Dynamic characteristics analysis of missile in ballistic flight

In this research, the nonlinear model of a ballistic missile has been linearized and validated. The nonlinear equation of motion for the flight dynamics of the missile has been used for modeling the missile. The transfer function and model reduction are derived. Dynamic stability analysis for longitudinal and lateral-directional motion has been made at some operating points throughout the flight. The effect of different phases and velocities of the flight has been analyzed by its pole locations and frequency response. It was found that the missile’s short period, Dutch roll, and roll subsidence mode are stable. The result of this work can be used for designing a robust autopilot controller that meets the stability and performance requirements of the plant throughout the whole flight envelope.