DocumentCode
335428
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
Volume
2
fYear
1994
fDate
29 June-1 July 1994
Firstpage
1665
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;
fLanguage
English
Publisher
ieee
Conference_Titel
American Control Conference, 1994
Print_ISBN
0-7803-1783-1
Type
conf
DOI
10.1109/ACC.1994.752354
Filename
752354
Link To Document