AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM INCLUDING VALVE BUILT-IN-TEST WITHOUT POSITION FEEDBACK

An aircraft environmental control system (ECS) includes a first valve (110) that is adjustable between a plurality of first positions to open or shut-off a bleed air flow that flows from an inlet of the first valve to an outlet of the first valve. A second valve (116) includes an inlet in fluid comm...

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Bibliographische Detailangaben
Hauptverfasser:	HARTMAN, Jay H, JOYCE, James, MALJANIAN, John M, KLINE, Erin G, KAMENETZ, Jeffry K
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION COSMONAUTICS DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR PARACHUTES PERFORMING OPERATIONS TRANSPORTING
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Beschreibung
Zusammenfassung:	An aircraft environmental control system (ECS) includes a first valve (110) that is adjustable between a plurality of first positions to open or shut-off a bleed air flow that flows from an inlet of the first valve to an outlet of the first valve. A second valve (116) includes an inlet in fluid communication with the first valve outlet, and is adjustable between a plurality of second positions to throttle the bleed air that flows from the inlet of the second valve to an outlet of the second valve. A valve position sensor (125) outputs a position signal indicating a measured position among the plurality of second positions. A controller (150) is in signal communication with the valve position sensor. The controller is configured to determine a primary effective area of the second valve based on the measured position, and to diagnose operation of the first valve based on the primary effective area.