This paper presents the study results of stability and attitude control of the launch vehicle for the initial stage of the launch. Launch vehicle model is treated as a rigid body or a flexible body. To stabilize the attitude of the rigid body model, a PID control is used. The PID gains are obtained by the dominant pole design which is a PID automatic tuning method. To stabilize the attitude of the flexible body model, the gain stabilization is used with a PID controller. After selecting 21 nominal points as a function of velocity of the launch vehicle from zero to 370 m/sec, the PID gains is computed at the design nominal points. The other gains are obtained by interpolating with the gains which are taken at the nominal points. Simulations are performed about the two cases. One is that the launch vehicle have the pitch angle error at the initial launch state. The other is that the launch vehicle have the disturbance of the cross-wind during flight. The control performance is shown from the result of the simulation.
