GUIDANCE CONTROL SYSTEM AND METHOD FOR TVC GUIDED MISSILE

摘要

PROBLEM TO BE SOLVED: To obtain a guided controller for a TVC guided missile capable of making it fly without fail at a designated attitude with practically enough accuracy in the TVC guided missile for which a rapid and large change in the attitude is required. ;SOLUTION: In order to realize a target direction n to target points to be passed at initial and middle stages, an attitude vector f and a flying direction m at each target position, there are provided a device 1 for calculating an attitude vector command value CfA at the present time, a device 1B for generating an attitude vector command value CfB every hour, a device 2 for selecting one of the attitude vector command values, and a device 3 for calculating an actuator command value CA for making an actual attitude vector with each command value, whereby the attitude of a TVC guided missile is taken so as to advance along an orbit suitable for the missile to ass through the target point with a designated attitude and in a flying direction, and an attitude vector command value every hours is altered to improve operation adaptability.;COPYRIGHT: (C)1998,JPO