OPTIMAL AIRCRAFT MANEUVERS AGAINST TWO PROPORTIONAL NAVIGATION GUIDED MISSILES

Optimal aircraft maneuvers against two missiles are studied. Our former studies against multiple missiles were conducted by employing massive simulations. In this paper, the problem is formulated as a nonlinear optimal control problem and solved by the steepest ascent method. In order to maximize the miss distance against two missiles simultaneously, a special type of criterion function is employed by introducing a window function. Some examples obtained by our method show the reasonable optimal controls of the aircraft, and verify the validity of our method. Our method will be applied to pursuit-evasion and collision avoidance problems with multiple vehicles.