Abstract:

In view of nonlinearity of targetmissile relative kinematic equations in threedimensional space and multiple constraints imposed in the midcourse guidance phase, the Gauss pseudospectral method is adopted for the design of the optimal midcourse guidance law with multiple constraints. And the secondorder dynamics of the missile autopilot is taken into account. The constraints include handover distance, line-of-sight (LOS) angles, LOS angular rates, and acceleration commands. The performance criterion is the integral of the squared control input multiplied by reciprocal of time-to-go to the power of n. The research results indicate that when time-varying weight coefficient is introduced into the performance criterion, in spite of the increasing fuel usage, the handover conditions are fulfilled while the acceleration commands could converge to zero, which contributes to the smooth transition from midcourse guidance to terminal guidance.