The input and the response of an angular rata gyroscopic system differ by an error signal, which la a function of the dynamic characteristics of the gyroscope assembly, the feedback control loop, and the mathematical properties of the inputs. The output and the input are not related in a linear manner, unless the error signal is negligible. The functional relationship of response error to the feedback system structure and the input rates was systematically explored for Air force HIG type gyroscopes employing linear types of feedback.
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