STABILIZATION CONTROL CIRCUIT FOR VERTICAL POSITION IN AN INERTIAL NAVIGATOR

Vertical velocity and vertical position of an aircraft are derived from the vertical acceleration and a measurement of altitude based on barometric pressure. An acceleration correction signal and a velocity correction signal are derived from an altitude error signal and the rate of change of altitude based on the barometric altimeter. The acceleration correction signal and velocity correction signal functions are such that the acceleration correction signal and the velocity correction signal are responsive to rapid climbs and dives of the aircraft.