A 6DOF nonlinear simulation of a satellite missile

Supervisor: Assoc. Prof. Dr. Sohayb ABDULKERIM September 2021 79 pages Recently, it has been witnessed a significant increase in the number of controlled missiles for various purposes specifically for launching satellites. To validate the performance of an air vehicle, and to carry out the designing process of the controller and stabilizer, missiles need to be perfectly modeled and simulated. The literature is very meager in the simulation of missiles using 6DOF model. Therefore, this project simulates the missile using 6DOF by SIMULINK. To perform the simulation, dynamical equations using newton's second law were derived. The resulted dynamical equations, a set of nonlinear time-variant and coupled differential equations, were simulated using MATLAB without the need for a linearization process. The thrust vector and inertia tensor were defined using tabular data which functions on time, while the aerodynamics and stability derivatives were also determined by tables that function to Mach's number, angle of attack, and slide slip angles. The simulation process was validated by comparing the resulted trajectory for a case study with a similar one found in the literature. The comparison showed a good agreement. The resulted simulator allowed to design and tuning of PID controller using the Ziegler Nichols method. This approach showed high flexibility and efficiency in finding missile trajectory and designing controller and stabilizer.