Abstract: A flow control valve includes an electrically controlled piezoelectric actuator, at least one pressure fitting and nozzle, and a nozzle orifice sealing mechanism coupled to the piezoelectric actuator. The piezoelectric actuator may be a piezo-ceramic actuator fixed along one side to a chamber of the flow control valve and having a free side opposite the fixed side. Upon receiving a voltage of a desired magnitude and polarity, the free side of the piezo-ceramic actuator and the nozzle orifice sealing mechanism moves to control a fluid flow into the chamber. By controllably dithering the piezoelectric actuator of the flow control valve, an output flow from the chamber may be accurately regulated.

Abstract: An integrated sensor implementation employs a data acquisition method for producing digital output signals that enables computing low latency, low noise, rate of pressure (or altitude etc.) change measurements. An example sensor includes a self-digitizing pressure and temperature sensor circuit that outputs a serial digital signal that varies with at least one physical parameter to which the sensor circuit is exposed. The sensor incorporates an internal sigma-delta A/D converter and digital data acquisition device that effectively time-stamps all acquired data. This time stamped data is then transmitted to an external processing resource (microprocessor) that is used to convert the self-digitized, time stamped data into low latency, low-noise proportional and rate parameter outputs having the desired engineering units for at least one physical parameter sensed. This low-latency, low noise rate of change signal may be derived without the latency penalty of digital filtering.

Abstract: An integrated sensor implementation employs a data acquisition method for producing digital output signals that enables computing low latency, low noise, rate of pressure (or altitude etc.) change measurements. An example sensor includes a self-digitizing pressure and temperature sensor circuit that outputs a serial digital signal that varies with at least one physical parameter to which the sensor circuit is exposed. The sensor incorporates an internal sigma-delta A/D converter and digital data acquisition device that effectively time-stamps all acquired data. This time stamped data is then transmitted to an external processing resource (microprocessor) that is used to convert the self-digitized, time stamped data into low latency, low-noise proportional and rate parameter outputs having the desired engineering units for at least one physical parameter sensed. This low-latency, low noise rate of change signal may be derived without the latency penalty of digital filtering.

Abstract: An integrated multi-mode sensor system is described that integrates into a single housing a sensor, signal conditioning circuitry, calibration memory, and interface circuitry that is compatible with both analog and digital end-use circuits. The sensor includes a housing, a sensor circuit, memory, and an interface circuit. The sensor circuit is disposed within the sensor housing, is operable, upon being energized, to supply an output signal that varies with at least one physical parameter to which the sensor circuit is exposed. The interface circuitry disposed within the sensor housing is adapted to receive a mode select signal and the sensor signal. The output circuit is selectively configurable, in response to the mode select signal, to implement one of a plurality of signal processing modes, including analog voltage output, asynchronous pulse density modulation (APDM) and synchronous pulse density modulation (SPDM) of various moduli, and an APDM or SPDM mode using a selectable I2C or SPI interface protocol.

Abstract: A pressure sensor includes a sensor die coupled to a glass support tube and located within a metallic intermediate sleeve. The glass support tube is bonded or otherwise attached to the metallic intermediate sleeve with solder or other adhesive material. End portions of the glass support tube and the metallic intermediate sleeve are configured to have complementary, contoured surfaces such that at least a portion of an attachment layer located there between is placed in compression during operation of the pressure sensor.

Abstract: An integrated multi-mode sensor system is described that integrates into a single housing a sensor, signal conditioning circuitry, calibration memory, and interface circuitry that is compatible with both analog and digital end-use circuits. The sensor includes a housing, a sensor circuit, memory, and an interface circuit. The sensor circuit is disposed within the sensor housing, is operable, upon being energized, to supply an output signal that varies with at least one physical parameter to which the sensor circuit is exposed. The interface circuitry disposed within the sensor housing is adapted to receive a mode select signal and the sensor signal. The output circuit is selectively configurable, in response to the mode select signal, to implement one of a plurality of signal processing modes, including analog voltage output, asynchronous pulse density modulation (APDM) and synchronous pulse density modulation (SPDM) of various moduli, and an APDM or SPDM mode using a selectable I2C or SPI interface protocol.

Abstract: An air data module is provided that is relatively small, lightweight, low cost, uses relatively low power, and is relatively easy to install, test, and maintain. The air data module includes a housing that is adapted to be mounted to an external surface of an aircraft, and includes at least a sensor compartment and an interface electronics compartment formed therein. A pitot-static probe is coupled to the housing and extends therefrom, and has a static pressure passageway that is in fluid communication with the sensor compartment. A plurality of static pressure ports are formed in the pitot-static probe and are in fluid communication with the static pressure passageway. A pitot pressure inlet port is formed in a distal end of the pitot-static probe. A static pressure sensor and a differential impact or absolute pitot pressure sensor, for example, may be mounted within the module and used to sense static pressure and impact or pitot pressure, respectively.

Abstract: An air data module is provided that is relatively small, lightweight, low cost, uses relatively low power, and is relatively easy to install, test, and maintain. The air data module includes a housing that is adapted to be mounted to an external surface of an aircraft, and includes at least a sensor compartment and an interface electronics compartment formed therein. A pitot-static probe is coupled to the housing and extends therefrom, and has a static pressure passageway that is in fluid communication with the sensor compartment. A plurality of static pressure ports are formed in the pitot-static probe and are in fluid communication with the static pressure passageway. A pitot pressure inlet port is formed in a distal end of the pitot-static probe. A static pressure sensor and a differential impact or absolute pitot pressure sensor, for example, may be mounted within the module and used to sense static pressure and impact or pitot pressure, respectively.

Abstract: According to one aspect of the present invention, this invention implements a low latency, wide bandwidth method and system for converting a numeric digital values into a pulse density modulated analog output signals. Such output signals having their lowest output frequency much closer to the system clock frequency, thus enabling wider bandwidth and simpler implementations than with traditional approaches. This method is based in part on an adaptation of Bresenham's Line Drawing Algorithm.

Abstract: A differential pressure-induced airflow based approach is used to measure Angle-Of-Attack (AOA) or Angle-Of-Sideslip (AOS) for an aircraft. Ports on opposing sides of an aircraft fuselage are coupled by an airway incorporating a mass airflow sensor. As the relative wind's angle of incidence changes direction with respect to the aircraft's longitudinal axis or wing chord, a differential pressure is created. The differential pressure induces an airflow between the ports whose magnitude is measured by a mass airflow sensor. The resulting airflow is a function of the respective AOA or AOS. The measured airflow and air data computer supplied parameters of airspeed (or dynamic pressure) and altitude (or static pressure) are utilized by an algorithm that reduces the data into angular AOA or AOS measurements.

Abstract: An air data sensor for an aircraft has a flush mounted plate at the outside surface of the aircraft and a housing for the sensor within the aircraft below the plate. A plurality of holes in the plate provide air flow to a pressure sensor in the housing. To prevent water from reaching the sensor, a trap chamber is provided below the holes. Various contorted air flow paths are disclosed. The tube to the pressure sensor may be heated.

Abstract: An air data sensor for an aircraft has a flush mounted plate at the outside surface of the aircraft and a housing for the sensor within the aircraft below the plate. A plurality of holes in the plate provide air flow to a pressure sensor in the housing. To prevent water from reaching the sensor, a trap chamber is provided below the holes. Various contorted air flow paths are disclosed. The tube to the pressure sensor may be heated.