A Nonovershooting Pitch-Angle Regulator for Aircraft with Conventional Aerodynamic Configuration

The problem of designing a nonovershooting controller for general high-order linear time-invariant plants is still open. In this paper, we propose a new technique to design nonovershooting pitch-angle regulator for conventional aircraft based on the forth-order model of longitudinal motion. The regulator is composed of the error-feedback and the feed forward control terms. Two forms of the regulator are presented which apply to the state-feedback and the output feedback cases, respectively. Simulation examples are given to show the effectiveness of the regulator.