Abstract: A method of fabricating a capacitive micromechanical electrical system (MEMS) pressure sensor includes the steps of forming a backing wafer, forming a diaphragm wafer that includes a diaphragm configured to deflect from an applied force and a pressure cavity configured to produce on the diaphragm the applied force which is indicative of a system pressure; fusing the diaphragm wafer to the backing wafer thereby forming a base wafer, forming a top wafer, joining the top wafer to the base wafer, thereby forming a detector wafer. The diaphragm defines a first capacitor surface and the top wafer defines a second capacitor surface. A void separates the second capacitor surface from the first capacitor surface by a separation distance which is a capacitor gap. A capacitive MEMS pressure sensor is also disclosed.

Abstract: A method for forming a heater on a substrate includes feeding a heater wire into a heating zone, the heater wire being in contact with a dielectric material within the heating zone, and coaxially co-extruding the heater wire and the dielectric material from the heating zone through a nozzle and onto a substrate such that the heater wire and the dielectric material form a heater for heating the substrate.

Abstract: An aircraft windshield wiper system includes a wiper arm, a wiper blade coupled to a first end of the wiper arm, and an output shaft coupled to a second end of the wiper arm. The wiper blade includes a fluid dispensing system including nozzles, a fluid control unit, fluid lines, fluid source, and a user interface. The wiper blade with the fluid dispensing system is configured to dispense a variety of fluids directly from the wiper blade onto the windshield of an aircraft.

Abstract: Apparatus and associated methods relate to synchronization of a ground support vehicle with a taxiing aircraft, so as to provide ground support services during taxi operation. After landing, a taxiing aircraft obtains a parking destination from a ground traffic controller. A first navigational route from a first location of the taxiing aircraft to the parking destination is determined. The taxiing aircraft transmits a signal indicative of the first navigational route to the ground support vehicle. A second navigational route of the ground support vehicle is determined so as to intercept the taxiing aircraft. The ground support vehicle navigates according to the determined second navigational route, and couples to the taxiing aircraft at a coupling location common to both the first and the second navigational routes. The ground support vehicle provides ground support service during continued navigation according to a coupled portion of the first navigational route.

Abstract: An aircraft windshield wiper system includes a wiper arm, a wiper blade coupled to a distal end of the wiper arm, and a drive shaft coupled to a proximal end of the wiper arm. The wiper blade is configured to clean water, dirt, and other debris from the windshield of the aircraft. The drive shaft is configured to rotate and cause the wiper arm with the coupled wiper blade to sweep across the windshield. The wiper arm includes both composite and metal components to reduce the weight of the windshield wiper system while also providing lightning strike protection.

Abstract: Apparatus and associated methods relate to ranging object(s) nearby an aircraft using triangulation. A light projector mounted at a projector location on the aircraft projects pulses of polarized light onto the scene external to the aircraft. The projected pulses of polarized light are polarized in a first polarization state. A camera mounted at a camera location on the aircraft has a shutter synchronized to the projector output pulse and receives a portion of the projected pulses of polarized light reflected by the object(s) in the scene and polarized at a second polarization state orthogonal to the first polarization state. Location(s) and/or range(s) of the object(s) is calculated, based on the projector location, the camera location, and pixel location(s) upon which the portion of light is imaged.

Abstract: A sensor assembly for monitoring a heater system for an aircraft probe sensor includes a current sensor module with a current sensor core and a high electromagnetically permeable enclosure around the current sensor core. An input wire pathway extends through the current sensor core and is configured to receive a heater input wire. A return wire pathway extends through the current sensor core and is configured to receive a heater return wire. A high electromagnetically permeable tube extends through the current sensor core and is configured to extend around one of the input wire and the heater return wire.

Abstract: Provided are embodiments for performing encryption and decryption. Embodiments include generating a random key address, obtaining a pre-stored key using the random key address, and re-arranging portions of the pre-stored key using the random key address and a first enable signal. Embodiments also include selecting a dynamic logic operation based on the random key address and a second enable signal, receiving data for encryption, and combining portions of the received data for encryption with the re-arranged portions of the pre-stored key using the dynamic logic operation to produce encrypted data. Embodiments include re-arranging portions of the encrypted data based on the random key address and a third enable signal, and combining the re-arranged portions of the encrypted data with the random key address into an encrypted data packet for transmission. Also provided are embodiments for a transmitter and receiver for performing the encryption and decryption.

Abstract: A thermal management system for a sensor module is disclosed that includes a housing enclosing the sensor module and having a bottom wall with a reception port formed therein, and a thermal isolation puck installed within the reception port formed in the bottom wall of the housing for reducing the rate at which thermal energy from a heater located within an adjacent flush static plate is lost to the housing.

Abstract: An air data sensor can include an acoustic transmitter configured to output an acoustic signal into an airflow and a plurality of acoustic transducers configured to receive the acoustic signal output by the acoustic transducer. The air data sensor can also include a light source configured to output a light beam into the airflow, and a light receiver configured to receive scattered light from the light beam. The light source and the light receiver can be bistatic such that a measurement zone is formed away from the air data sensor.

