S.N. Finogenov, M.E. Tsarkov, V. Abo Hamra

It is offered an algorithm of the optimal nonlinear trajectory control of the flying vehicle direction, which provides a high quality of the self-guidance and which is different from the famous ones by the functional change of the value of the coefficient of the pass of the regulator, negative feedback by the normal acceleration of the missile, using the correcting signal as a mark of the normal acceleration of the target. An offered algorithm will admit to provide a high quality of the self-guidance and an interception of the maneuvering targets as well as of the intensive maneuvering.