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.

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.

Full Text Link

Share

 
COinS