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

    公开(公告)号:US20190293204A1

    公开(公告)日:2019-09-26

    申请号:US15927471

    申请日:2018-03-21

    Abstract: An aircraft environmental control system (ECS) includes a first valve 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 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 outputs a position signal indicating a measured position among the plurality of second positions. A controller 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.

    BLEED VALVE MODULE WITH POSITION FEEDBACK AND COOLING SHROUD

    公开(公告)号:US20190093555A1

    公开(公告)日:2019-03-28

    申请号:US16199872

    申请日:2018-11-26

    Abstract: A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements.

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