Design of the Scheme Flight Trajectory Command for the Tactical Missile

Abstract

For the case of the scheme trajectory command design for the tactical missile, the longitudinal and lateral commands and the compound controller of the attitude and height were designed. In the launch segment, four kinds of heading angle commands were presented adopting the arc method and reduction law. In the variable height flight segment, two kinds of height commands were gained by using the parabolic and exponential function. Considering the earth curvature, the formula of the great circle course and distance was gotten applying spherical triangle solution method, and the flight command along the route dot in the lateral plane was obtained. The simulation results show that the designed scheme trajectory commands are feasible and effectively.