Guidance consists of directing missile to predetermined point in space and is subdivided into navigation, computation, and control; inertially guided missile systems can be divided into 2 classes, depending upon type of guidance equations used to define error signals to drive control systems, explicit and delta guidance equations; one method of simplifying mechanization is to decrease rigor of solution of navigation and guidance problems; major sources of error are inertial measurement errors, equation and computation errors, control system errors, gravitational anomalies, and free-flight dispersion errors; guidance and system accuracy.
Guidance concepts for tactical missiles
Sperry Eng Rev
Sperry Engineering Review ; 17 , n 1
1964
6 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Coherent active seeker guidance concepts vor tactical missiles
Tema Archive | 1978
|Guidance and control of tactical missiles
TIBKAT | 1972
|Guidance and Control of Tactical Missiles
NTIS | 1972
|Guidance Methods for Tactical and Strategic Missiles
NTIS | 1990
|