Design, control, and guidance of a tactical missile with lateral thrusters

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Tezin Türü: Yüksek Lisans

Tezin Yürütüldüğü Kurum: Orta Doğu Teknik Üniversitesi, Mühendislik Fakültesi, Elektrik ve Elektronik Mühendisliği Bölümü, Türkiye

Tezin Onay Tarihi: 2015

Öğrenci: FAHRETTİN KAĞAN İPEK

Danışman: MEHMET KEMAL LEBLEBİCİOĞLU

Özet:

Maneuverability is a key concept for tactical missiles. In this thesis different aerodynamic configurations of a tactical missile is investigated. Effect of fixed wing position on stability and agility is discussed at different phases of the flight. A secondary actuator, lateral thruster system, is introduced. This system employs reaction forces obtained by ejecting high velocity gases at desired times. Unlike aerodynamic fins or thrust vector controlling of the main engine, thruster system control effect is constant at all phases of the flight. This makes it an interesting actuator for low speed conditions when main engine is not vector controlled and aerodynamic fin effectiveness is weak. One peculiarity of the system is that it can only work in on-off fashion; hence thruster modulator is introduced in the controller design to mitigate the nonlinear behavior of the thrusters. Missile initial turnover maneuvers are studied in vertical ground launch and in horizontal airborne launch. Terminal phase guidance is also examined. These scenarios are modeled in a 6 DoF simulation environment and lateral thruster effect is discussed.