Comparative analysis of autopilot architectures for air defense missiles

Date

2024-9-05

Author

Çelikbudak Altıntaş, Merve

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High precision control is essential during the ascent phase of surface-to-air defense missiles, due to the need for sudden attitude maneuvers to align with the tracking system. In this thesis, a comprehensive 6-DOF nonlinear missile model is developed to simulate the behavior of a tactical surface-to-air missile. Various nonlinear autopilot designs, including Nonlinear Active Disturbance Rejection Control (ADRC) and PID controllers, are implemented and compared under different architectural frameworks. These designs have been thoroughly examined and compared not only in terms of control performance but also regarding energy consumption. To further explore the guidance accuracy, an acceleration controller is implemented and integrated as a third loop in a cascaded configuration with attitude controllers. This additional control loop is analyzed using PNG across selected autopilot architectures. The comparison focuses on their performance when engaging maneuvering targets, taking into account the adaptability and responsiveness of different control strategies under dynamic conditions. In addition to performance evaluations, the study incorporated detailed models of disturbance effects and delays, enabling a thorough comparison of the various autopilot architectures. Specifically, control actuation system delays, and sensor measurement delays are considered for assessing how different controllers handle real-world system challenges. These analyses provide a deeper understanding of the trade-offs between response speed, system stability, and guidance performance, particularly when comparing the conventional PID control strategies with second-order nonlinear ADRC techniques. This thesis contributes valuable insights to the missile control systems, focusing on stability, precision, and energy consumption. It also emphasizes the importance of disturbance rejection, and delay robustness in enhancing the overall performance, and reliability of missile guidance systems.

Subject Keywords

Nonlinear active disturbance rejection control (ADRC), Proportional-integral-derivative (PID), Extended state observer (ESO), Tracking differentiator (TD), Nonlinear state error feedback (NLSEF), Air defense missile, Autopilot system, Disturbance rejection

URI

https://hdl.handle.net/11511/111277

Collections

Graduate School of Natural and Applied Sciences, Thesis