missile is launched when the missile 10 starts to be launched the missile 10 caught by the sabots 110 by means of the position adjustment pin 140 proceeds together with the sabots 110 within the canister 20 overcoming the frictional force generated by a load in an axial direction between the travel lock bolt 170 and the travel lock bar 120 then the contact state between the travel lock bolt 170 and the travel lock bar 120 is released and accordingly the outer circumferential surface of the sabot body 111 is slid in a state of contacting with the inner surface of the canister 20 by virtue of the spring 160 and the spring seat 150 at the moment the missile 10 blasts off after being highly accelerated within the canister 20 the sabots 110 scatter in all directions by a restoration force of the compressed spring 160 as stated above the scope of the present invention is not limited to the above described specific embodiment of the present invention but can be modified suitably within the coverage of the claims for example without installing an travel lock bar 120 in the sabots the travel lock bolt can contact directly with the upper surface of the sabot so as to remove the clearance between the missile and the canister as so far described a lateral support device system of a canister launched missile in accordance with the present invention has the following advantages that is by installing sabots separably formed on the outer circumferential surface of the missile and the travel lock bolt.