Proportional-Integral-Derivative Controller in Proportional Navigation Guidance
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In this thesis, a Proportional-Integral-Derivative (PID) guidance scheme is discussed to improve the miss distance accuracy and the finite time stability problem in the Proportional Navigation Guidance (PNG). The primary goal of this study is to design the PID guidance that can accurately intercept the fast maneuvering target. The PID guidance is the extended version of the PNG with the integral and derivative terms in parallel. For the understanding of the conventional PNG model, the two-dimensional (2-D) engagement model of the missile and target is analyzed. Two characteristics are found in the PNG model: (1) its’ stability is kept in the finite time but becomes unstable at the vicinity of the interception and (2) the Line-of-sight angle rate (LOSR) increases as the target acceleration magnitude increases. To regulate the LOSR, the PID guidance is derived based on the servomechanism theory. The PID guidance model replaces the proportional gain of the conventional PNG model by the PID controller. A PID controller design using the numerical method through the iterative simulation is presented. For the various missile and target initial geometries, the capture region of the PID guidance is evaluated and compared with the conventional PNG model. In the end, the PID guidance model shows the improved miss distance accuracy, the extended stable time, and extended capture region when compared with the PNG model.
Kim, Byungjun (2016). Proportional-Integral-Derivative Controller in Proportional Navigation Guidance. Master's thesis, Texas A & M University. Available electronically from