In this thesis

the technique of improving the precision of rocket-projectile by controlling trajectory error has been investigated. After building up controllable trajectory dynamics equation

control logic of lateral push vector motor ignition is established. A number of pulse motors are located on the muzzle of the rocket-projectile

and can provide a set of constant correct forces in order to improve the precision of rocket-projectile. In simulation example contrast

the powered end velocity and wing are considered to obey normal distribution

and the result indicates that the circular error probable is reduced 11. The feasibility of the method about lateral push vector motor firing control logic has been proved.