Closed Loop Optimal Guidance Control For Aircraft In Ascent Phase

This paper provides an optimal guidance method that meets 6 terminal constraints of velocity and position. For the aircraft whose thrust direction of engine is controllable, we derive the optimal control problem of its ascending trajectory. The key is to solve a kind of forward and backward differential equations (FBDEs), which is with six variables, and the initial and terminal values of the backward variable are free and those values of the backward variables are fixed herein. The solvability of FBDEs is then transformed into a zero finding problem. The main contribution is to reduce the zero-finding problem with six variables to one with five variables and give some numerical algorithms including damped Newton method and genetic algorithm.