Linear analysis of zero-lift pitching moment coefficient and gravity effects on missile autopilots

The most of the studies on disturbance rejection are covered with robust control methods, where this paper suggests a narrowed but a more simplified linear model based technique to assess the robustness of the controllers. In this paper presented, the problems originated from the disturbances are aimed to be obtained as far in advance as possible. The method used in this work reduces the iterative fine tuning time course between the non-linear simulation and the linear model;hence it enhances the authority over the design process and the designer's comprehension of the true linear model.