Optimal guidance laws for missiles with second order characteristics
Abstract
A mathematical model with second order characteristics was employed to define optimal intercept guidance laws. The minimum control energy consumption was taken as the performance index, resulting in a definition of two separate cases for the terminal state: a zero terminal miss distance and an outofcontrol intercepting curved surface. The Laplace transformation was used to solve the conjugate state equations and the state equations. Intercept guidance laws were formulated and require an input of either the terminal time or the lead time. Correctional of the sightline rotation. Attention was also given to optimal guidance control laws for the proper frequency of a missile approaching infinity, i.e., an ideal particle.
 Publication:

Acta Aeronautica et Astronautica Sinica
 Pub Date:
 December 1982
 Bibcode:
 1982AcAAS...3...71Z
 Keywords:

 Energy Consumption;
 Interception;
 Miss Distance;
 Missile Control;
 Optimal Control;
 Acceleration (Physics);
 Angular Acceleration;
 Equations Of State;
 Laplace Transformation;
 Mathematical Models;
 Terminal Guidance;
 Space Communications, Spacecraft Communications, Command and Tracking