Abstract: An anti-spin system for an aircraft can include an anti-spin module configured to execute a computer implemented method. The method can include receiving flight data from one or more aircraft flight data systems, determining if the aircraft is near stall or in a stall using the flight data, and determining if the aircraft is in uncoordinated flight while near stall or in a stall to determine if the aircraft is near spin or in a spin using the flight data. If the aircraft is determined to be near spin, the method includes at least one of sending an alert to a warning indicator in a cockpit to warn the pilot of a spin or near spin condition, or sending a signal to an automated control system for inputting automatic control to the aircraft to avoid a spin by coordinating the aircraft or avoiding a stall while uncoordinated.

Abstract: Apparatus and associated methods relate to a system for detecting foreign object debris ingested into an aircraft engine. The system detects such foreign object debris by projecting a beam of light over an inlet of the aircraft engine. When foreign object debris is ingested into the aircraft engine, it intercepts the beam of light and scatters a back-scattered portion of the intercepted beam of light. An optical detector is configured to detect the back-scattered portion of the intercepted beam of light. A processor is configured to determine whether foreign object debris is ingested by the aircraft engine based on a comparison of a threshold value with a signal indicative of the back-scattered portion generated by the optical detector.

Abstract: Apparatus and associated methods relate to determining health of an electrical heater of an air data probe based on a comparison between a calculated expected value and a measured value of an electrical property of the electrical heater. The expected value of the electrical property is calculated based in part on the electrical power provided to the electrical heater and further based in part on the aircraft flight parameters and/or environmental conditions. Such aircraft flight parameters and/or environmental conditions can include at least one of: electric power source status, airspeed, air pressure, altitude, air temperature, humidity, liquid water content, ice water content, droplet/particle size distribution, angle of attack, and angle of sideslip. These aircraft flight parameters and/or environmental conditions are received via an aircraft interface.

Abstract: A aircraft health management system for identifying an anomalous signal from one or more air data systems (ADS) includes one or more of a frequency processor, configured to provide a spectral signal that is representative of a frequency content of the first ADS signal, a noise processor, configured to provide a noise signal that is representative of a noise level of the first ADS signal, and a rate processor, configured to provide a rate signal that is representative of a rate of change of the first ADS signal. The aircraft health management system also includes a comparator configured to provide a differential signal between the first ADS signal and the second ADS signal, and a prognostic processor configured to determine if the ADS signal is anomalous by comparing values representative of a flight condition signal, the differential signal, and the spectral, noise, and/or rate signals.

Abstract: A probe includes a probe head, a probe tip extending from the probe head and having a sensor in fluidic communication with a first fluid stream, a pressure channel extending into the probe tip through the sensor face with a pressure sensor that senses pressure in the pressure channel, and a temperature channel extending into the probe tip through the sensor face. The temperature channel including a temperature orifice disposed on the sensor face and at least one exit port distal from the sensor face. The temperature channel is parallel to and fluidly separate from the pressure channel and includes a temperature sensor that senses temperature in the temperature channel. The temperature channel directs fluid flow from the temperature orifice to the at least one exit port, thereby discharging fluid flow into a second fluid stream.

Abstract: A pitot tube includes an outer tube extending from a first tube end to second tube end, the second tube end defining a tip portion of the pitot tube, the tip portion including an inlet opening. A tube sleeve inside of the outer tube at least partially defines a tube passage extending from the first tube end to the second tube end. The tube sleeve includes a sleeve outer surface having a sleeve body portion having a first outer diameter and a sleeve tip portion located at the tip portion of the pitot tube. The sleeve tip portion has a second outer diameter smaller than the first outer diameter. A heating element is located between the outer tube and the tube sleeve at at least the sleeve tip portion.

Abstract: Provided are embodiments for performing encryption and decryption in accordance with one or more embodiments. The embodiments include generating a random key address, obtaining a pre-stored key using the random key address, and re-arranging portions of the pre-stored key using the random key address. Embodiments also include selecting a dynamic logic operation based on the random key address, receiving data for encryption, and combining portions of the received data for encryption with the re-arranged portions of the pre-stored key using the dynamic logic operation to produce encrypted data. Embodiments include re-arranging portions of the encrypted data based on the random key address and combining the re-arranged portions of the encrypted data with the random key address into an encrypted data packet for transmission. Also provided are embodiments for a transmitter and receiver for performing the encryption and decryption.

Abstract: An acoustic air data system includes first and second acoustic transmitters, an array of acoustic receivers, and control circuitry. The array is positioned to receive first and second acoustic signals. The control circuitry determines time difference of arrival (TDOA) of the first and second acoustic signals. The control circuitry determines, for each of a first and second set of acoustic receiver pairs, a signal velocity of the first and second acoustic signals, respectively, based on a distance between an inner acoustic receiver and an outer acoustic receiver and a corresponding TDOA for each pair of acoustic receivers. The control circuitry estimates one or more of wind angle, speed of sound, Mach number, and true airspeed of the airflow about the exterior of the vehicle based on parameters of a best fit circle.