Patent application number | Description | Published |
20090055129 | AIRCRAFT VEHICULAR PROPULSION SYSTEM MONITORING DEVICE AND METHOD - Methods and systems for monitoring rotating shaft shafts and couplings in an aircraft propulsion system is described. The measurement system/method provides for accurate and precise monitoring of a rotating shaft flexible coupling in a fixed wing aircraft vehicle propulsion system. The measuring system/method provides for a high reliability short take off vertical landing fixed wing aircraft in which the vertical propulsion dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular shaft coupling misalignment measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the propulsion system drive shaft. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame. The collar misalignment measuring system of the invention provide a misalignment measurement of the propulsion system drive shaft flexible coupling which relates to a critical performance of rotating shaft coupling in the operation of an aircraft vehicle. The method/system provides for monitoring a rotating drive shaft system and dynamically measuring a rotating drive shaft coupling in a fixed wing aircraft propulsion system. | 02-26-2009 |
20090254230 | Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations - An aircraft with at least one rotating machine creating troublesome vibrations, the aircraft comprised of an aerostructure, the aircraft including:
| 10-08-2009 |
20090294231 | Magneto-rheological fluid damper having enhanced on-state yield strength - Please replace the Abstract with the following amended Abstract: A magneto-rheological fluid valve includes a magnetic field generator having at least one electromagnetic coil and at least one magnetic pole having a pole length L | 12-03-2009 |
20100012768 | ROTARY WING AIRCRAFT ROTATING MACHINERY VIBRATION CONTROL SYSTEM - Helicopters and rotary wing aircraft vibration control system for controlling rotating machinery vibrations are provided for rotating machinery vibrations correlating with operational rotating frequencies. The vibration control system includes a first imbalance rotor with a first mass concentration, the first imbalance rotor driven to rotate with a first controllable phase, a second imbalance rotor with a second mass concentration, the second imbalance rotor driven to rotate with a second controllable phase, a third imbalance rotor with a third mass concentration, the third imbalance rotor driven to rotate with a third controllable phase, a fourth imbalance rotor with a fourth mass concentration, the fourth imbalance rotor driven to rotate with a fourth controllable phase. The vibration control system includes vibration sensors for monitoring the vibration and outputting vibration signals. The vibration control system includes a controller, the controller receiving an operational rotating frequency reference signal, the controller also receiving the vibration sensor signals with the controller controlling the first imbalance rotor first controllable phase, the second imbalance rotor second controllable phase, the third imbalance rotor third controllable phase, and the fourth imbalance rotor fourth controllable phase relative to the rotating frequency reference signal to produce a biaxial force which reduces the vibration signals outputted from the vibration sensors. | 01-21-2010 |
20100034655 | HELICOPTER HUB MOUNTED VIBRATION CONTROL AND CIRCULAR FORCE GENERATION SYSTEMS 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. | 02-11-2010 |
20100221096 | COMPUTER SYSTEM AND PROGRAM PRODUCT FOR CONTROLLING VIBRATIONS - The computer programmable system and program product include first program instructions for actively driving a first imbalance mass concentration rotor and a second imbalance mass concentration rotor at a vibration canceling rotation frequency while controlling the rotational position of the first imbalance mass concentration and the second imbalance mass concentration to produce a rotating net force vector to inhibit periodic vibrations. The program product includes second program instructions to opposingly orient the first imbalance mass concentration relative to the second imbalance mass concentration during a starting stopping rotation speed less than the vibration canceling rotation frequency. The system includes a fault mode control protocol for controlling a rotation of the rotors during a sensed failure of the rotating assembly vibration control system. | 09-02-2010 |
