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In current aerospace research, redundant digital computers, operating asynchronously for low cost and high reliability, are being considered for the control of high-performance aircraft. Asynchronous sampling in the control loops leads to inherent errors even under normal, failure-free operation. Such errors are defined and characterized by a useful approximation, and state equations are derived for their description in a dual-redundant, closed-loop system. A covariance analysis of the inherent errors is developed. The state equations and the covariance analysis are applied to a simulation based on a digitized version of the U. S. Air Force A-7D pitch-axis control system, with the aid of a specially-prepared, packaged computer program.
Date of Publication: Feb 1977