Nonlinear Dynamics Modelling and Free-Launch Simulation of a Flying-Vehicle

Guided systems’ development always requires several subsystems laboratory and real tests during the Research and Development (R&D) phase. Since conducting real flight test is limited and expensive for the purpose of guided system development and production. Researchers and developers resort to adopting verified and valid dynamic models, that enables them to complete the development and research processes in a more logical and less costly manner. In current paper, a nonlinear 6-DOF mathematical model for a subsonic flying vehicle dynamics is developed, simulated, and validated with referenced data (Velocity, Range, and Normal Acceleration). The flying vehicle body configuration through this study is symmetrical around its vertical plane and initially impulse trusted during its boost phase. The aerodynamic coefficients of the flying body are developed using Missile DATCOM and formed in look-up tables in the Simulink-Model. The entire flying body’s semi-empirical aerodynamics’ model is comprehensively described based on (Mach Number, Angle of Attack and Side Slip Angle). The model is simulated under certain flight conditions using the AeroSim Blockset nonlinear equations which are solved by the Runga-Kutta method (ODE) using MATLAB/Simulink.