Testing of an aircraft pressure control system may be performed without
use of an altitude chamber. Aircraft cabin configuration date may be
modeled and used, along with high resolution positional feedback from a
simulated valve, to produce a high resolution electrical signal that may
represent a simulated cabin pressure. A voltage-to-pressure transducer
may convert the electrical signal to a pneumatic signal. The pneumatic
signal may be employed to operate a cabin-pressure controller under test.
The controller may operate an outflow valve actuator and an attached
potentiometer. The potentiometer may produce a feedback signal and
closed-loop testing of the aircraft pressure control system may thus be
performed. The outflow valve actuator may be operated without being
attached to an outflow valve because a simulated aerodynamic load may be
applied to the actuator.