Title :
Approximate analytical guidance schemes for homing missiles
Author :
Stansbery, Donald T. ; Balakrishnan, S.N.
Author_Institution :
Dept. of Mech. & Aerosp. Eng., Missouri Univ., Rolla, MO, USA
fDate :
29 June-1 July 1994
Abstract :
Closed form solutions for the guidance laws are developed using modern control techniques. The resulting two-point boundary value problem is solved through the use of the state transition matrix of the intercept dynamics. Results are presented in terms of a design parameter.
Keywords :
boundary-value problems; control system synthesis; matrix algebra; missile guidance; optimal control; approximate analytical guidance schemes; closed form solutions; guidance laws; homing missiles; intercept dynamics; modern control techniques; state transition matrix; two-point boundary value problem; Acceleration; Aerodynamics; Aerospace engineering; Boundary value problems; Closed-form solution; Differential equations; Missiles; Modems; Navigation; State-space methods;
Conference_Titel :
American Control Conference, 1994
Print_ISBN :
0-7803-1783-1
DOI :
10.1109/ACC.1994.752354
