Pitch Mode Control System Design of Guided Missile
Muhammad A. R Yass1, Mohammed Wajeeh Ameen2
1Dr. Muhammad A. R Yass, Assistant Professor, Department of Electromechanical Engineering, University of Technology, Baghdad 00964, Iraq, India.
2Mohammed Wajeeh Ameen, MSc., Department of Computer Techs. Engineering, Dijlah University College, Baghdad 00964, Iraq, India.
Manuscript received on August 20, 2017. | Revised Manuscript received on August 28, 2017. | Manuscript published on September 05, 2017. | PP: 26-34 | Volume-7 Issue-4, September 2017. | Retrieval Number: C3035077317/2017©BEIESP
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©The Authors. Published By: Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/

Abstract: In this paper, the analysis of non-homogenous longitudinal equation of motion for transport Airplane in pitch mode to estimate and calculate the performance of the dynamic motion and Transfer function in pitch mode. The pitch feedback control system diagram with actuator Design to calculate the behavior using time response method for different gain values (K) and Different Gyro sensitivity values (GR) to obtain the best stability, peak value and time response. The results shows that the best stability and control behavior achieved when K=1.41 and GR= 1.19.
Keywords: Control system, stability, aerodynamic.