Abstract: A stress-sensitive device includes a substrate having a first surface with a cavity defined therein and a three-dimensional deformable material extending along the first surface and into the cavity. The three-dimensional deformable material has an electrical characteristic responsive to deformation. A method of forming a three-dimensional stress-sensitive device includes providing a substrate having a first surface and a second surface opposite the first surface, forming a cavity in the substrate, wherein the cavity is open to the first surface, depositing a sacrificial layer in the cavity, depositing a deformable material on the sacrificial layer, and removing at least a portion of the sacrificial layer to form an interstitial space between the deformable material and the substrate in the cavity.

Abstract: A windshield wiper system for an aircraft includes a wiper drive shaft with a first end and a second end opposite the first end. The second end includes a first threaded section between the first end and the second end, a second threaded section extending axially along the wiper drive shaft between the first threaded section and the second end relative to a center axis of the wiper drive shaft, and a spline section axially between the first threaded section and the second threaded section. Further included is a first nut to thread to the first threaded section, a second nut to thread to the second threaded section, and a wiper arm assembly including an adjustment sleeve configured to interlock with the spline section, a wiper arm with a first end configured to enclose the adjustment sleeve, and a second end of the wiper arm attached to a wiper blade.

Abstract: An airborne object detection system can include one or more imaging devices configured to be disposed on an aircraft and to produce imaging data of one or more portions of an environment surrounding the aircraft, and an object detection system operatively connected to the one or more imaging devices to receive the imaging data. The object detection system can be configured to determine whether there are one or more collision risk objects in the imaging data that will or are likely to collide with the aircraft based on the imaging data. The object detection system can be configured to determine a collision location on the aircraft that the one or more collision risk objects will or are likely to collide with.

Abstract: A pressure sensor includes a header with a cavity, a pressure sensing element, an isolator, an isolator support, a damping gap, and oil. The pressure sensing element is in the cavity. The isolator has corrugations and is mounted to a top of the header. The isolator covers the cavity. The isolator support is in the cavity of the header above the pressure sensing element. The isolator support is corrugated. The corrugations of the isolator support align with the corrugations on the isolator. The damping gap is between the isolator support and the isolator. The damping gap has a constant width between the isolator support and the isolator. Oil fills the damping gap and the cavity in the header. The oil moves between the damping gap and the header cavity in response to external pressure changes moving the isolator.

Abstract: A wiper apparatus includes a wiper axis interface configured for mounting a wiper assembly to a wiper drive. A lower wiper arm extends from the wiper axis interface to a wiper mount that is configured to connect the lower arm to an upper arm. A first end of the lower wiper arm proximate the wiper axis interface has a first airfoil profile and wall thickness. A second end of the lower wiper arm proximate the wiper mount has a second airfoil profile and wall thickness. An intermediate portion of the lower wiper arm extending between the first and second ends has a transitioning airfoil profile and thickness that transitions from the first airfoil profile and wall thickness to the second airfoil profile and wall thickness.

Abstract: A system includes an optical ice detection (OID) sub-system optically coupled to light collection optics. A water vapor differential absorption LIDAR (WV-DIAL) sub-system is optically coupled to the OID laser source or light collection optics. The OID sub-system and the WV-DIAL sub-system share at least a portion of an optical path of the light source or through the light collection optics. The OID sub-system, the WV-DIAL sub-system, and the illumination and light collection optics can all be aboard an aircraft. A method includes using a set of illumination and light collection optics aboard an aircraft to obtain data indicative of optical ice detection (OID) and water vapor differential absorption LIDAR (WV-DIAL), e.g. to detect contrail forming conditions for the aircraft and/or predict persistence of contrails from the aircraft.

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: In accordance with at least one aspect of this disclosure, a system can include, a housing assembly and an element assembly having a dual-material component therein, the element assembly joined within the housing assembly via a weld joint at a weld interface between the dual material component and the housing assembly.

Abstract: A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that an evacuation slide deployment path is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to identify a region within the captured image data that corresponds to the evacuation slide deployment path, determine whether the evacuation slide deployment path will generate a failed deployment outcome, and produce a warning associated with the evacuation slide deployment path in response to determining that the evacuation slide deployment path will generate the failed deployment outcome.

Abstract: A method includes converting audio to text, converting the text to a taxi path, and using a look-up table (LUT) to check for obstructions in the taxi path. The method includes issuing a warning if there are one or more obstructions in the taxi path based on the LUT or else refraining from issuing a warning if there are not one or more obstructions in the taxi path based on the LUT. Converting audio to text can include using a machine learning model. Before converting the audio to text, the method can include checking communications between a pilot and air traffic control (ATC) for keywords relevant to taxiing. Converting audio to text can be performed upon detecting the keywords in the audio. The audio can include words spoken by ATC to the pilot and/or words spoken by the pilot to ATC.

