HELICOPTER HUB MOUNTED VIBRATION CONTROL AND CIRCULAR FORCE GENERATION SYSTEMS FOR CANCELING VIBRATIONS
First Claim
1. A rotary wing aircraft, said rotary wing aircraft having a nonrotating aerostructure body and a rotating rotary wing hub,said rotary wing aircraft including a vehicle vibration control system,a rotating hub mounted vibration control system, said rotating hub mounted vibration control system mounted to said rotating rotary wing hub with said rotating hub mounted vibration control system rotating with said rotating rotary wing hub,a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to said relative rotation of said rotating rotary wing hub member rotating relative to said nonrotating body,at least a first nonrotating body vibration sensor, said 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, said at least a first nonrotating body circular force generator fixedly coupled with said nonrotating body,a distributed force generation data communications network link, said distributed force generation data communications system network link linking together at least said first nonrotating body circular force generator and said rotating hub mounted vibration control system wherein said rotating hub mounted vibration control system and said first nonrotating body circular force generator communicate force generation vibration control data through said distributed force generation data communications network,said 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, said controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with said controllable rotating force phase controlled in reference to said rotary wing aircraft member sensor data correlating to said relative rotation of said rotating rotary wing hubrotating relative to said nonrotating body wherein said vibration sensed by said at least first nonrotating body vibration sensor is reduced.
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Accused Products
Abstract
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.
134 Citations
19 Claims
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1. A rotary wing aircraft, said rotary wing aircraft having a nonrotating aerostructure body and a rotating rotary wing hub,
said rotary wing aircraft including a vehicle vibration control system, a rotating hub mounted vibration control system, said rotating hub mounted vibration control system mounted to said rotating rotary wing hub with said rotating hub mounted vibration control system rotating with said rotating rotary wing hub, a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to said relative rotation of said rotating rotary wing hub member rotating relative to said nonrotating body, at least a first nonrotating body vibration sensor, said 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, said at least a first nonrotating body circular force generator fixedly coupled with said nonrotating body, a distributed force generation data communications network link, said distributed force generation data communications system network link linking together at least said first nonrotating body circular force generator and said rotating hub mounted vibration control system wherein said rotating hub mounted vibration control system and said first nonrotating body circular force generator communicate force generation vibration control data through said distributed force generation data communications network, said 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, said controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with said controllable rotating force phase controlled in reference to said rotary wing aircraft member sensor data correlating to said relative rotation of said rotating rotary wing hubrotating relative to said nonrotating body wherein said vibration sensed by said at least first nonrotating body vibration sensor is reduced.
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14. A aircraft vibration control system, for a aircraft vehicle having a nonrotating aerostructure body and a rotating rotary wing hub, including,
a rotating hub mounted vibration control system, said rotating hub mounted vibration control system mounted to said rotating rotary wing hub with said rotating hub mounted vibration control system rotating with said rotating rotary wing hub, a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to said relative rotation of said rotating rotary wing hub member rotating relative to said nonrotating body, at least a first nonrotating body vibration sensor, said 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 force generator, said at least first nonrotating body force generator fixedly coupled with said nonrotating body, a distributed force generation data communications network serial link, said distributed force generation data communications system network serial link linking together at least said first nonrotating body force generator and said rotating hub mounted vibration control system wherein said rotating hub mounted vibration control system and said first nonrotating body force generator communicate and share force generation vibration control data through said distributed force generation data communications network, said at least first nonrotating body force generator controlled to produce a force with a controllable magnitude and a controllable phase, said controllable force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with said controllable force phase controlled in reference to said rotary wing aircraft member sensor data correlating to said relative rotation of said rotating rotary wing hub rotating relative to said nonrotating body and said rotating hub mounted vibration control system includes at least a first hub mounted vibration control system rotor with a first imbalance mass concentration, said first hub mounted vibration control system rotor driven to rotate at a first rotation speed greater than an operational rotation frequency of said rotating rotary wing hub, and at least a second hub mounted vibration control system rotor with a second imbalance mass concentration, said second hub mounted vibration control system rotor driven to rotate at said first rotation speed greater than said operational rotation frequency of said rotating rotary wing hub, wherein said vibration sensed by said at least first nonrotating body vibration sensor is reduced.
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16. A aircraft vibration control system, for a aircraft vehicle having a nonrotating aerostructure body and a rotating rotary wing hub, including,
a rotating hub mounted means for controlling vibrations, said rotating hub mounted means for controlling vibrations mounted to said rotating rotary wing hub with said rotating hub mounted means for controlling vibrations rotating with said rotating rotary wing hub, a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to said relative rotation of said rotating rotary wing hub member rotating relative to said nonrotating body, at least a first nonrotating body vibration sensor, said 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 force generator, said at least first nonrotating body force generator fixedly coupled with said nonrotating body, a means for linking together said first nonrotating body force generator and said rotating hub mounted means for controlling vibrations wherein said rotating hub mounted means for controlling vibrations and said first nonrotating body force generator communicate and share force generation vibration control data through said means for linking, said at least first nonrotating body force generator controlled to produce a force with a controllable magnitude and a controllable phase, said controllable force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with said controllable force phase controlled in reference to said rotary wing aircraft member sensor data correlating to said relative rotation of said rotating rotary wing hub rotating relative to said nonrotating body and, wherein said vibration sensed by said at least first nonrotating body vibration sensor is reduced.
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17. A vehicle vibration control system for controlling troublesome vibrations in a nonrotating vehicle body having a rotating machine member, said vehicle vibration control system including a vehicle vibration control system controller,
a rotating machine member sensor, for inputting vehicle rotating machine member data correlating to a relative rotation of said rotating machine member rotating relative to said nonrotating body into said vehicle vibration control system controller, at least a first nonrotating vehicle body vibration sensor, said at least first nonrotating vehicle body vibration sensor inputting at least first nonrotating vehicle body vibration sensor data correlating to vehicle vibrations into said vehicle vibration control system controller, at least a first nonrotating vehicle body circular force generator, said at least a first nonrotating vehicle body circular force generator for fixedly mounting to said nonrotating vehicle body wherein said at least first nonrotating vehicle body circular force generator is controlled by said controller to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, said controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with said controllable rotating force phase controlled in reference to said vehicle rotating machine member sensor data correlating to said relative rotation of said vehicle rotating machine member rotating relative to said nonrotating vehicle body with said vehicle vibration sensed by said at least first nonrotating vehicle body vibration sensor reduced by said controller, and a hub mounted vibration control system, said hub mounted vibration control system linked with said vehicle vibration control system controller.
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19. A method of controlling vibration, said method including,
providing at least a first nonrotating vehicle body circular force generator, fixedly mounting said at least first nonrotating vehicle body circular force generator to a nonrotating vehicle body, controlling said at least first nonrotating vehicle body circular force generator to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, providing hub mounted vibration control system, fixedly mounting said hub mounted vibration control system to a rotatable hub of said nonrotating vehicle body, providing a distributed force generation data communications network link and linking said hub mounted vibration control system together with said at least first nonrotating vehicle body circular force generator.
Specification