| 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 |
| 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 |
| 20100090054 | METHOD AND SYSTEM FOR CONTROLLING HELICOPTER VIBRATIONS - A method/system for controlling helicopter vibrations is provided that includes a vibration canceling force generator for actively generating a vibration canceling force. The system includes a resonant actuator having a natural resonant frequency and a resonant actuator electronic control system. The resonant actuator electronic control system provides an electrical drive current to the resonant actuator to drive the resonant actuator about the resonant frequency when commanded by a received command signal. The resonant actuator has a feedback output with the feedback output fed back into the resonant actuator electronic control system wherein the resonant actuator electronic control system adjusts the electrical drive current based on the resonant actuator feedback output to generate the vibration canceling force. | 04-15-2010 |
| 20110033310 | ELECTROMAGNETIC INERTIAL ACTUATOR - An electromagnetic inertial actuator includes a support base and a parallel arrangement of a first flexure part, a voice coil motor part, and a second flexure part. The parallel arrangement is cantilevered from the support base. | 02-10-2011 |
| 20110197703 | Aircraft propeller balancing system - An aircraft system/method for propeller balancing. The system includes an inboard driver with a first and second inboard electromagnetic coil, the inboard driver and the first counterweight balancing rotor and the second counterweight balancing rotor centered around the aircraft propeller shaft rotating machine member with the first inboard electromagnetic coil proximate the first inboard magnets of the first counterweight balancing rotor, with the inboard electromagnetic coil driver proximate the rotation axis of the aircraft propeller shaft rotating machine member and the first counterweight balancing rotor outboard of the inboard electromagnetic coil driver with the first inboard electromagnetic coil generating a electromagnetic field to electromagnetically step the first inboard magnets of the at least first counterweight balancing rotor to electromagnetically actuate rotational movement of the first counterweight balancing rotor around the rotating machine member and relative to the inboard electromagnetic coil driver to a first rotor held balancing position. | 08-18-2011 |
| 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 |
| 20110209958 | RESONANT INERTIAL FORCE GENERATOR HAVING STABLE NATURAL FREQUENCY - A resonant inertial force generator for controlling vibrations of a structure includes a compliant spring comprising a stack of flexures and elastomeric shims in alternating arrangement, a driven inertial mass coupled to the compliant spring to generate a vibration controlling force. | 09-01-2011 |
