Abstract: A lateral-thrust control device for a four-quadrant final-phase guidance control of a missile having lateral-thrust nozzles (10) communicating with a solid-fuel gas generator (13). Each of the nozzles has a valve member (22, 38), whose open and closed states are controlled by a common actuator (12, 30) which is rotatable and axially displaceable to select one nozzle to be supplied with gas from the gas generator while the other nozzles are closed according to the required flight mode. The actuator is configured such that each of the lateral-thrust nozzles (20) can be individually controlled to be active or inactive, intermittently, and independently of one another. In one embodiment, the actuator is a cylindrical piston and in another is a conical member.