This study, focuses to simulate separation process in different launchers numerically using fluent software. In present case, an aerodynamic equations coupled with rigid body dynamics, because of resultant aerodynamic forces and gravity, is developed to simulate the detachment motion of strap-on boosters. As can be seen from the results, by changing in booster elongation and changing in operation mach number and the effect of expansion waves from the core rocket and the booster, separation trajectory follows safe separation or collision between core and booster.


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