An explicit closed-form formula of a discrete guidance law for a linear time-invariant, acceleration commanded, arbitrary-order missile and a linear, time-invariant arbitrary-order, maneuvering target is derived. The formula is given in terms of the missile and target transfer functions and responses to initial conditions. Examples are explicitly solved for zero-lag and a first-order missile. As an example, it is shown that the discrete proportional navigation ratio is higher than 3 and time varying in contrast to the continuous case.<>
Discrete optimal guidance for high-order missile and maneuvering target
IEEE Transactions on Aerospace and Electronic Systems ; 27 , 6 ; 870-872
01.11.1991
232934 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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