Analytic Solution for Nonlinear Impact-Angle Guidance Law with Time-Varying Thrust

This paper presents an impact-angle guidance law of unmanned aerial vehicles (UAVs) with time-varying thrust in a boosting phase. Most current research on assumes that UAV speed is constant terms controlled thrust. However, the and acceleration phase keep changing because Environmental factors manufacturing process error may prohibit accurately predicting vehicle-thrust profiles. We propose nonlinear by analytically solving second-order dynamics coefficients. The proposed analytic solution enables one to update gains according initial states so desired impact angle met while miss-distance reduced. prove finite-time convergence Lyapunov stability theory. Various simulation studies are performed verify law.