Ballistic Flight and Control Simulation of Rkx200tj/Booster during Boost and Climb-Phases

The problem encountered while developing the RKX-200TJ/booster is the measurement of vehicle mass (center of gravity). The thrust line of the rocket booster does not coincide with the center of gravity can induce a pitch disturbance. By controlling the pitch parameter, the pitch disturbance phenomenon can be minimized. In this paper presents the flight performance and dynamics analysis and the design of the pitch and roll control system for RKX200TJ/booster during rocket boost and climb phase. The result indicates that the pitch disturbance can be reduced until 27% decrease whereas roll angle (�) can be damped at zero level (� = 0). Pitch angle (�) can be maintained at angle 5° for the climb phase. Although the one of moment arm case shows the static instability and uncontrollability during rocket boost phase, the control system can control the vehicle to further phase. This simulation is presented in X-Plane and Simulink. The PID controller is selected in the control system design.