Akademik Veri Yönetim Sistemi
Journal of Engineering Sciences and Design, cilt.13, sa.4, ss.1-10, 2025 (Hakemli Dergi)
In this study, the trajectory of a high-power rocket was obtained from a model created using MATLAB/Simulink. The nonlinear aerodynamic and thrust systems and the variable mass due to fuel consumption are the basic components of this model. The model has been validated by the data collected during the launch of a real rocket. In the case of a need to add new subsystems, the model provides easy integration through its modular and flexible structure.
The model has been verified by comparing the simulation results for the altitude and orbit of the rocket with the values of real rocket launch data, as well as through the Rocketpy open-source trajectory prediction tool. In order to discuss the effect of mass effect on flight performance, different mass scenarios were performed. Additionally, the velocity of the rocket, the forces acting on the rocket during flight, and its position over time from launch to landing are presented.