Uyarlamalı Denetim Yöntemlerinin Sıvı Yakıtlı Roketlerde İtki Vektör Denetim Sistemlerine Uygulanması

Abstract

Thrust Vector Systems are used to control the angle or angular velocity of the thrust generated by engines in combat aircraft, spacecraft, or rocket systems. The process of enabling movement capability in Thrust Vector Systems through specific control methods is known as Thrust Vector Control. These control systems must effectively counteract disturbances and changes in system parameters resulting from environmental conditions. This thesis encompasses the results obtained from the utilization of Indirect and Direct Self-Tuning Model Reference and Proportional-Integral Control approaches in the control of Thrust Vector Systems. The control approaches mentioned have been utilized in two distinct methodologies. One methodology employs cascade control, which incorporates an inner speed loop and an outer position loop. The other methodology utilizes a single-loop position control strategy. Both control strategies have undergone rigorous testing through simulations and real-time experimentation. In simulations, the methods are subjected to various disturbances to assess their respective disturbance rejection capabilities, providing comprehensive insights into their comparative performances. The real-time application results obtained in this study reveal that both Indirect and Direct Self-Tuning Model Reference and Indirect Self-Tuning Proportional-Integral Control methods demonstrated satisfactory control performances. However, it's noteworthy that the Direct Self-Tuning Proportional-Integral Control approach, despite its promising performance in simulations, could not be successfully executed in real-time. Among all the application results, Indirect Self-Tuning Model Reference Control emerged as the most effective approach, showcasing superior performance.