Abstract: A sensor includes an airfoil body, a heater element, and a temperature probe. The airfoil body defines a sensor axis and having a leading edge, a trailing edge, and an ice accretion feature. The heater element extends axially through the airfoil body between the leading edge and the trailing edge of the airfoil body. The temperature probe extends axially through the airfoil body between the heater element and the trailing edge of the airfoil body. The heater element is axially overlapped by the ice accretion feature to accrete ice chordwise forward of a tip surface aperture. Gas turbine engines, methods of making sensors, and methods of accreting ice on sensors are also described.

Abstract: A connector includes a shell, an insert that fits within the shell, and a socket that extends within the insert. The socket includes a hood, a body within the hood, an annular tine extending from the body within the hood, an annular lip extending around the tine adjacent an end of the tine, and a cavity formed within the tine.

Abstract: A pitot tube includes an outer tube extending from a first tube end to second tube end. The second tube end defines a tip portion of the pitot tube. A tube sleeve is located inside of the outer tube and defines a tube passage extending from the first tube end to the second tube end. A heating element is located between the outer tube and the tube sleeve. The heating element is isolated from airflow into the tube passage. A method of forming a pitot tube includes installing a heating element to an outer surface of a tube sleeve, the tube sleeve defining a tube passage of the pitot tube. The tube sleeve is secured in an outer tube such that the heating element is between the tube sleeve and the outer tube and is isolated from airflow through the tube passage.

Abstract: A sensor includes a mount arranged along a sensor axis, an airfoil body fixed to the mount and having a first face and second face extending along the sensor axis, a heater element, and a temperature probe. The heater element and the temperature probe are positioned within the airfoil body and extend axially along the airfoil body. The airfoil body defines within its interior a pressure channel having an inlet segment extending between the heater element and the first face of the airfoil body to prevent ice formation and/or melt ice entrained within air traversing the pressure channel. Gas turbine engines, methods of removing ice or preventing ice formation, and methods of making sensors are also described.

Abstract: Apparatus and associate methods relate to desaturation protection of a metal-oxide-semiconductor field-effect transistor (MOSFET) or an insulated-gate bipolar transistor (IGBT). Desaturation protection circuitry provides desaturation protection to the MOSFET or IGBT as well protection of the desaturation protection circuitry, should such circuitry be connected to reverse power. The desaturation protection circuitry determines a desaturation condition based on a control voltage generated by a Zener-diode-resistor network conductively coupled between first and second conduction nodes of the MOSFET or IGBT. The Zener-diode-resistor network is coupled to first and second conduction nodes via a rectifying diode that is configured to protect the desaturation protection circuitry from reverse bias power. Negative feedback limits current through a signal isolation device that is conductively isolated from the output node, which indicates whether the desaturation condition has been determined.

Abstract: A probe head of a magnetostrictive oscillator includes a base and a plurality of hollow protrusions extending from the base. Each protrusion of the plurality of hollow protrusions includes a first end and a second end opposite the first end. The second end is connected to the base. Each protrusion also includes an inner side and an outer side opposite the inner side.

Abstract: A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that an engine inlet of an engine of the aircraft is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to determine whether persons or foreign objects are present near the engine inlet, or detect damage or deformation of the engine inlet.

Abstract: A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that an evacuation slide deployment path is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to identify a region within the captured image data that corresponds to the evacuation slide deployment path, determine whether the evacuation slide deployment path will generate a failed deployment outcome, and produce a warning associated with the evacuation slide deployment path in response to determining that the evacuation slide deployment path will generate the failed deployment outcome.

Abstract: Disclosed is an aircraft windshield wiper system, having: a wiper arm; a reversible motor that drives the wiper arm, the motor including: a stator; a rotor configured to rotate relative to the stator; a forward shaft segment that is driven by the rotor and being rotationally connected to the wiper arm; an aft shaft segment that is driven by the rotor, the aft shaft segment including a forward end and an aft end; a ball nut that translates along the aft shaft segment from rotation of the aft shaft segment; a forward stop at a forward end of the aft shaft segment, configured to stop forward translational motion of the ball nut along the aft shaft segment; and an aft stop at an aft end of the aft shaft segment, configured to stop aft translational motion of the ball nut along the aft shaft segment.

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.