Abstract: A bulkhead for an air data probe includes an upstream end, a downstream end, and an upstream portion extending from the upstream end. The upstream portion includes an exterior surface, a first plurality of walls extending radially outward from the exterior surface of the upstream portion, a first pad extending radially outward from the exterior surface of the upstream portion, and a first plurality of channels formed between one or more of the first plurality of walls and the first pad. The first plurality of channels are configured to receive a wire heater.

Abstract: A device or system for prognostic health monitoring (PHM) of aircraft-based analog angle of attack (AoA) sensors includes a data coordinator for sampling AoA data collected by one or more AoA sensors. The data coordinator concurrently samples sensor health data from a suite of monitoring sensors within each AoA sensor (e.g., orientation, voltage, current, temperature). Based on the analog AoA data and sensor health data, the data coordinator determines a sensor responsiveness factor (RF) for each reporting analog AoA sensor. Current RF data is compared to historical RF data to determine a trending responsiveness factor for each analog AoA sensor. If the responsiveness factor for any AoA sensor trends beyond a threshold level, the data coordinator generates an alert for preventive maintenance personal on the ground, the alert indicative of one or more specific fault conditions in that AoA sensor depending on the responsiveness threshold breached.

Abstract: A detector includes a scoop portion. The scoop portion includes a top surface extending continuously from a forward tip to an aft end, a bottom surface opposite from the top surface, and a receiving portion therebetween. The bottom surface includes an aperture. The top surface includes a detent formed therein opposite from the aperture across the receiving portion. The detent is configured and adapted to receive at least a portion of a sensor. A method includes additively manufacturing a scoop portion and brazing a strut portion to the scoop portion. The scoop portion includes an upper surface, a lower surface, and a receiving portion therebetween.

Abstract: Apparatus and associated methods relate to improving measurement of metrics of air data of an atmosphere outside an aircraft. Such measurements are improved by estimating a daylight portion of light received by an optical receiver configured to receive a reflected portion of the projected beam backscattered by the atmosphere. Estimation of the daylight portion is performed using a daylight filter. The daylight filter receives the light received by the optical receiver after it has been filtered by a vapor cell filter and separates the light, as filtered, into a beam sampling portion and a complementary non-sampling portion. The non-beam sampling portion includes wavelengths immediately adjacent to the beam sampling portion. The non-beam sampling portion is used to estimate the daylight portion within the beam sampling portion, which also contains the reflected portion of the projected beam used for calculating the metrics of air data.

Abstract: A windshield wiper system has a drive arm with a drive shaft connector, a curved cantilever beam, and a wiper blade assembly. The drive arm is configured to connect to a drive shaft at the drive shaft connector. The curved cantilever beam is connected to the drive arm with a first drive arm fastener and a moveable drive arm fastener. The first drive arm fastener is positioned on the drive arm between the drive shaft connector and the moveable drive arm fastener. The wiper blade assembly is connected to the curved cantilever beam with a wiper blade fastener. The curved cantilever beam has an effective length extending from the moveable drive arm fastener to the wiper blade assembly fastener.

Abstract: A blockage detection system for detecting aircraft probe blockages includes a processor, a communication device, and computer-readable memory. The computer-readable memory encoded with instructions that, when executed by the processor, cause the system to execute a blockage detection algorithm. The processor receives a static pressure and an impact pressure from one or more aircraft probes. The processor converts the static pressure and the impact pressure to a correlating variable, via the blockage detection algorithm. The processor evaluates the correlating variable, via the blockage detection algorithm, to determine if a value of the correlating variable exceeds a threshold indicative of a blockage. The processor outputs a blockage indicator, to a receiving system in response to the correlating variable exceeding the first threshold indicative of a blockage. The processor is further able to determine if the blockage has cleared by reference to an external comparative pressure measurement.

Abstract: In accordance with at least one aspect of this disclosure, a system includes a wiper system having at least one wiper arm configured to wipe a windshield of a vehicle, a reservoir configured to hold washer fluid, and a fluid line fluidly connected between the reservoir and the wiper system configured to provide the jet of washer fluid from an outlet of the reservoir to the wiper arm for spraying onto the windshield. The reservoir includes, an interior volume having an outlet, and a piston configured to force the washer fluid through the outlet to produce a jet of washer fluid at the outlet.

Abstract: Apparatus and associated methods relate to measuring metrics of a contrail produced by an aircraft engine. To measure such metrics, a beam of light is projected into a projection volume that intersects an exhaust path of the aircraft engine. Light from a reception volume that intersects the exhaust path of the aircraft engine is received. An intersection volume is formed by an intersection of the reception volume and the projection volume. The light received includes a reflected portion of the projected beam backscattered by the atmosphere from within the intersection volume. The reflected portion of light received is used to determine whether a contrail is forming within the intersection volume. An alert is generated in response to determination that a control is forming within the intersection volume.

Abstract: A system includes a wiper arm configured to sweep along a sweep zone defined between a start position and an end sweep position, a wiper drive shaft operatively connected at a proximal end to the wiper arm to drive the wiper arm between the start position and the end sweep position, a tracer operatively connected to a distal end of the wiper drive shaft configured to mimic movement of the wiper arm, and one or more position indicators disposed proximate a distal end of the tracer corresponding to at least the start position and the end sweep position, where the distal end of the tracer configured interact with the one or more limiters during operation of the wiper arm.

