Abstract: A method of generating data outputs as instructed by a configuration file on a computer system for an aircraft includes processing, as instructed by one or more parameters of the configuration file, data from a first data source. In some embodiments, the first data source comprises either a sensor associated with the aircraft or an addressable memory. In some embodiments, the one or more parameters comprise instructions for using one or more certified functions. The method also includes outputting the processed data to at least one of the addressable memory, a display, and an external device.

Abstract: An automatic aircraft pitch axis flight stabilization system which does not require the use of a gyroscope is described. Stability signals are derived from an altitude signal responsive to atmospheric pressure. Means responsive to rate of change of altitude produces a vertical rate signal and means responsive to rate of change of vertical rate produces a vertical acceleration signal. The vertical speed signal is combined with a command signal which causes the aircraft to fly at constant altitude, at constant vertical speed, or to descend along a glide slope, and the vertical acceleration signal to produce a control signal which operates a means, such as a servomechanism for positioning the vertical control surfaces of the aircraft.