Abstract: A nozzle configured to receive and disperse a high-pressure fluid or a low-pressure fluid is disclosed. The nozzle includes a nozzle body defining an open end, a closed end, and a side wall connecting the open end to the closed end, where the open end of the nozzle body configured to receive either the high-pressure fluid or the low-pressure fluid. The side wall defines a plurality of low-pressure apertures, a plurality of high-pressure apertures, and a compressible member positioned within the nozzle body. The plurality of high-pressure apertures are positioned downstream from the plurality of pressure apertures. The low-pressure apertures are smaller in size by a predefined ratio when compared to the high-pressure apertures. The compressible member is in an expanded position and blocks the plurality of high-pressure apertures when the open end of the nozzle body receives the low-pressure fluid.

Abstract: Ice detection systems for aircraft and related methods are disclosed. A disclosed example ice detection system includes a thermochromic device to sense a temperature of freestream air relative to a temperature threshold, and a hydrochromic device to sense an amount of moisture in the freestream air relative to a moisture threshold. A controller to detect an icing condition in response to the thermochromic device sensing a temperature that is less than or equal to the temperature threshold and the hydrochromic device sensing an amount moisture that exceeds the moisture threshold.

Abstract: A method and apparatus for simulating icing conditions using a wind tunnel is provided. Water drops are sprayed from a number of nozzles into the wind tunnel. A mist of cryogenic liquid is sprayed into a path of the water drops downwind of the nozzles in the wind tunnel, wherein the mist of cryogenic liquid turns the water drops into ice crystals.

Abstract: A nozzle configured to receive and disperse a high-pressure fluid or a low-pressure fluid is disclosed. The nozzle includes a nozzle body defining an open end, a closed end, and a side wall connecting the open end to the closed end, where the open end of the nozzle body configured to receive either the high-pressure fluid or the low-pressure fluid. The side wall defines a plurality of low-pressure apertures, a plurality of high-pressure apertures, and a compressible member positioned within the nozzle body. The plurality of high-pressure apertures are positioned downstream from the plurality of high-pressure apertures. The low-pressure apertures are smaller in size by a predefined ratio when compared to the high-pressure apertures. The compressible member is in an expanded position and blocks the plurality of high-pressure apertures when the open end of the nozzle body receives the low-pressure fluid.

Abstract: Systems and methods are provided for an ice detector with a movable airfoil. The movable airfoil may be airfoil shaped and the ice detector may include an ice detection sensor. The movable airfoil may be adjusted in angle of attack and/or configuration to simulate the pressure gradient experienced by one or more of the wing, fuselage, engine, horizontal/vertical stabilizer, or other component of the aircraft. Sensors may be used to detect the configuration of the aircraft or the components of the aircraft and the configuration of the movable airfoil may then be adjusted to approximate the pressure distribution around the aircraft component. Ice accretion on the movable airfoil may be determined via the data from the ice detector.

Abstract: A method and apparatus for simulating icing conditions using a wind tunnel is provided. Water drops are sprayed from a number of nozzles into the wind tunnel. A mist of cryogenic liquid is sprayed into a path of the water drops downwind of the nozzles in the wind tunnel, wherein the mist of cryogenic liquid turns the water drops into ice crystals.

Abstract: A system detects ice on a surface. The system comprises an ultraviolet (UV) light source configured to project light primarily in the UV-A spectrum onto the surface. The system further comprises an optical device configured to capture an image of the surface while the light primarily in the UV-A spectrum is projected by the UV light source. The system further comprises a control device communicatively coupled to the optical device. The control device is configured to receive the image from the optical device and determine whether or not ice is present on the surface based respectively on whether or not visible light induced by the light projected by the UV light source is captured in the image.

Abstract: Ice detection systems for aircraft and related methods are disclosed. A disclosed example ice detection system includes a thermochromic device to sense a temperature of freestream air relative to a temperature threshold, and a hydrochromic device to sense an amount of moisture in the freestream air relative to a moisture threshold. a controller to detect an icing condition in response to the thermochromic device sensing a temperature that is less than or equal to the temperature threshold and the hydrochromic device sensing an amount moisture that exceeds the moisture threshold.

Abstract: Aspects of the present disclosure relate to systems and methods for automated fire detection, such as in aircraft galleys, or other areas where power sources may result in fire or smoke. The system includes one or more detectors to monitor for smoke or fire in an aircraft galley. Upon detection of smoke or fire, a signal is sent from the one or more detectors to a controller. In response to the incoming signal, the controller sends a signal to a galley power source. The signal provided to the galley power source ceases the application of power to one or more devices located in the galley, extinguishing the source of the fire or smoke. The controller may also send a notification signal to alert the crew to the potential fire hazard. A method of operation is also disclosed.

