Abstract: A probe system includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe. An operational voltage is provided to the resistive heating element to provide heating for the probe. The control circuit is configured to provide a test voltage different than the operational voltage and monitor a test current generated in the resistive heating element while providing the test voltage. The control circuit is further configured to detect micro fractures in the resistive heating element based on the test current.

Abstract: Embodiments include techniques for an automated aircraft landing analysis, the techniques includes requesting landing information corresponding to a current landing, wherein the landing information includes historic average landing information, and receiving the landing information. Techniques also include retrieving recorded aircraft system parameters corresponding to the current landing, and calculating a landing distance for the current landing. Techniques include calculating a deviation of the calculated landing distance for the current landing, and displaying results of the calculated deviation.

Abstract: A damper assembly for an angle of attack sensor includes a rotor including a conical portion, a damper housing in which the rotor is positioned, the damper housing being configured to be adjusted axially with respect to the rotor and including a tapered interior surface that matches a profile of the conical portion, and a locking mechanism adjacent the damper housing.

Abstract: An air data system for an aircraft includes a multi-function probe (MFP) and an inertial reference unit (IRU). The MFP is positioned to sense a pressure of airflow about an exterior of the aircraft. A first electronics channel of the MFP is electrically coupled to the IRU to generate air data parameter outputs based on the pressure sensed by the MFP and inertial data sensed by the IRU.

Abstract: Apparatus and associated methods relate to determining airspeed and/or altitude based on acoustic waves caused by airflow. One of more acoustic transducers are positioned along an exterior surface of an aircraft. Each of the one or more acoustic transducers is configured to detect acoustic waves caused by the airflow. The acoustic waves detected are indicative of an airstream condition proximate the acoustic transducer, such as, for example, airspeed and/or altitude. A processor is configured to determine airspeed and/or altitude of the aircraft based, at least in part, on the acoustic waves detected.

Abstract: A pressure sensor includes a MEMS pressure transducer with a pressure sensing diaphragm and sensor elements, an isolator diaphragm spaced apart from the pressure sensing diaphragm, and a ceramic header body. The ceramic header body has an electrical conductor and transducer aperture with the MEMS pressure transducer supported therein. The isolator diaphragm is coupled to the to the MEMS pressure transducer by a fluid and is sealably fixed to the ceramic body. The ceramic header body bounds the fluid and the electrical conductor electrically connects the MEMS pressure transducer with the external environment. Differential pressure sensors and methods of making pressure sensors are also described.

Abstract: A system includes a lens mount defining an inner bore that includes inward facing threads for engaging a lens component, with a lens opening at one end of the lens mount. The lens mount includes outward facing threads for engaging a camera housing. A first seal ring is included inside the inner bore for sealing against the lens component. A second seal ring is included on an outside of the lens mount for sealing against the camera housing.

Abstract: A probe head of a pitot probe includes a mandrel having a helical groove, a heater within the helical groove of the mandrel such that an exterior surface of the heater is flush with an exterior surface of the mandrel, and an outer shell having an interior surface in air-tight contact with the mandrel and the heater.

Abstract: Apparatus and associated methods relate to creating corrected images of a scene for a terminal-imaging seeker using an electrically-controllable coded-aperture mask pattern embodied in a programmable spatial light modulator. The coded-aperture mask pattern includes a plurality of pinhole-like apertures, each of which is configured to perform pinhole-like lensing of the scene. The plurality of pinhole-like apertures form a multiplex of overlapping images on a focal plane array aligned with the optical axis. An image processor reconstructs, based on a configuration of the plurality of pinhole-like apertures and the multiplex of overlapping images, a single image of the scene.

Abstract: Provided are embodiments for a resistor array. The resistor array includes a plurality of resistor elements, where the plurality of resistor elements includes a redundancy region for a most significant bit of an expected value. The resistor array also includes one or more switches coupled to the plurality of resistor elements, and a first terminal and a second terminal coupled to the plurality of resistor elements. Also provided are embodiments for trimming the resistor array where the resistor array includes a redundancy region for a most significant bit for an expected value.

Abstract: A fluid reservoir for a vehicle includes a reservoir body with a sensing chamber portion, a neck portion, and a reserve chamber portion. The neck portion is connected to the sensing chamber portion and the reserve chamber portion is connected to the sensing chamber portion by the neck portion. The neck portion defines a neck portion volume that is smaller a volume defined by the sensing chamber to limit slosh in the sensing chamber when a reserve volume of fluid is present within the fluid reservoir. Windscreen washing systems and aircraft having fluid reservoirs are also described.

