In this paper the problem of guided missile flight with minimum normal acceleration is investigated. Obtaining an analytical result for the problem in its general form is very difficult. A constant normal acceleration policy is obtained which requires keeping the normal acceleration constant all the flight time and satisfying all the constraints. Computer programs are prepared and executed using real data to form some charts for different velocities and different missile initial conditions. Comparing the results using the above optimum policy, and the results solving the problem by using gradient technique shows that it gives a less normal acceleration. The results also showed a great improvement compered with the conventional methods of guidance.
Flight policy of guided missile with minimum normal acceleration
Flugrichtlinien fuer gesteuerte Flugkoerper mit minimaler Normalbeschleunigung
Proc. of the 1984 American Control Conf. ; 3 ; 1422-1426
1984
5 Seiten, 5 Bilder, 14 Quellen
Aufsatz (Konferenz)
Englisch
Minimum time flight policy of guided missile
Tema Archiv | 1984
|NTIS | 1970
GWLB - Gottfried Wilhelm Leibniz Bibliothek | 1959
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