Patent ID: 9096320
Filing Date: 2015-08-04
Classification: B64D

Abstract:
1. An aircraft cabin pressure control system thrust recovery outflow valve, comprising: a valve frame configured to be mounted on an aircraft exterior skin, the valve frame including an inner surface, an outer surface, a forward seat, and an aft seat, the inner surface defining a flow passage through the valve frame; a single valve door rotationally coupled to the valve frame, and including a leading edge, a trailing edge, and two side edges, the single valve door adapted to receive a drive torque and configured, upon receipt of the drive torque, to rotate between a closed position, a full-open position, and a plurality of partial-open positions between the closed position and the full-open position; and an aerodynamic flap including a first end and a second end, the first end coupled to the single valve door, the second end biased toward the trailing edge of the single valve door, wherein the second end engages the valve frame when the single valve door is in the closed position and in a plurality of open positions.