The work presented in this paper is a cose study of a hardware non-linear avionic fuel control system. Initially a system block diagram is formed using the manufacturer's estimates of the nominal parameter values. Some of the parameters have to be optimized using the digital computer to satisfy certain performance criteria. By using these optimum values an analytic linear transfer function is derived and used to calculate the system reference response. Various other responses obtained from the digital simulation using different numerical integration methods are compared with the reference response to determine the optimum integration method. The chosen integration method is then used to determine an optimum discretization interval. Common non-linearities which may exist in such servosystems are then introduced into the digital model in order to study their effects on the system transient response.
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