Approximate Analytical Guidance Schemes for Homing Missiles

S. N. Balakrishnan; Donald T. Stansbery

doi:10.1109/ACC.1994.752354

Approximate Analytical Guidance Schemes for Homing Missiles

S. N. Balakrishnan
, Donald T. Stansbery

Missouri University of Science and Technology

Research output: Contribution to journal › Article › peer-review

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.

Original language	American English
Journal	Proceedings of the American Control Conference, 1994
DOIs	https://doi.org/10.1109/ACC.1994.752354
State	Published - Jan 1 1994

Keywords

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

Disciplines

Aerospace Engineering
Mechanical Engineering

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Approximate Analytical Guidance Schemes for Homing MissilesFinal published version, 367 KBLicense: Unspecified

Cite this

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title = "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.",

keywords = "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",

author = "Balakrishnan, \{S. N.\} and Stansbery, \{Donald T.\}",

year = "1994",

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doi = "10.1109/ACC.1994.752354",

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journal = "Proceedings of the American Control Conference, 1994",

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AU - Stansbery, Donald T.

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N2 - 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.

AB - 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.

KW - Approximate Analytical Guidance Schemes

KW - Boundary-Value Problems

KW - Closed Form Solutions

KW - Control System Synthesis

KW - Guidance Laws

KW - Homing Missiles

KW - Intercept Dynamics

KW - Matrix Algebra

KW - Missile Guidance

KW - Modern Control Techniques

KW - Optimal Control

KW - State Transition Matrix

KW - Two-Point Boundary Value Problem

UR - https://scholarsmine.mst.edu/mec_aereng_facwork/3407

U2 - 10.1109/ACC.1994.752354

DO - 10.1109/ACC.1994.752354

M3 - Article

JO - Proceedings of the American Control Conference, 1994

JF - Proceedings of the American Control Conference, 1994

ER -

Approximate Analytical Guidance Schemes for Homing Missiles

Abstract

Keywords

Disciplines

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