Abstract: A system for an aircraft includes an aircraft component that includes a heater routed through the aircraft component, the heater including a resistive heating element and insulation surrounding the resistive heating element. A first current flows into the resistive heating element to provide heating for the aircraft component and a second current flows out of the resistive heating element. The system further includes a first sensor configured to produce a first sensor signal representing the first current, a second sensor configured to produce a second sensor signal representing the second current, a leakage sensor configured to produce a leakage sensor signal representing a leakage current, and a signal processor configured to sample and measure the first current, the second current, and a leakage current using a high frequency sampling rate to identify the presence of electric arcing. The detection of electric arcing is used to predict future heater failure and estimate heater remaining useful life.

Abstract: An air data computer senses acceleration and rotational rate of an aircraft with an inertial sensor assembly of the air data computer. The air data computer determines first attitude information of the aircraft based on the acceleration and rotational rate sensed with the inertial sensor assembly. The air data computer receives second attitude information of the aircraft from a source external to the air data computer, and determines attitude correction values based on the first attitude information and the second attitude information. The air data computer applies the attitude correction values to the first attitude information to produce error-corrected attitude information that is output from the air data computer.

Abstract: An air data probe includes a probe body including a probe wall. The probe body is formed from a first material by direct energy metal deposition. An insert is positioned in the probe wall. The insert is formed from a second material different from the first material. The insert is encapsulated in the probe wall via the direct energy metal deposition.

Abstract: An acoustic sensor system for an aircraft includes a transmitter configured to emit acoustic signals external to the aircraft, and at least one microphone positioned on an exterior of the aircraft and configured to sense the acoustic signals as sensed data. The acoustic sensor system is configured to direct the acoustic signals to the at least one microphone such that a sound pressure level is attenuated perpendicular to the aircraft.

Abstract: A method of characterizing an aerosol, the method comprising illuminating aerosol particles located within a measurement volume with a first electromagnetic radiation pulse emitted from a first source and receiving one or more electromagnetic radiation returns that have been scattered by the aerosol particles illuminated by the first electromagnetic radiation pulse at one or more sensors, illuminating the aerosol particles within the measurement volume with a second electromagnetic radiation pulse emitted from a second source and receiving a one or more electromagnetic radiation returns scattered by the aerosol particles illuminated by the second electromagnetic radiation pulse at the one or more sensors, determine at least one of intensity based on the one or more electromagnetic radiation returns, and determine an aerosol parameter based on an algorithm and the at least one intensity.

Abstract: Embodiments include a system for prognosis of a wireless aircraft network including a network manager including a network prognostic manager, one or more data controllers operably coupled to the network manager over a first connection, and one or more wireless nodes operably coupled to the one or more data controllers over a second connection, wherein the second connection is a different type of connection than the first connection, wherein the network manager includes a network prognostic manager, wherein the network prognostic manager. The network manager performs a method of receiving measured parameters from a wireless communications network, computing thresholds associated with the parameters, comparing the received parameters to the computed thresholds, identifying a failure condition based on the comparison of the received parameters to the computed thresholds, and based at least in part on the identified failure condition, executing a corrective action.

Abstract: An acoustic sensor system for an aircraft, and method for operating the same, includes a transmitter, at least one microphone, and a control circuit. The transmitter is configured to emit acoustic signals external to the aircraft. The at least one microphone is positioned on an exterior of the aircraft and configured to sense the acoustic signals as sensed data. The control circuit is configured to receive the sensed data and control the transmitter through a drive circuit, and is configured to detect an environmental condition and control the transmitter to emit the acoustic signals at a reduced intensity based on the detected environmental condition.

Abstract: A thermocouple assembly for use in a high-temperature gas path that includes a thermocouple. The thermocouple includes a first conductor and a second conductor, the first and second conductors formed of different materials and coupled to one another by junction, a metal sheath surrounding the first and second conductors wherein the metal sheath is substantially coaxial with the both the first conductor and the second conductor. The assembly also includes: a first termination electrically coupled to the first conductor; a second termination electrically coupled to the second conductor; a first connector configured to couple to the first termination; a second connector configured to couple to the second termination; and a housing configured to cover the first and second terminations and the first and second connectors.

Abstract: A method of testing sensors includes providing a test sheet that includes a plurality of sensor assemblies, a plurality of test pads, and traces extending from the sensor assemblies to the plurality of test pads. A sensor is positioned on each sensor assembly. Each sensor is connected to the sensor assembly with wire bonds. An enclosure is formed over the plurality of sensor assemblies. An electrical signal is detected from each of the plurality of sensor assemblies at the test pads.