20100221110 | HELICOPTER VIBRATION CONTROL SYSTEM AND ROTATING ASSEMBLY ROTARY FORCES GENERATORS FOR CANCELING VIBRATIONS - A rotary blade rotating hub mounted rotating assembly vibration control system including a first imbalance mass concentration rotor, a second imbalance mass concentration rotor, a third imbalance mass concentration rotor, and a fourth imbalance mass concentration rotor. The first imbalance mass concentration rotor has a first imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The second imbalance mass concentration rotor has a second imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The third imbalance mass concentration rotor has a third imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The fourth imbalance mass concentration rotor has a fourth imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The first and second imbalance mass concentration rotors are driven at a first rotation speed greater than the rotating assembly operational rotation frequency while controlling the rotational position of the first imbalance mass concentration and the second imbalance mass concentration to produce a first rotating net force vector to inhibit a first vibration frequency. The third and fourth imbalance mass concentration rotors are driven at a second rotation speed greater than the rotating assembly operational rotation frequency while controlling the rotational position of the third imbalance mass concentration and the fourth imbalance mass concentration to produce a second rotating net force vector to inhibit a second vibration frequency. | 09-02-2010 |
20110027081 | HELICOPTER HUB MOUNTED VIBRATION CONTROL AND CIRCULAR FORCE GENERATION SYSTEMS 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 driven to rotate about a rotating hub center Z axis by a gear box transmission. 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 about the rotating hub center Z axis relative to the nonrotating body, a first nonrotating body vibration sensor outputting first nonrotating body vibration sensor data correlating to vibrations. The helicopter vibration control system includes at least first and second nonrotating body circular force generators, the nonrotating body circular force generators fixedly coupled with the nonrotating helicopter body proximate the transmission and oriented relative to the rotating hub center Z axis, and a distributed force generation data communications network link, the distributed force generation data communications system network link linking together the nonrotating body circular force generators and the rotating hub mounted vibration control system wherein the rotating hub mounted vibration control system and the nonrotating body circular force generators are controlled to produce rotating forces wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced. | 02-03-2011 |
20110035105 | LAND VEHICLES AND SYSTEMS WITH CONTROLLABLE SUSPENSION SYSTEMS - The land vehicle includes a body, a power plant and a plurality of land engagers, the land engagers for engaging land and propelling the land vehicle across land. The land vehicle includes a controllable suspension system, the controllable suspension system for controlling suspension movements between the body and the land engagers. The land vehicle includes a computer system and suspension sensors located proximate the land engagers for measuring suspension parameters representative of suspension movements between the body and the land engagers and outputting a plurality of suspension sensor measurement output signals. The land vehicle includes controllable force suspension members located proximate the land engagers and the suspension sensors, the controllable force suspension members applying suspension travel forces between the body and the land engagers to control the suspension movements. The land vehicle computer system includes controllable suspension system algorithms for controlling the controllable force suspension members to control vehicle body motion and the suspension movements between the body and the land engagers and inhibit the driver from crossing into an identified impending driver vehicle safety margin. | 02-10-2011 |
20110056780 | CONTROLLABLE VEHICLE SUSPENSION SYSTEM WITH A CONTROLLABLE MAGNETORHEOLOGICAL FLUID STRUT - The controllable suspension system includes a strut with a magnetorheological fluid damper. The magnetorheological fluid damper includes a longitudinal damper tubular housing having a longitudinally extending axis and an inner wall for containing magnetorheological fluid. The damper includes a piston head movable within the damper tubular housing along a longitudinal length the housing, with the damper piston head providing a first upper variable volume magnetorheological fluid chamber and a second lower variable volume magnetorheological fluid chamber, with a fluid flow gap between the upper and lower fluid chambers, the damper piston having a longitudinal piston rod for supporting the piston head within the housing, with the piston supported within the housing with a piston rod bearing assembly disposed between the housing and the rod, with the piston rod bearing assembly having a piston rod bearing seal interface. | 03-10-2011 |
20110204882 | AIRCRAFT VEHICULAR PROPULSION SYSTEM MONITORING DEVICE AND METHOD - Methods/systems for monitoring an aircraft propulsion system is described. The measurement system/method provides for accurate and precise monitoring of rotating members in an aircraft vehicle propulsion system. The measuring system/method provides for a high reliability aircraft in which the propulsion dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the aircraft system. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame. The measuring system provides a misalignment measurement of the propulsion system drive shaft flexible coupling which relates to a critical performance of rotating shaft coupling in the operation of an aircraft vehicle. The method/system provides for monitoring a rotating drive shaft system and dynamically measuring a rotating drive shaft coupling in an aircraft. | 08-25-2011 |