Abstract: A system detects ice on a surface. The system comprises an ultraviolet (UV) light source configured to project light primarily in the UV-A spectrum onto the surface. The system further comprises an optical device configured to capture an image of the surface while the light primarily in the UV-A spectrum is projected by the UV light source. The system further comprises a control device communicatively coupled to the optical device. The control device is configured to receive the image from the optical device and determine whether or not ice is present on the surface based respectively on whether or not visible light induced by the light projected by the UV light source is captured in the image.

Abstract: A method for detecting an icing condition using an apparatus comprising a piezoelectric material and a vibration detector. The piezoelectric material has a surface proximate to a surface of a vehicle. The piezoelectric material is configured to vibrate. The vibration detector is configured to detect a change in vibrations in the piezoelectric material that indicates a presence of an icing condition on the surface of the piezoelectric material.

Abstract: An aircraft comprises a fuselage having a compartment, and a fire suppression system for delivering fire suppressant to the compartment. The system includes at least one suppressant concentration sensor located in the compartment, a valve for regulating flow of the fire suppressant to the compartment, and a controller, responsive to the sensor, for controlling the valve to maintain fire suppressant concentration within the compartment at a target concentration.

Abstract: Systems and methods are provided for an ice detector with a movable airfoil. The movable airfoil may be airfoil shaped and the ice detector may include an ice detection sensor. The movable airfoil may be adjusted in angle of attack and/or configuration to simulate the pressure gradient experienced by one or more of the wing, fuselage, engine, horizontal/vertical stabilizer, or other component of the aircraft. Sensors may be used to detect the configuration of the aircraft or the components of the aircraft and the configuration of the movable airfoil may then be adjusted accordingly.

Abstract: Aspects of the present disclosure relate to systems and methods for automated fire detection, such as in aircraft galleys, or other areas where power sources may result in fire or smoke. The system includes one or more detectors to monitor for smoke or fire in an aircraft galley. Upon detection of smoke or fire, a signal is sent from the one or more detectors to a controller. In response to the incoming signal, the controller sends a signal to a galley power source. The signal provided to the galley power source ceases the application of power to one or more devices located in the galley, extinguishing the source of the fire or smoke. The controller may also send a notification signal to alert the crew to the potential fire hazard. A method of operation is also disclosed.

Abstract: A method for detecting an icing condition using an apparatus comprising a piezoelectric material and a vibration detector. The piezoelectric material has a surface proximate to a surface of a vehicle. The piezoelectric material is configured to vibrate. The vibration detector is configured to detect a change in vibrations in the piezoelectric material that indicates a presence of an icing condition on the surface of the piezoelectric material.

Abstract: A method and apparatus for detecting an icing condition. The apparatus comprises a piezoelectric material and a vibration detector. The piezoelectric material has a surface proximate to a surface of a vehicle. The piezoelectric material is configured to vibrate. The vibration detector is configured to detect a change in vibrations in the piezoelectric material that indicates a presence of an icing condition on the surface of the piezoelectric material.

Abstract: A method and apparatus for detecting an icing condition. The apparatus comprises a sensor system and an icing condition detector. The sensor system is configured to collect drops of water from air on an exterior of an aircraft and generate a number of images of the drops of water collected. The icing condition detector is configured to detect a presence of a number of types of icing conditions for the aircraft using the number of images from the sensor.

Abstract: A method and apparatus for an ice detection system. The ice detection system includes a first sensor located on a leading edge of a vertical stabilizer on an aircraft, a second sensor located on a first side of the vertical stabilizer, and a third sensor located on a second side of the vertical stabilizer. The first sensor is configured to detect a first type of icing condition for the aircraft. The second sensor is configured to detect a second type of icing condition for the aircraft. The third sensor is configured to detect the second type of icing condition for the aircraft.

Abstract: A method and apparatus for generating a flow of heated air in an airfoil model of an inlet of an aircraft engine. Heated air is sent into a duct system associated with the airfoil model of the inlet of the aircraft engine. The heated air is circulated within the airfoil model of the inlet of the aircraft engine using the duct system in a manner that simulates air flowing in the inlet of the aircraft engine.

Abstract: A method and apparatus for detecting icing conditions. An icing condition detection system comprises a number of sensors and an icing condition detector. The number of sensors is located in a number of locations on an aircraft. A sensor in the number of sensors is configured to emit electromagnetic radiation into drops of water in an environment around the aircraft. The sensor in the number of sensors is configured to detect responses to the electromagnetic radiation. The sensor in the number of sensors is configured to generate data from the responses. The icing condition detector is configured to monitor for the data from the number of sensors. The icing condition detector is further configured to detect a presence of a number of types of icing conditions for the aircraft using the data from the number of sensors.