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: An optical ice detector and airspeed probe includes an ice detection module and an airspeed module. The ice detection module detects the presence or absence of ice, water, or ice and water particles, and the airspeed module determines a line-of-sight speed along a directional vector, each based on backscatter light returns emitted from a common collimated light source. An electronics module determines an airspeed of an aircraft based on the line-of-sight speed determined by the airspeed module and at least one aircraft parameter received from the air data system.

Abstract: An ultrasonic air data system can include a pole having a length longer than a boundary layer thickness of a boundary layer flow such that at least a distal end of the pole is configured to extend outwardly from an aircraft surface to be at least partially outside of the boundary layer flow. The system can include a transmitter disposed on or in the pole at or near the distal end of the pole such that the transmitter is located at least partially outside of the boundary layer flow when in use, wherein the transmitter is configured to output a transmitter signal. The system can include one or more receivers disposed downstream of the pole as defined by the boundary layer flow and configured to receive the transmitter signal.

Abstract: A system for an aircraft includes an optical sensor, at least one aircraft sensor, and a controller. The optical sensor is configured to emit a laser outside the aircraft, and the at least one aircraft sensor is configured to sense at least one aircraft condition. The controller is configured to determine a first operational state of the aircraft based upon the at least one aircraft condition and determine a second operational state of the aircraft based on the at least one aircraft condition, and operate the optical sensor to emit the laser at a first intensity during the first operational state and a second intensity during the second operational state, wherein the second intensity is greater than the first intensity.

Abstract: An air data sensor can include an acoustic transmitter configured to output an acoustic signal into an airflow and a plurality of acoustic transducers configured to receive the acoustic signal output by the acoustic transducer. The air data sensor can also include a light source configured to output a light beam into the airflow, and a light receiver configured to receive scattered light from the light beam. The light source and the light receiver can be bistatic such that a measurement zone is formed away from the air data sensor.

Abstract: An acoustic air data system includes first and second acoustic transmitters, an array of acoustic receivers, and control circuitry. The array is positioned to receive first and second acoustic signals. The control circuitry determines time difference of arrival (TDOA) of the first and second acoustic signals. The control circuitry determines, for each of a first and second set of acoustic receiver pairs, a signal velocity of the first and second acoustic signals, respectively, based on a distance between an inner acoustic receiver and an outer acoustic receiver and a corresponding TDOA for each pair of acoustic receivers. The control circuitry estimates one or more of wind angle, speed of sound, Mach number, and true airspeed of the airflow about the exterior of the vehicle based on parameters of a best fit circle.

Abstract: Apparatus and associated methods relate to detecting turbulence of an airstream over an airfoil surface of an aircraft using a sequence of acoustic transducers attached to the airfoil surface of the aircraft along a path. Each of the sequence of acoustic transducers is configured to detect acoustic waves indicative of airstream condition proximate the acoustic transducer. A processor is configured to determine, for each of the sequence of acoustic transducers, a level of turbulence of the airstream proximate the acoustic transducer.

Abstract: A laser sensing system includes an emitter configured to emit a laser, and a controller. The intensity of the laser is based upon power provided to the laser sensing system. The controller is configured to control the power provided to the laser sensing system, obtain feedback parameters indicative in part of molecular content of the atmosphere, and control the power provided to the laser sensing system based upon the feedback parameters.

Abstract: An optical ice detector and airspeed probe includes an ice detection module and an airspeed module. The ice detection module detects the presence or absence of ice, water, or ice and water particles, and the airspeed module determines a line-of-sight speed along a directional vector, each based on backscatter light returns emitted from a common collimated light source. An electronics module determines an airspeed of an aircraft based on the line-of-sight speed determined by the airspeed module and at least one aircraft parameter received from the air data system.

Abstract: A system includes a laser air data sensor and an acoustic air data sensor. The laser air data sensor is configured to emit directional light into airflow about an aircraft exterior and to generate first air data parameter outputs for the aircraft based on returns of the emitted directional light. The acoustic air data sensor is configured to emit acoustic signals into the airflow about the aircraft exterior, sense the acoustic signals, and generate second air data parameter outputs for the aircraft based on the sensed acoustic signals.

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: 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: An acoustic air data system includes first and second acoustic transmitters, an array of acoustic receivers, and control circuitry. The array is positioned to receive first and second acoustic signals. The control circuitry determines time difference of arrival (TDOA) of the first and second acoustic signals. The control circuitry determines, for each of a first and second set of acoustic receiver pairs, a signal velocity of the first and second acoustic signals, respectively, based on a distance between an inner acoustic receiver and an outer acoustic receiver and a corresponding TDOA for each pair of acoustic receivers. The control circuitry estimates one or more of wind angle, speed of sound, Mach number, and true airspeed of the airflow about the exterior of the vehicle based on parameters of a best fit circle.

Abstract: Apparatus and associated methods relate to detecting turbulence of an airstream over an airfoil surface of an aircraft using a sequence of acoustic transducers attached to the airfoil surface of the aircraft along a path. Each of the sequence of acoustic transducers is configured to detect acoustic waves indicative of airstream condition proximate the acoustic transducer. A processor is configured to determine, for each of the sequence of acoustic transducers, a level of turbulence of the airstream proximate the acoustic transducer.

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: 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: 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: An aircraft freestream data system can include a first ultrasonic air data system (UADS) configured to sense local acoustic properties at a first location on an aircraft, a first local air data module operatively connected to the first UADS and configured to determine first local air data of the first location and to output first local air data, and a freestream data module operatively connected to the first local air data module. The freestream data module can be configured to receive the first local air data from the local air data module, determine one or more freestream air data parameters based on at least the first local air data, and output the one or more freestream air data parameters to one or more aircraft consuming systems.

Abstract: An air data sensor can include an acoustic transmitter configured to output an acoustic signal into an airflow and a plurality of acoustic transducers configured to receive the acoustic signal output by the acoustic transducer. The air data sensor can also include a light source configured to output a light beam into the airflow, and a light receiver configured to receive scattered light from the light beam. The light source and the light receiver can be bistatic such that a measurement zone is formed away from the air data sensor.

Abstract: A system and method for an aircraft includes a low profile pneumatic sensing system and an acoustic sensing system. The low profile pneumatic sensing system includes a pneumatic sensor positioned to sense first sensed data of an airflow about an exterior of the aircraft and does not extend beyond a boundary layer of the aircraft. The first sensed data is 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 second sensed data. The second sensed data is used to determine second air data parameters.