Abstract: An adjustable moment counterweight assembly for an angle of attack sensor includes a fixed counterweight configured to fixedly attach to a shaft of the angle of attach sensor, the shaft being rotatable about an axis; an adjustable counterweight configured to move in a radial direction relative to the fixed counterweight via rotation of a threaded member; and a first fastener in operable communication with the fixed counterweight and the adjustable counterweight such that the first fastener can fixedly attach the adjustable counterweight to the fixed counterweight.

Abstract: Apparatus and associated methods relate to determining altitude of an aircraft during flight based on properties of vortex shedding. A vortex-shedding projection is projected into the airstream adjacent to the exterior surface of the aircraft so as to cause vortex-shedding turbulence of the airstream. One or more downstream sound-pressure detectors, which are attached to the exterior surface of the aircraft downstream from the vortex-shedding projection, detect(s) a vortex-shedding frequency f of the vortex-shedding turbulence caused by the vortex-shedding projection. A processor determines the altitude of the aircraft based, at least in part, on the vortex-shedding frequency f of the vortex-shedding turbulence as detected by the one or more downstream sound-pressure detectors.

Abstract: A sensor is configured to attach to a main body and includes a sensor body, a transducer, a transmitter, and a power source. The sensor body is configured to provide a smooth transition with a surface of the main body. The transducer is positioned within the sensor body and is configured to provide a sensed output. The transmitter is positioned within the sensor body and is configured to transmit the sensed output. The power source is positioned within the sensor body and is configured to provide electrical power to the transducer and the transmitter.

Abstract: Systems and methods for operating sensors in an aircraft are provided. Aspects include receiving, by a processor associated with a sensor, a first request to test a transmitter function of the sensor, transmitting a test message to one or more other sensors associated with the aircraft, and listening to a transmitter associated with each of the one or more other sensors to determine a transmitter status of the sensor, wherein the transmitter status of the sensor is a pass status based on receiving a confirmation from at least one of the one or more other sensors. Aspects also include transmitting air data parameters and health status parameters associated with the air data probe to the one or more other air data probes.

Abstract: An air data probe includes a probe head, a port within the probe head in fluid communication with external airflow, and a pneumatic pressure sensor mounted within the port.

Abstract: An aircraft probe includes a base, a strut that extends from the base, at least one port, and an electronics assembly insertable into the strut and removable from the strut. The electronics assembly includes at least one pressure sensor that is pneumatically connected to the at least one port to sense a first pressure when in the inserted position.

Abstract: A MEMS pressure sensor includes a first plate with a hole on a diaphragm bonded to the first plate around its rim with the diaphragm positioned over the hole. An isolation frame is bonded to the diaphragm and a second plate with a pillar is bonded to the isolation frame around its rim to form a cavity such that the end of the pillar in the cavity is proximate a surface of the diaphragm. The diaphragm and second plate form a capacitive sensor which changes output upon deflection of the diaphragm relative to the second plate.

Abstract: Systems and methods for wireless network deployment are provided. Aspects include scanning, by a network controller, a plurality of wireless channels to determine an energy level for each channel in the plurality of wireless channels. Selecting a primary channel and a secondary channel from the plurality of wireless channels based at least in part on the energy level. Selecting a primary wireless controller and a secondary wireless data controller for each of the plurality of the wireless sensor nodes and establishing wireless communication with each of a plurality of wireless sensors over the primary channel and the secondary channel.

Abstract: An aircraft ice detection system is configured to determine a condition of a cloud and includes a radar transmitter, a radar receiver, optics and a splitter. The radar transmitter is configured to produce quasi-optical radiation. The optics are configured to direct the quasi-optical radiation from the radar transmitter to the cloud and receive reflected quasi-optical radiation from the cloud. The radar receiver is configured to receive the reflected quasi-optical radiation from the optics and the splitter is configured to direct the reflected quasi-optical radiation from the optics to the radar receiver.

Abstract: Inspecting an air data probe for physical degradation includes generating a silhouette of the air data probe based on an identification of the air data probe to be inspected. The silhouette is simultaneously displayed with an image of the air data probe produced by a camera, and the displayed image of the air data probe is caused to conform to the silhouette on the display. An image of the air data probe is captured while the displayed image of the air data probe conforms to the silhouette on the display. The captured image is analyzed to identify physical degradation of the air data probe. A maintenance recommendation for the air data probe is generated based on the identified physical degradation.

