Abstract: An angle of attack sensor includes a housing having an open end and a closed end, a faceplate positioned on the open end of the housing, the faceplate having an opening, a vane assembly extending through the opening of the faceplate, a vane shaft connected to the vane assembly and extending within the housing, the vane shaft having a bore extending through the vane shaft, a bearing surrounding the vane shaft, a vane shaft seal surrounding the vane shaft adjacent the bearing, and a first vent hole extending from an interior surface of the vane shaft to an exterior surface of the vane shaft between the bearing and a first end of the vane shaft seal, the first vent hole being in fluid communication with the bore of the vane shaft.

Abstract: A method and system of synchronizing a local clock with a master clock using a serial communication bus includes receiving by a serial data interface receiver a master time signal corresponding to a master clock, generating by a frequency tuning loop a time error signal corresponding to a difference between the master time signal and a local time signal, generating by the frequency tuning loop an actual frequency signal based on a base frequency and the time error signal, producing by the frequency tuning loop a command frequency error based on the actual frequency signal and the local time signal, and producing by the local clock an updated local time signal based on the command frequency error.

Abstract: A method for an automated aircraft landing analysis including: receiving one or more aircraft landing performance parameters for one or more landing phases; determining a landing performance deviation for each of the one or more landing phases in response to the one or more aircraft landing performance parameters; identifying at least one of a system fault, a failure, and a pilot error that could have led to the landing performance deviations for each of the one or more landing phases; developing a fault tree for the landing performance deviations for each of the one or more landing phases; identifying measurable parameters, calculable parameters, inferable parameters, or observable parameters within the fault tree; converting the fault tree into a high level reasoning model using a standard inference methodology; performing a root cause analysis; identifying a root cause of the landing performance deviation; and displaying the root cause of landing performance deviation.

Abstract: A transceiver baseband hardware is provided. The transceiver baseband hardware includes a baseband hardware. The baseband hardware includes an encryption-decryption block. The encryption-decryption block encrypts intended transmission data and decrypts encrypted data with key coefficients via a cross logical operation of the encryption-decryption block. The cross logical operation includes when lower significant bytes of the key coefficients operating on most significant bytes of the intended transmission data and the encrypted data.

Abstract: An ultrasonic air data system (UADS) can include a body configured to mount to an aircraft, an acoustic signal shaping feature associated with the body, and an acoustic source operatively connected to the acoustic signal shaping feature, the acoustic source configured to emit a directional acoustic signal. The acoustic signal shaping feature can be configured to reshape the directional acoustic signal from the acoustic source into an at least partially reshaped signal. The system can include one or more acoustic receivers disposed on or at least partially within the body for receiving the reshaped signal.

Abstract: Disclosed is a method that includes receiving absolute wireless access point coordinates from wireless access points that define respective wireless access point positions of the wireless access points. The method includes orienting the directional antenna to orientations based on the absolute wireless access point coordinates. The method includes transmitting test signals to the respective wireless access points while the directional antenna is positioned at the orientations to generate the database entries associated with the respective wireless access point positions. The method includes orienting the directional antenna according to a first one of the database entries having a greatest likelihood to establish a first communications path between a first one of the wireless access points and the wireless endpoint. The method includes transmitting a data signal to the first one of the wireless access points with a minimum transmission power based on the database entries.

Abstract: A wall for a heated faceplate includes a base and tines protruding from the base and spaced from each another. The tines are configured to accumulate ice in a manner which promotes shedding of small ice formations to prevent large accumulations of ice father aft on the faceplate.

Abstract: A cover for a probe head of an air data probe includes a sleeve defining a cavity for enclosing a portion of the probe head of the air data probe, the sleeve including a closed end, an open end opposite the closed end, and an interior surface extending from the open end to the closed end, and a reservoir for holding insect repellent, the reservoir located at least partially within the cavity of the sleeve.

Abstract: A Wireless Avionics Intra-Communication (WAIC) system includes a communication network and a WAIC adapter location system. The communication network is configured to exchange data with a portable wireless device via WAIC adapter. The WAIC adapter location system is configured to determine a location of the WAIC adapter, which selectively connects and disconnects the portable device from the communication network based on the location.

Abstract: Apparatus and associated methods relate to sampling a large volume of a cloud atmosphere so as to obtain a large signal response from even a sparse distribution of water droplets in the cloud atmosphere. Such a volume can be probed by projecting an uncollimated optical beam into the cloud atmosphere and sampling the signal backscattered from the water droplets located within the probed volume. The uncollimated optical beam can be generated by projecting a diverging pulse of light energy from a polished end of a first optical fiber. A second optical fiber can be used to receive the optical signal backscattered from the cloud atmosphere. The second optical fiber can also have substantially the same field of view as the first optical fiber, so as to receive signals from a volume of the cloud atmosphere that is substantially commensurate with the probed volume.