Abstract: A windshield wiper system for an aircraft includes a wiper arm and a wiper shaft with a first end connected to a base of the wiper arm. An electric motor is coupled to the wiper shaft to rotationally drive the wiper shaft. The windshield wiper system also includes a brake system. The brake system includes an electromagnet comprising an energized mode and a de-energized mode. The brake system also includes an anti-rotation assembly with a first element and a second element. The first element is connected directly to the wiper shaft. The second element is rotationally stationary relative the wiper shaft and the first element. The second element is configured to interlock with the first element to prevent rotation of the first element and the wiper shaft when both the electromagnet is in the de-energized mode and the wiper arm is in a park position.

Abstract: A method for prognostic health monitoring (PHM) of aircraft-based angle of attack (AoA) sensors includes sampling analog or digital AoA data sensed by one or more AoA sensors. The method includes sampling concurrent sensor health data (e.g., orientation, current, voltage, temperature) from monitoring sensors within each AoA sensor. The method includes, based on the sampled AoA data and concurrent sensor health data, determining a current responsiveness factor (RF) for each individual AoA sensor. The method includes retrieving prior or historical RF data for each individual AoA sensor. The method includes, based on the current and historical RF data, determining an RF trend over time for each AoA sensor. The method includes, when the RF for any AoA sensor trends beyond a responsiveness threshold, generating an alert for preventative maintenance personnel on the ground, the alert indicative of specific fault conditions of the AoA sensor depending on the responsiveness threshold breached.

Abstract: In accordance with at least one aspect of this disclosure, an air data probe includes, an outer shell defining an airflow path from an inlet at a proximal end thereof to a distal end thereof and a heater configured to be installed within the outer shell an in the airflow path, the water dam comprising, one or more sensing elements at a distal end thereof. The system also includes, a water dam disposed on or in the heater winding and between a proximal end and distal end of the heater winding configured to impede a flow of water droplets and ice crystals to permit proper drain hole operation, prevent moisture buildup in rear areas of the probe and pressure lines, and prevent interaction of the flow of water and the one or more sensing elements. The water dam is configured to mechanically stabilize itself on or in the heater winding during installation of the heater winding and water dam into the outer shell.

Abstract: A gas detection system includes a first optical fiber bundle connected to a first multi-pass cell for connecting the first multi-pass cell to a Raman spectrum analyzer. A second optical fiber bundle is connected to the first multi-pass cell for connecting the first multi-pass cell to a second multi-pass cell. The second optical fiber bundle can include a delay coil configured to provide temporal spacing between spectral returns from the first multi-pass cell and from the second multi-pass cell. The first and second multi-pass cells can be biconic multipass cells with a the first optical fiber bundle directed toward a first D-mirror, which is directed toward a T-mirror, which is directed toward a second D-mirror, which is directed toward the second optical fiber bundle. The D-mirrors can be on an opposite end of the first multi-pass cell from the T-mirror and the first and second optical fiber bundles.

Abstract: An optical apparatus can be configured to cover an optical transceiver. At least a portion of the apparatus can be configured to move relative to the transceiver between a block state wherein the apparatus is configured to block transmission from a transmitter of the optical transceiver to a receiver of the optical transceiver as well as block emission from the transmitter to the atmosphere, and one or more transmit states wherein the apparatus is configured to allow at least partial transmission from the transmitter of the optical transceiver to a receiver of the optical transceiver while blocking emission from the transmitter to the atmosphere.

Abstract: In some applications, aircraft air data probes are heated to prevent rain, ice, or other moisture from attaching to the air data probe. The body of the air data probe and the components positioned within the body of the air data probe can be constructed from differing materials, resulting in differing coefficient of thermal expansions for each component. Retention features are added to a housing to prevent an epoxy potting from expanding outside its intended region and preventing damage to the electronic components within the housing.

Abstract: An air-data probe component includes an additively manufactured inner member. The inner member includes integrally formed, monolithic structures including a mandrel bulkhead defining a plurality of pneumatic chambers therein in fluid communication with an outer surface of the mandrel bulkhead through respective pressure ports, and a plurality of pneumatic tubes extending aft of the mandrel bulkhead along a probe axis, each in fluid communication with a respective one of the plurality of pneumatic chambers. An outer cover tip can be engaged about the mandrel bulkhead with a plurality of bores therethrough for fluid communication of outside air pressure into the plurality of pneumatic tubes through the outer cover tip. A forward surface of the outer cover tip can be flush, conformal, and continuous with an aerodynamic outer surface of an aircraft.

Abstract: An air data probe includes an air data probe body and an additively manufactured heater on the air data probe body.

Abstract: An ice detection sensor apparatus includes a strut body extending along a longitudinal axis. The strut body includes an axially extending wall extending around the longitudinal axis to surround an interior space, and an axial-facing end wall connected to an axial end of the axially extending wall. The axial-facing end wall partially bounds the interior space. A magneto strictive oscillator sensing element extends from the interior space, through the axial-facing end wall. The sensing element is engaged to the axial-facing end wall for oscillation along the longitudinal axis relative to the axial-facing end wall. A permanent magnet (PMG) element is integral with, e.g., monolithic with, the strut body.