The Boeing Company

Erik Marc Langhofer

Charles Steven Meis

Mark Joseph Clemen, Jr

George Albert Perry

Jerry Lee Wert

Scott Hutchinson Gardner

Rachel Malia Darr

David Charles Hass

Edward Charles Natsui

Bryan Douglas Welsh

Olubusola Anthony Dasilva

Heath Alan Conn

Hosam El Din El-Gabalawy

Joseph M DiRusso

Melissa Marie Bravin

Bryan D Welsh

Mark Joseph Clemen

A system and method include a first icing detector configured to detect a first icing condition in relation to one or more portions of an aircraft. The first icing detector is configured to output a first icing signal indicative of the first icing condition. A second icing detector is configured to detect a second icing condition in relation to the one or more portions of the aircraft. The second icing detector is configured to output a second icing signal indicative of the second icing condition. A control unit is in communication with the first icing detector and the second icing detector. The control unit is configured to receive the first icing signal from the first icing detector and the second icing signal from the second icing detector. The control unit is further configured to distinguish between presence of supercooled liquid water and ice crystal icing in response to receiving one or both of the first icing signal or the second icing signal.

Deicing systems and methods for an aircraft

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.

Ice crystal icing condition simulation method and system

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.

Icing condition detection method

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.

Icing condition detection system

A method is provided that includes a number of operations performed in real-time during flight of the aircraft. That is, the method may include monitoring a continuous electrical signal output by a sensor on a surface of the aircraft, where a magnitude of the electrical signal may be related to an amount of ice buildup. The method may include calculating a liquid water content (LWC) value as a function of a rate of change of the electrical signal, and iteratively calculating a total water exposure (TWE) value as a function of the LWC value. The TWE value may represent a total water exposure of the aircraft from a time of an initial event, and may be calculated as a running total over a plurality of iterations. And the method may include performing a remedial or alert action in an instance in which the TWE value reaches a TWE threshold.

Detecting inflight icing conditions on aircraft

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.

Automated water drop measurement and ice detection system

A thermal anti-ice system in an aircraft. A controlled valve receives air from a compressor bleed port of an engine of the aircraft. A self-regulating valve is fluidly connected between the controlled valve and an inlet of the engine. A first pressure sensor senses pressure between the valves. A second pressure sensor senses pressure between the self-regulating valve and the inlet. The system can be used to de-ice aircraft inlet lip skins made of composite materials that have comparatively lower design temperatures than other comparable materials.

Growing community of inventors

Seattle, WA, United States of America

Erik Marc Langhofer