AIR-TO-AIR MISSILE GUIDANCE FOR NONMANEUVERABLE TARGET INTERCEPTION AT MAXIMUM DISTANCE

Two methods implementing high targeting trajectories of the air-to-air missile are developed. Computations of optimal flight trajectories at the given constraints are implemented using the direct method of optimization of nonlinear dynamic systems, namely, the collocation method, in order to analyze the guidance methods by the criterion of maximum distance of the missile launch. The trajectories obtained using the developed guidance methods are compared to the optimal trajectories. Recommendations for the choice of the guidance method as well as for the settings of the method parameters depending on the missile launch conditions are given.