The Boeing Company

Rachel Malia Darr

Charles Steven Meis

Erik Marc Langhofer

David Charles Hass

George A McEachen

Patrick T Baker

Jon Meis

David J Shaw

A method implemented on an aircraft for controlling a fire suppression system comprises receiving, by a computing system of the aircraft, an indication that the fire suppression system of the aircraft should transition to an active state. The computing system determines whether the aircraft is on a surface. Responsive to determining that the aircraft is on the surface, the computing system controls the fire suppression system to remain or transition to an inactive state.

System and method for controlling a fire suppression system of an aircraft

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.

Dual-flow nozzle for dispersing a high-pressure fluid and a low-pressure fluid

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.

Ice detection systems for aircraft and related methods

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 fire suppression system for a compartment of an aircraft includes a sensor system, at least one valve, and a controller. The sensor system is located within the compartment and includes, at least, a first sensor and a second sensor. The first sensor is configured to detect atmospheric substances within the compartment and the second sensor is configured to detect combustion products within the compartment. The at least one valve is configured for regulating flow of a fire suppressant to the compartment. The controller is configured to control flow of the fire suppressant, via the at least one valve, in response to input from the sensor system. The controller provides instructions to discharge the fire suppressant if the first sensor detects atmospheric substances and the second sensor detects combustion products.

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Renton, WA, United States of America

Rachel Malia Darr