Abstract: A system includes a probe, a transducer, and a sealing feature. The probe is detachable and includes a first gas path extending from a head to a mount. The transducer is configured to mate with the mount and includes a second gas path with an inlet configured to be in fluid communication with the outlet of the first gas path when the transducer is mated with the mount and at least one sensor disposed along the second gas path. The sealing feature includes a first membrane configured to allow pressure to be conveyed from the first gas path to the second gas path when the transducer is mated with the mount while preventing contaminants from entering the second gas path when the transducer is distant from the probe.

Abstract: Apparatus and associated methods relate to rendering an image of objects in a region of an airport taxiway. The image is rendered from data provided by multiple sources. Three-dimensional models of static airport structures located within the region of an airport taxiway are provided. Rendered image data of the region of the airport taxiway if formed based on the retrieved three-dimensional models of the static airport structures. Data indicative of locations of dynamic objects within the region of the airport taxiway is also provided. Symbols identifying the dynamic objects within the region of the airport taxiway are mapped into the rendered image data at the locations indicated by the provided data. The rendered image data is sent to a display device configured to display the rendered image data.

Abstract: Apparatus and associated methods relate to detecting cloud conditions from a distance by generating a polarized microwave-frequency electromagnetic pulse and evaluating various reflected wave parameters pertaining to a corresponding cloud-reflected microwave-frequency electromagnetic reflection. Various cloud metrics can be calculated using these collected wave parameters. The microwave-frequency pulses can be scanned over multiple dimensions, using a steered beam arrangement which will lead to the ability to scanning a conical sector of the space in front of the aircraft. These collected multi-dimensional wave parameters can then be used to generate multi-dimensional maps of cloud metrics. Such cloud metrics can include relative velocities of moving cloud conditions in the flight direction, particle density distributions, ice/water ratios, estimates of particle side distributions, etc.

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.

Abstract: A method of repairing an air data probe includes assessing an air data probe for a damaged portion. The method includes depositing a material on the air data probe to repair the damaged portion of the air data probe. An air data probe includes a probe body including a sense port inlet defined through a wall of the probe body. At least a portion of the wall surrounding the sense port inlet is defined by a deposited material having a different microstructure than a material defining another portion of the wall.

Abstract: Systems and methods for sensing an analog signal through digital input/output (I/O) pins are provided. Aspects include an analog to digital (ADC) circuit configured to generate a digital signal based on observations of the analog signal obtained from an analog circuit, where the ADC circuit includes a difference amplifier, a comparator, a divideby2 counter and two AND gates. Aspects also include a controller including a pin configured to receive the digital signal. The controller is configured to count pulses within the digital signal and determine values corresponding to the analog signal based on the counted pulses.

Abstract: A windshield wiper system for an aircraft is provided and includes a motor, an output shaft, a wrap spring and crank rocker mechanism (WSCRM) to which the motor and the output shaft are coupled and a controller. By way of the WSCRM, first directional rotation input to the WSCRM from the motor via a two-stage gear reduction is converted such that the output shaft drives wiper blade oscillation through a first sweep angle and second directional rotation input to the WSCRM from the motor is converted such that the output shaft drives wiper blade oscillation through a second sweep angle. The controller is configured to control the motor such that the first directional rotation is continuously or non-continuously input during first or second flight conditions, respectively, and the second directional rotation is continuously input during third flight conditions.

Abstract: A system and method for an aircraft includes an air data system and an acoustic sensing system. The air data system includes a pitot tube positioned to sense a pitot pressure of an airflow about an exterior of the aircraft, and an angle of attack vane positioned to sense an angle of attack of the aircraft. The pitot pressure and the angle of attack are used to determine first air data parameters. The acoustic sensing system is configured to emit acoustic signals about the exterior of the aircraft and sense the acoustic signals as sensed data. The sensed data is used to determine second air data parameters.

Abstract: An optical system includes an illumination source. A lens is optically coupled to the illumination source for projecting a line image. The lens conforms to a curved profile, and the lens is a Fresnel lens. A method of projecting a line image includes generating illumination from an illumination source. The method includes focusing the illumination through a lens to form a line image, wherein the lens is as described above.

Abstract: An acoustic airspeed sensor system can include at least one acoustic transmitter configured to provide an acoustic pulse, a plurality of acoustic receivers including at least a first acoustic receiver positioned at a first radial distance from the at least one acoustic transmitter and a second acoustic receiver positioned at a second radial distance from the at least one acoustic transmitter. The first acoustic receiver is configured to receive the acoustic pulse at a first time and output a first receiver signal. The second acoustic receiver is configured to receive the acoustic pulse at a second time and output a second receiver signal. The sensor system can include an air data module operatively connected to the first acoustic receiver and the second acoustic receiver. The air data module is configured to determine true air speed (TAS) based upon a first signal delay, a second signal delay, and a wind angle.