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.
Recommended Citation
S. N. Balakrishnan and D. T. Stansbery, "Approximate Analytical Guidance Schemes for Homing Missiles," Proceedings of the American Control Conference, 1994, Institute of Electrical and Electronics Engineers (IEEE), Jan 1994.
The definitive version is available at https://doi.org/10.1109/ACC.1994.752354
Meeting Name
American Control Conference, 1994
Department(s)
Mechanical and Aerospace Engineering
Keywords and Phrases
Approximate Analytical Guidance Schemes; Boundary-Value Problems; Closed Form Solutions; Control System Synthesis; Guidance Laws; Homing Missiles; Intercept Dynamics; Matrix Algebra; Missile Guidance; Modern Control Techniques; Optimal Control; State Transition Matrix; Two-Point Boundary Value Problem
Document Type
Article - Conference proceedings
Document Version
Final Version
File Type
text
Language(s)
English
Rights
© 1994 Institute of Electrical and Electronics Engineers (IEEE), All rights reserved.
Publication Date
01 Jan 1994
