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

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2015

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İpek, Fahrettin Kağan

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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.

Subject Keywords

Guided missiles., Tactical missiles., Projectiles, Aerial., Lateral thrusters.

URI

http://etd.lib.metu.edu.tr/upload/12619056/index.pdf
https://hdl.handle.net/11511/24923

Collections

Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats

F. K. İpek, “Design, control, and guidance of a tactical missile with lateral thrusters,” M.S. - Master of Science, Middle East Technical University, 2015.