Due to the importance of the flight time elapsed of a guided missile before impact, the minimum time flight policy is investigated in this paper. Using the maximum principle the well known results of bang-bang control policy is given but with a highly complicated costate equation. Some remarks are given about the behaviour of the optimal control policy. Three different numerical algorithms are described and applied to obtain a bang-bang control policy using real data for the missile. The first and second algorithms are based on the remarks obtained from the analytical results. The gradient technique is also used in obtaining the third algorithm. The effect of both the amplitude of the control and the allowable number of switches in the control on the miss distance are obtained. The relation between the target velocity and the final time is also investigated.
Minimum time flight policy of guided missile
Richtlinien fuer die minimale Flugzeit von gesteuerten Flugkoerpern
Proc. of the 1984 American Control Conf. ; 3 ; 1416-1421
1984
6 Seiten, 7 Bilder, 14 Quellen
Aufsatz (Konferenz)
Englisch
Flight policy of guided missile with minimum normal acceleration
Tema Archiv | 1984
|NTIS | 1970
GWLB - Gottfried Wilhelm Leibniz Bibliothek | 1959
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