (110) includes a controller (140) based on a remote stationary micro-processor, and the controller operates under a computer program control stored therein, and is suitable for controlling the balancing apparatus assembly (110) by the method specified by the stored program, and environmental and measured parameters. COPYRIGHT: (C)2007,JPO&INPIT

Dyer Stephen William

Papers

Electromagnetically actuated rotating machine unbalance compensator

Elektromagnetisch betätigter Unwuchtkompensator einer rotierenden Maschine

Electro-magnetically operated device for correcting unbalance of rotary machine