Abstract: A method includes forming an image of a scene on a sensor through a coded aperture, wherein the coded aperture and sensor are optically coupled within an imaging platform to form a superpositioned, physically encoded image of the scene on the sensor. The method includes generating raw image data from the sensor representative of the superpositioned, physically encoded image of the scene, and transmitting the raw image data to a platform remote from the imaging platform so the raw data is encrypted during transmission. The method can include using the platform remote from the imaging platform to deconvolve the superpositioned, physically encoded image into a decoded image.

Abstract: Disclosed is a process of manufacturing a pitot tube assembly including: obtaining a metal cylindrical tube having a first axial portion that is a first material blank for an assembly inlet portion of the pitot tube assembly and a second axial portion that is a second material blank for a body portion of the pitot tube assembly; nesting the first axial portion of the tube within a cylindrical graphite insert; nesting the cylindrical graphite insert within a cylindrical sheath; constraining axial motion of the insert; performing laser scanning to the assembly inlet portion; and performing additive manufacturing to the pitot tube assembly inlet portion.

Abstract: An acoustic air data sensor for an aircraft includes an acoustic transmitter, an acoustic receiver, an acoustic signal generator, timing circuitry, speed of sound determination circuity, and communication circuitry. The acoustic transmitter is located to transmit an acoustic signal through an airflow stagnation chamber that is pneumatically connected to an exterior of the aircraft and configured to receive and stagnate airflow from the exterior of the aircraft. The acoustic receiver is positioned at a distance from the acoustic transmitter to receive the acoustic signal. The pulse generator causes the acoustic transmitter to provide the acoustic signal. The timing circuitry determines a time of flight of the acoustic signal from the acoustic transmitter to the acoustic receiver. The speed of sound determination circuity determines, based on the time of flight and the distance, a speed of sound through air in the stagnation chamber. The communication circuitry outputs the speed of sound.

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 transceiver baseband hardware including an encryption-decryption block configured to encrypt and jumble intended transmission data or unjumble and decrypt received encrypted data, the encryption-decryption based on key coefficients generated based on a random key address, the encryption-decryption implemented via a cross logical operation of the encryption-decryption block. The cross logical operation includes when lower significant bytes of the key coefficients operating on most significant bytes of the intended transmission data and the encrypted data. The jumble and unjumble are implemented by a byte displacement/placement block based at least in part on the random key address.

Abstract: A micromechanical pressure sensor for measuring a pressure differential includes a diaphragm having an inner region and two edge regions, one opposite the other with respect to the inner region. Two or more piezoresistive resistance devices are on the diaphragm, at least one in each of the inner and edge region, and are configured to be electrically connected in a bridge circuit. The micromechanical pressure sensor is configured so that an operating temperature of the one or more piezoresistive resistance devices in the inner region is substantially the same as an operating temperature of the one or more piezoresistive resistance devices in at least one of the edge regions throughout a full operating range such that an error of the micromechanical pressure sensor output resulting from self-heating is less than if the micromechanical pressure sensor were not configured to maintain the operating temperatures substantially the same.

Abstract: A system includes a heating element, a signal injector, and a signal receiver. The heating element is coupled between a first node and a second node. The signal injector is communicatively coupled the heating element via the first node. The signal generator is configured to provide a test signal to the heating element. The signal receiver is communicatively coupled to the heating element via the second node. The signal receiver is configured to receive the test signal from the heating element and to determine a capacitance of the heating element based upon the received test signal.

Abstract: A micromechanical piezoresistive pressure sensor includes a diaphragm configured to mechanically deform in response to an applied load, a sensor substrate located on the diaphragm, and a number of piezoresistive resistance devices located on the sensor substrate. The piezoresistive resistance devices are arranged in a first planar array defining a grid pattern having two or more rows, each row being aligned in a first direction. The piezoresistive resistance devices are configured to be electrically connected in a number of bridge circuits, whereby the piezoresistive resistance devices in each row is electrically connected in an associated bridge circuit. A method of using the micromechanical piezoresistive pressure sensor is also disclosed.

Abstract: An air data probe system can include a pitot static system configured to sense at least one total pressure value of a flow at one or more locations, at least one static pressure value of the flow at the one or more locations, and, directly or indirectly, at least one differential static pressure value of the flow at the one or more locations. The system can include an angle of slip (AOS) module configured to determine a local angle of slip (LAOS) value at each location based on the at least one total pressure value at each location, the at least one static pressure value at each location, and the at least one differential static pressure value at each location.

Abstract: A system for an aircraft includes a heater comprising a resistive heating element and insulation surrounding the resistive heating element. A first current flows into the resistive heating element to provide heat and a second current flows out of the resistive heating element. The system further includes a leakage sensor configured to produce a leakage sensor signal representing a leakage current from the heater and a prediction processor configured to predict heater failure based on the leakage sensor signal.