Patent ID: 6962324

Claim:
An aircraft cabin pressure control valve, comprising: a valve body adapted to mount on the fuselage of an aircraft and having at least a first flow port, a second flow port, and a flow passage therebetween; one or more valve gates rotationally mounted on the valve body proximate the first flow port, each valve gate rotatable between a plurality of valve angles relative to the first flow port to thereby control an effective flow area therethrough, wherein each valve gate is in a closed position when the valve angle is zero degrees; and one or more walls adjacent to the valve body, each wall having at least a distal edge, an inner surface, and an outer surface, each wall inner surface surrounding at least a portion of at least one of the valve gates at least when its valve angle is zero degrees, and each wall distal edge formed at a non-zero wall angle relative to the first flow port, whereby the effective flow area through the first flow port varies substantially non-linearly with valve angle for valve angles from zero degrees up to a predetermined number of degrees.