20110259994 | HELICOPTER VIBRATION CONTROL SYSTEM AND ROTATING ASSEMBLY ROTARY FORCES GENERATORS FOR CANCELING VIBRATIONS - A rotary blade rotating hub mounted rotating assembly vibration control system ( | 10-27-2011 |
20120035808 | LAND VEHICLES AND SYSTEMS WITH CONTROLLABLE SUSPENSION SYSTEMS - The land vehicle includes a body, a power plant and a plurality of land engagers, the land engagers for engaging land and propelling the land vehicle across land. The land vehicle includes a controllable suspension system, the controllable suspension system for controlling suspension movements between the body and the land engagers. The land vehicle includes a computer system and suspension sensors located proximate the land engagers for measuring suspension parameters representative of suspension movements between the body and the land engagers and outputting a plurality of suspension sensor measurement outputs. The land vehicle includes controllable force suspension members located proximate the land engagers and the suspension sensors, the controllable force suspension members applying suspension travel forces between the body and the land engagers to control the suspension movements. The land vehicle computer system includes a controllable suspension system algorithm for controlling the controllable force suspension members to control vehicle body motion and the suspension movements between the body and the land engagers, and a health usage monitoring algorithm for monitoring sensors and assessing a health and a usage of the vehicle and its suspension components. | 02-09-2012 |
20120136533 | HELICOPTER VIBRATION CONTROL SYSTEM AND CIRCULAR FORCE GENERATION SYSTEMS FOR CANCELING VIBRATIONS - A rotary wing aircraft including a vehicle vibration control system. 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, 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 hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced. | 05-31-2012 |
20120141276 | FREQUENCY-DEPENDENT DAMPER AND ROTARY WING SYSTEM - A frequency-dependent damper for creating a damping force in response to a variable-frequency disturbance includes an outer damper body having an internal cavity, an inner damper body for receiving the variable-frequency disturbance extending into the internal cavity, a first fluid chamber and a second fluid chamber defined inside the internal cavity, a piston separating the first and second fluid chambers, a selected orifice for transferring fluid between the first and second fluid chambers, and a selected spring element arranged serially between the piston and the inner damper body such that the piston can move relative to the inner damper body through deformation of the spring element. | 06-07-2012 |
20120158217 | DISTRIBUTED ACTIVE VIBRATION CONTROL SYSTEMS AND ROTARY WING AIRCRAFT WITH SUPPRESSED VIBRATIONS - A method and system is disclosed for controlling problematic vibrations in an aircraft having. The method and system have the ability to cancel problematic rotary wing helicopter vibrations using independent active force generator power and with distributed communications therebetween. | 06-21-2012 |
20120256055 | AIRCRAFT ROTARY WING MOTION CONTROL AND INSTRUMENTED MOTION CONTROL FLUID DEVICE - An aircraft rotary wing motion control fluid device providing motion control and with wireless sensing of at least one fluid property inside the fluid device is provided. The wireless sensing system is integrated with at least one of the first and second aircraft rotary wing motion control fluid device bodies. The wireless sensing system includes at least one fluid property sensor in sensing proximity to the at least one fluid chamber and a communications device for wirelessly conveying a measurement made by the at least one fluid property sensor to a remote location. | 10-11-2012 |
20120257847 | ROTARY WING AIRCRAFT INSTRUMENTED MOTION CONTROL BEARINGS - Motion control bearings and methods making such with the capability to monitor properties therein is provided. Devices and methods for creating and using motion control bearings for rotary wing aircraft in particular are disclosed using wireless communication and monitoring of multiple load, motion and health related information items related to the bearing and blade at the wing hub. Static and dynamic blade orientation provides additional information on flight regime, thrust vectors, and gross vehicle weight. Power is provided using kinetic energy power harvesting. | 10-11-2012 |
20150034433 | MAGNETO-RHEOLOGICAL FLUID DAMPER HAVING ENHANCED ON-STATE YIELD STRENGTH - A magneto-rheological fluid valve includes a magnetic field generator having at least one electromagnetic coil and at least one magnetic pole having a pole length L | 02-05-2015 |