Design of a Three-Loop Attitude Control Autopilot for Quasi-Attack Angle of Static Unstable Guided Rockets

This paper proposes a design method for a three-loop attitude control autopilot for the quasi-attack angle of statically unstable guided rockets. Based on the analytical relationship between control system gain and open-loop cutoff frequency, as well as the damping ratio and poles and zeros, the design method optimizes the desired relative stability margin of the control system. By iterating the optimization calculations with pole placement strategies, it quickly obtains the relevant gain coefficients under the constraint of the desired stability margin. Simulations under various statically unstable conditions show that the designed autopilot can ensure the performance stability of the control system and has significant engineering application value.