Development of flight control system for 2D differential geometric guidance and control problem

Purpose - The paper aims to provide further study on the development and analysis of flight control system for two-dimensional (2D) differential geometric (DG) guidance and control system based on the application of a set-point weighting proportional-integral-derivative (PID) controller. Design/methodology/approach - The commanded angle-of-attack is developed in the time domain using the classical differential geometry theory. Then, a set-point weighting PID controller is introduced to develop a flight control system so as to form the 2D DG guidance and control system, and the gains of the PID controller are determined by the Ziegler-Nichols method as well as the Routh-Hurwitz stability criterion. Finally, the classical frequency method is utilized to study the relative stability and robustness of the designed flight control system. Findings - The results demonstrate that the designed controller yields a fast responding and stable system which is robust to the high frequency parameters variation. Moreover, the DG guidance law is viable and effective in a realistic missile defense engagement. Originality/value - This paper provides a novel approach on the development of DG guidance and control system associated with its stability analysis.