Abstract: A linear lighting device may include an elongated housing that defines a cavity. The linear lighting device may include plurality of emitter printed circuit boards configured to be received within the cavity. Each of the plurality of emitter printed circuit boards may include a plurality of emitter modules mounted thereto. Each of the plurality of emitter printed circuit boards may include a control circuit configured to control the plurality of emitter modules mounted to the respective emitter printed circuit board based on receipt of one or more messages. The linear lighting device may include a total internal reflection lens for each of the plurality of emitter printed circuit boards. The total internal reflection lens may be configured to diffuse light emitted by the emitter modules of the plurality of emitter printed circuit boards.

Abstract: A linear lighting device may include an elongated housing that defines a cavity. The linear lighting device may include plurality of emitter printed circuit boards configured to be received within the cavity. Each of the plurality of emitter printed circuit boards may include a plurality of emitter modules mounted thereto. Each of the plurality of emitter printed circuit boards may include a control circuit configured to control the plurality of emitter modules mounted to the respective emitter printed circuit board based on receipt of one or more messages. The linear lighting device may include a total internal reflection lens for each of the plurality of emitter printed circuit boards. The total internal reflection lens may be configured to diffuse light emitted by the emitter modules of the plurality of emitter printed circuit boards.

Abstract: 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.

Abstract: 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.

Abstract: Actuator assemblies are formed by at least one cylinder where each cylinder is formed by at least one piezoelectric fiber composite actuator adapted to have actuation energy applied thereto.

Abstract: 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.

Abstract: 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.

Abstract: 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.