The Boeing Company

Ultra Electronics Limited

The Boeing Company, Boeing Commercial Airplanes Group

Hosam E El-Gabalawy

Steve G Mackin

Ian McGregor Stothers

Charles Steven Meis

Warren Andrew Atkey

Douglas J Silva

Royal E Boggs

Cris Kevin Bosetti

Camron Ravell Call

Todd J Germeroth

Mohamed Elbibary

John Alexander Ziebart

David J Lamb

Luis Antonio Laracuente-Colon

A surge control system and method include a valve assembly located along a fluid conduit downstream of one or more compressors in a flow circuit, and configured to receive a fluid stream from the one or more compressors. The valve assembly includes a valve body, a pitot tube integrated onto the valve body, and a pressure sensor device operably connected to the pitot tube. A controller of the surge control system receives pressure measurements generated by the pressure sensor device. The pressure measurements represent pressure in the pitot tube over time. The controller analyzes at least one of (i) the pressure measurements or (ii) flow velocity values derived from the pressure measurements, and detects a surge condition in the flow circuit based on oscillations in the at least one of the pressure measurements or the flow velocity values.

System, method, and valve assembly for surge protection

An ice protection system for an aircraft includes one or more heaters configured to be coupled to a surface of a wing of the aircraft. The ice protection system also includes a controller configured to, in response to a first determination indicating presence of an icing condition, determine a setpoint temperature for a first location of an outer surface of the wing configured to be heated by a heater of the one or more heaters. The controller is also configured to control power provided to the heater based on the setpoint temperature. The setpoint temperature for the first location is determined to cause a second location of the outer surface of the wing, which is heated by the heater and is located at a particular distance from the first location, to remain above a threshold temperature based on a projected temperature profile of the outer surface heated by the heater.

Ice protection system for an aircraft

Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet and a compressor outlet. The compressor inlet to receive airflow from a first air supply source. An air mixing device having a first mixer inlet to receive compressed air from the compressor outlet and a second mixer inlet to receive bleed air from a bleed air system. The bleed air to provide a motive fluid to enable the air mixing device to mix the bleed air and the compressed air to produce mixed air for the anti-icing system.

Bleed air systems for use with aircraft and related methods

A method for controlling compressed air sent to pneumatic systems. The method includes acquiring a set of performance demands for each of a plurality of pneumatic systems in a platform, where the performance demands indicate needs for the compressed air supplied to each of the pneumatic systems, identifying a maximum allowable air discharge temperature limit of a variable speed air compressor configured to supply compressed air to the pneumatic systems, and controlling an operation of the compressor to supply the compressed air to the pneumatic systems to meet the acquired performance demands for at least one of the pneumatic systems while operating the compressor below the maximum allowable air discharge temperature limit.

Compressed air 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

A method includes receiving a plurality of temperature measurements from temperature sensors of an aircraft. The method includes determining whether a first count of one or more first temperature metrics that are within a temperature range is greater than a first threshold. The one or more temperature metrics are derived from the plurality of temperature measurements. The method includes initiating generating an icing output signal when the first count is greater than or equal to the first threshold.

System and method for aircraft ice detection within a zone of non-detection

An ice detection system, in particular a method, apparatus and controller for detecting icing conditions and the presence of ice formed on a structure. Also, a method, apparatus and controller to detect the prevailing environmental conditions to determine whether or not ice may form on a structure. Two heaters of an ice protection system (experiencing substantially the same environmental conditions) are driven to different temperatures (the first greater than or equal to 0&#xb0; C., and the second less than 0&#xb0; C.). A difference in the powers required to drive the two heaters indicates the prevailing environmental conditions. In another embodiment, a heater of an ice protection system is driven and the rate of change of surface temperature is measured over several periods. A substantial deviation from a rate of change of surface temperature, which indicates the presence of ice on the surface of the structure, is detected.

Ice detection system and method

An ice detection system, in particular to a system for detecting icing conditions and a system for detecting the presence of ice formed on a structure, and the methods for doing the same. Two heaters of the ice protection system (experiencing substantially the same environmental conditions) are driven to different temperatures (the first greater than or equal to 0&#xb0; C., and the second less than 0&#xb0; C.). The difference in the powers required to drive the two heaters indicates the prevailing environmental conditions. A heater of the ice protection system is driven and the rate of change of surface temperature is measured over several periods. A substantial deviation from a rate of change of surface temperature, which indicates the presence of ice on the surface of the structure, is detected.

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Bothell, WA, United States of America

Hosam E El-Gabalawy