Instruments and Systems: Monitoring, Control, and Diagnostics Annotation << Back Synthesis of an Optimal Missile Homing System Using the Proportional Guidance Method DO QUANG THONG In practice, missile homing systems (MHS) with the use of the proportional guidance method (PGM) are widely used. In it, in order to destroy targets at different altitudes, a normal acceleration stabilization system (NASS) is used. In the synthesis of MHS, it is necessary to synthesize NASS. Here there are two approaches: the first approach: fi rst synthesize the NASS, then synthesize the MHS; the second: synthesize both the NASS and the MHS. In this paper, we consider the methods of MHS synthesis according to the first approach. In this paper, we propose methods for the synthesis of MHS with a minimum total error and a minimum time of the NASS transition process. To simplify the synthesis, we adopt the linear model of the NASS and try to use the commands of the Control System Toolbox (Matlab) package as much as possible. Next, the influence of gravity, the longitudinal acceleration of missiles, and the blinding of the homing head on the accuracy of the synthesized SSR is investigated. The simulation results show that gravity, the longitudinal acceleration of the missiles, and the blinding of the homing head have little effect on the accuracy of the synthesized MHS. Keywords: System synthesis, missile, missile homing system, proportional guidance method. DOI: 10.25791/pribor.8.2021.1282 Pp. 17-24.