Akademik Veri Yönetim Sistemi
Tezin Türü: Yüksek Lisans
Tezin Yürütüldüğü Kurum: Orta Doğu Teknik Üniversitesi, Mühendislik Fakültesi, Havacılık ve Uzay Mühendisliği Bölümü, Türkiye
Tezin Onay Tarihi: 2018
Öğrenci: BARAN DİLAN ÖZDİL
Danışman: ALİ TÜRKER KUTAY
Özet:In this thesis, estimation of an optimal trajectory for a tactical missile is studied. Missile guidance algorithm is developed to achieve a desired mission goal according to some performance criteria and the imposed constraints. Guidance algorithms may include trajectory optimization to shape the whole trajectory in an optimal way, so that the desired performance needs such as maximum impact velocity, minimum time-of-flight or specific crossing angles can be satisfied. By performing missile path planning, an optimized trajectory helps to achieve missile mission with required performance criteria. In order to optimize missile trajectory, various optimization algorithms can be utilized. In this thesis, Genetic Algorithm will be focused on mainly. Efficiency of gradient based optimization algorithms are also studied. Waypoints that missile must visit are taken as control parameters of the algorithm. A hypothetical missile is modeled for the analyzes. Trajectory optimization is perfomed based on two cases. The first one is aimed to reach an air target with maximum velocity and minimum flight time. In the second one, achieving a desired impact angle with maximum velocity against a stationary ground target is the purpose. Results are compared with reference models which uses conventional guidance algorithms. Optimization algorithms are run offline initially and after that with the insights obtained, lookup tables are created for real time use in missile guidance. Scenario parameters are the inputs of lookup tables, and by interpolating the waypoints corresponding to these parameters, waypoints that the missile must visit can be obtained. This allows the missile trajectory to be improved without running the optimization algorithm in each scenario.