Rastgele arayıcı başlık gürültüleri ve hedef manevralarının güdüm performansı üzerine etkileri.

The aim of this thesis is to scrutinize the effects of challenging target maneuvers and distinctive random seeker noise on guidance performance. The guidance problem is formulated as a feedback control system and a homing loop is modeled via Matlab-Simulink software to simulate possible 3D engagement scenarios. In order to track maneuverable targets and derive the rates of LOS angles in azimuth and elevation planes, a couple of seeker models are presented. Moreover, blind flight phenomenon is investigated for gimbaled seeker models. Besides, prominent random seeker noise and error sources are mathematically modeled and introduced into the homing guidance loop. A target estimator is implemented to estimate the states of the maneuvering target, including target’s acceleration components. Augmented Proportional Navigation Guidance Law is mechanized to compute the required lateral acceleration components in azimuth and elevation planes of the line of sight frame. Furthermore, a new technique is proposed to deal with the blind flight predicament, which may be regarded as a contribution to the missile guidance literature. Finally, the resulting end-game plots of the pursuer and the evader for challenging guidance scenarios are presented. Multiple Monte Carlo simulations are carried out randomly to judge the performance of the overall guidance system based on a statistical approach. By doing so, the effects of target maneuver types, different engagement geometries, seeker models, random noise sources, target estimator models and guidance algorithms on overall guidance performance are compared. Overall guidance performances are assessed in terms of average miss distance values, hit ratios and average engagement times.M.S. - Master of Scienc