Explicit, closed form formula of a discrete optimal guidance law for a linear, time-invariant acceleration commanded and arbitrary order missile and a linear, time-invariant, arbitrary order maneuvering target is derived. The formula is given in terms of the missile's and target's transfer functions and responses to initial conditions. Examples are explicitly solved for zero lag and for 1st order missiles. It is shown that the discrete proportional navigation ratio is higher and time varying rather than equal to 3 as in the continuous case.
Discrete Optimal Guidance for High Order Missile and Maneuvering Target
1990
5 pages
Report
No indication
English
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