The book examines the movement of missiles near the center of mass of controlled, rotating and stabilized in roll, taking into account aerodynamic, hardware and inertial cross-links. proposed structure of aerodynamic cross-links for such missiles is based on symmetry of their configurations. The dependencies of the components of aerodynamic force and moment on the angles of attack, sliding and angles of deflection of the controls are described by Taylor and Fourier rows, which, on the one hand, greatly simplifies the analysis of the effect of non-linearities and cross-links on the aerodynamic characteristics of missiles of various layouts with asymmetric air flow, on the other hand, allows the use of electronic digital computers for this purpose. Cross-links arising in separate channels of aircraft missile control system are considered.