An H∞ Design Approach for a PID Automatic Flight Control System of a Launch Vehicle
The paper presents a design methodology for the automatic flight control of a launch vehicle. In the proposed approach the controller has a PID (Proportional-Integral-Derivative) structure but its gains are determined solving an H∞ norm minimization problem of the mapping from the atmospheric disturbances to the control amplitude and to the angle of attack of the launcher. The design methodology is illustrated by numerical examples in which both time responses and stability robustness properties of the optimal PID controller are analyzed.
A. M. Stoica and M. R. Stefanescu, "An H∞ Design Approach for a PID Automatic Flight Control System of a Launch Vehicle", Applied Mechanics and Materials, Vol. 859, pp. 116-123, 2017