Automatic guidance procedure for missile - avoids interaction between pitch roll and yaw control systems for symmetrically controlled missiles.

摘要

The procedure relates to the problem of interaction between control of roll and yaw when changes are made to the forward flight of the missile. Commands for transverse control of the missile coming from the guidance system are converted into commands related to a standardised reference plane relating to the axis of flight the missile which reduces to rotation of the missile by an angle about its axis of flight. The acceleration commands are calculated separately from the stabilised reference plane and are converted to the axes of roll and yaw. ADVANTAGE -Improved automatic control of symmetrical missiles in flight.