Approximate Analytical Guidance Schemes for Homing Missiles
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. The results of comparison with other guidance laws will be presented at the conference (for lack of space).
Recommended Citation
D. T. Stansbery and S. N. Balakrishnan, "Approximate Analytical Guidance Schemes for Homing Missiles," Proceedings of the American Control Conference, vol. 2, pp. 1665 - 1669, Dec 1994.
Department(s)
Mechanical and Aerospace Engineering
International Standard Serial Number (ISSN)
0743-1619
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2024 The Authors, All rights reserved.
Publication Date
01 Dec 1994
