In order to provide an accurate time-to-go to the proportional navigation guidance,the calculation method of time-to-go was studied based on the missile-target relative motion model.The time-to-go caculation model was established according to the criterion of the missle’s leading angle converging to zero.For the special case that the navigation gain was three,the first and second order solutions of the model were obtained by using the analytical method,and the accuracy of these solutions were evaluated by simulation analysis.The approximate solution of time-to-go for the other navigation gain was obtained by using the polynomial fitting method.The simulation results show that the fifth order polynomial fitting has better precision.The time-to-go algorithm was applied to intercepting different types of tagets with proportion navigation guidance.The results show that the algorithm can effectively intercept the constant speed target and the constant acceleration target,as long as the missile’s velecity is large enough.
Key words
missile /
time-to-go /
proportional navigation /
polynomial fitting /
target interception
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References
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Footnotes
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