Melanie Lynn Fox

7732998, Jun 8, 2010

Aug 3, 2006

11/462114

Sidney G. Allison - Williamsburg VA, US
Qamar A. Shams - Yorktown VA, US
Robert L. Fox - Hayes VA, US
Melanie L. Fox Chattin, legal representative - Hayes VA, US

The United States of America as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

H01L 41/04
H01L 41/08

310369, 310365

A telescoping actuator assembly includes a plurality of cylindrical actuators in a concentric arrangement. Each cylindrical actuator is at least one piezoelectric fiber composite actuator having a plurality of piezoelectric fibers extending parallel to one another and to the concentric arrangement's longitudinal axis. Each cylindrical actuator is coupled to concentrically-adjacent ones of the cylindrical actuators such that the plurality of cylindrical actuators can experience telescopic movement. An electrical energy source coupled to the cylindrical actuators applies actuation energy thereto to generate the telescopic movement.

20050007239, Jan 13, 2005

Apr 30, 2004

10/839445

Stanley Woodard - Hampton VA, US
Bryant Taylor - Smithfield VA, US
Qamar Shams - Yorktown VA, US
Robert Fox - Hayes VA, US
Melanie Fox - Hayes VA, US
Robert Bryant - Lightfoot VA, US

G01N029/02
H04Q005/22

340010200, 340010410

Magnetic field response sensors designed as passive inductor-capacitor circuits produce magnetic field responses whose harmonic frequencies correspond to states of physical properties for which the sensors measure. Power to the sensing element is acquired using Faraday induction. A radio frequency antenna produces the time varying magnetic field used for powering the sensor, as well as receiving the magnetic field response of the sensor. An interrogation architecture for discerning changes in sensor's response frequency, resistance and amplitude is integral to the method thus enabling a variety of measurements. Multiple sensors can be interrogated using this method, thus eliminating the need to have a data acquisition channel dedicated to each sensor. The method does not require the sensors to be in proximity to any form of acquisition hardware. A vast array of sensors can be used as interchangeable parts in an overall sensing system.

20060049833, Mar 9, 2006

Sep 8, 2004

10/943655

Robert Moses - Seaford VA, US
Robert Fox - Hayes VA, US
Richard Chattin - Newport News VA, US
Qamar Shams - Yorktown VA, US
Christopher Fox - Yorktown VA, US
Melanie Fox - Hayes VA, US

U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

G01N 27/00

324633000, 324071100

A system and method are provided for monitoring performance capacity of a piezoelectric material that may form part of an actuator or sensor device. A switch is used to selectively electrically couple an inductor to the piezoelectric material to form an inductor-capacitor circuit. Resonance is induced in the inductor-capacitor circuit when the switch is operated to create the circuit. The resonance of the inductor-capacitor circuit is monitored with the frequency of the resonance being indicative of performance capacity of the device's piezoelectric material.

20070069083, Mar 29, 2007

Jun 8, 2006

11/422984

Qamar Shams - Yorktown VA, US
Michael Logan - Chesapeake VA, US
Robert Fox - Hayes VA, US
Melanie Fox - Hayes VA, US
John Ingham - Alexandria VA, US
Sean Laughter - Chester VA, US
Theodore Kuhn - Fredericksburg VA, US
James Adams - Gloucester VA, US
Walter Babel - Smithfield VA, US

G05D 1/00

244195000

A self-contained avionics sensing and flight control system is provided for an unmanned aerial vehicle (UAV). The system includes sensors for sensing flight control parameters and surveillance parameters, and a Global Positioning System (GPS) receiver. Flight control parameters and location signals are processed to generate flight control signals. A Field Programmable Gate Array (FPGA) is configured to provide a look-up table storing sets of values with each set being associated with a servo mechanism mounted on the UAV and with each value in each set indicating a unique duty cycle for the servo mechanism associated therewith. Each value in each set is further indexed to a bit position indicative of a unique percentage of a maximum duty cycle for the servo mechanism associated therewith. The FPGA is further configured to provide a plurality of pulse width modulation (PWM) generators coupled to the look-up table. Each PWM generator is associated with and adapted to be coupled to one of the servo mechanisms.

7580323, Aug 25, 2009

May 23, 2006

11/419818

Sidney G. Allison - Williamsburg VA, US
Qamar A. Shams - Yorktown VA, US
Robert L. Fox - Hayes VA, US
Melanie L. Fox Chattin, legal representative - Hayes VA, US

The United States of America as represented by the Administrator of the National Aeronautics and Space Adninistration - Washington DC

G02B 6/00

367140, 25022714

An optical assembly is formed by one or more piezoelectric fiber composite actuators having one or more optical fibers coupled thereto. The optical fiber(s) experiences strain when actuation voltage is applied to the actuator(s). Light passing through the optical fiber(s) is wavelength tuned by adjusting the actuation voltage.