The Boeing Company

Cris Kevin Bosetti

Charles Steven Meis

Ian M Gunter

Hosam E El-Gabalawy

Michael C Cates

W Brendan Blanton

Fred Norman Krueger

Dean Walters

Bernard P Paul, Jr

Ken L Bernier

John J Biel-Goebel

Jr Bernard P Paul

A Light Detecting and Ranging (LIDAR) based system detecting and quantifying ice accretions and shedding on an aircraft. This system can be used to detect ice, operate ice protection systems, and satisfy aircraft icing certification requirements. This system can also be used to determine the shape, thickness, type, and location of the ice accretions.

Light detection and ranging (LIDAR) ice detection system

An icing conditions detection system is configured to detect icing conditions with respect to an aircraft. The icing conditions detection system includes an icing conditions detector secured to a surface of the aircraft and that is configured to detect liquid water within an air stream through which the aircraft flies. A free stream of atmospheric air passes over the icing conditions detector during flight. An icing conditions determination control unit is communicatively coupled to the icing conditions detector, and is configured to detect a first icing condition and a second icing condition based on at least one icing conditions signal received from the icing conditions detector. The first icing condition differs from the second icing condition.

Aircraft icing conditions detection systems and methods

Systems and methods for the manufacture and use of artificial ice shapes for aircraft certification, including methods of manufacturing artificial ice shapes, artificial ice component systems for attachment to aircraft, methods of flight testing aircraft having artificial ice sections attached thereto, and artificial ice testing systems.

Systems and methods for icing flight tests

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.

Supercooled large drop icing condition detection system

An ice detection system comprising a first group of sensors and a second group of sensors. The first group of sensors is located in a first group of locations on an aircraft. The first group of sensors in the first group of locations is configured to detect a first type of icing condition for the aircraft. The second group of sensors is located in a second group of locations on the aircraft. The second group of sensors in the second group of locations is configured to detect a second type of icing condition for the aircraft.

Growing community of inventors

Seattle, WA, United States of America

Cris Kevin Bosetti