Modeling and Simulation of Pre-Apogee Trajectories for Low Altitude Rockets

The objective of this study is develop a mathematical model of a rocket's trajectory during flight, a fundamental aspect of sounding rocket design and performance analysis. To this end, the equations of motion of the rocket are integrated using the fourth-order Runge-Kutta method to simulate a set of rocket parameters. In this context, the variation of altitude, velocity, acceleration, and pitch angle values of the rocket with time during flight are investigated. The accuracy of the numerical results assessed by comparing them to real flight data and open source software. The research highlights the significance of mathematical modeling and simulation in design and optimization of rockets.