抄録
The guidance force, which guides an aircraft on the desired trajectory, consists of two parts. One is the force necessary for programming motion and the other is the force to eliminate the guidance errors, which depends significantly on the magnitude of the guidance error correction gains, that is, guidance gains. In this paper, using small perturbation theory, the gains are computed as the functions of the parameters of the dynamics for the autopilot. Finally the simulation results show the effectiveness of the guidance gains computed in this paper.
