Autopilot Implementation Synthesis via Processor-in-Loop Test
Abdelaty, B., Ouda, A., Elhalwagy, Y., Elnashar, G. (2017). Autopilot Implementation Synthesis via Processor-in-Loop Test. EKB Journal Management System, 17(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017), 1-11. doi: 10.21608/asat.2017.22784
Bahaaeldin Gamal Abdelaty; Ahmed Nasr Ouda; Yehia Zakaria Elhalwagy; Gamal Ahmed Elnashar. "Autopilot Implementation Synthesis via Processor-in-Loop Test". EKB Journal Management System, 17, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017, 2017, 1-11. doi: 10.21608/asat.2017.22784
Abdelaty, B., Ouda, A., Elhalwagy, Y., Elnashar, G. (2017). 'Autopilot Implementation Synthesis via Processor-in-Loop Test', EKB Journal Management System, 17(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017), pp. 1-11. doi: 10.21608/asat.2017.22784
Abdelaty, B., Ouda, A., Elhalwagy, Y., Elnashar, G. Autopilot Implementation Synthesis via Processor-in-Loop Test. EKB Journal Management System, 2017; 17(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017): 1-11. doi: 10.21608/asat.2017.22784

Autopilot Implementation Synthesis via Processor-in-Loop Test

International Conference on Aerospace Sciences and Aviation Technology
Article 80, Volume 17, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017, April 2017, Page 1-11  XML PDF (1.14 MB)
Document Type: Original Article
DOI: 10.21608/asat.2017.22784
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Authors
Bahaaeldin Gamal Abdelaty1; Ahmed Nasr Ouda1; Yehia Zakaria Elhalwagy2; Gamal Ahmed Elnashar2
1Technical Research Center, Egyptian Armed Force, Egypt.
2Military Technical College, Egyptian Armed Force, Egypt.
Abstract
Abstract: This paper presents design and implementation of 2DOF PID autopilot capable of dealing with the issue related to the missile aging, uncertainty in aerodynamic coefficient calculations, and different disturbance sources that affects the missile tactical specifications. 2DOF PID autopilot is carried out to achieve both control objective of follow reference signal and system robustness, which better than traditional PID. This paper presents redesign a 2DOF PID appropriate autopilot capable of dealing with the issue related to the missile aging, uncertainty in aerodynamic coefficient calculations, different disturbance sources and thrust degradation that affects the missile tactical specifications, which carried out with linearized mathematical model of actuating system and missile airframe and nonlinear flight simulation model under MATLAB environment. The overall block diagram of the underlying missile system have to be presented with mathematical model of the linearized underlying missile airframe and actuating system. The 2DOF PID autopilot has to be evaluated to clarify the merits and demerits of it and implemented based on embedded raspberry pi system. At the end, processor-in-loop experimental test is used to validate the proposed digital autopilot performance, which is correctly described on embedded system and achieved the required system response more than the conventional one with accepted flight path and minimum miss-distance.
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