The patent application relates to an electronic guidance system which when provided with a set of target position coordinates prior to launch, calculates the missile position and velocity in an inertially fixed coordinate system during flight. All inertial coordinate system variables are defined by a three axis orthorganal coordinate system centered on the target position. This guidance system functions without an active roll control by continuously pointing the velocity vector of the missile towards the target position. (Author)
An Inertial Guidance System for Vertically Launched Missiles Without Roll Control
1978
27 pages
Report
Keine Angabe
Englisch
An Optimal Composite Guidance Strategy For Vertically Launched Anti-Skimmer RF Missiles
British Library Conference Proceedings | 1998
|Guidance systems advance in air-launched missiles
Tema Archiv | 1989
|