The TurboRocket Trajectory Determination System

摘要

The TurboRocket trajectory determination system incorporates a comprehensive and rigorous treatment of the aerodynamics of the rocket, the engine thrust variation with altitude, and the vehicle weight change over time. The mathematical model was implemented in MATLAB-Simulink with the numeric integration based on a Runge-Kutta-RK4 solver, returning the vehicle acceleration, velocity, and altitude at fixed time intervals. Results from the application of the software show that a 300 N maximum thrust turbojet engine operating at full power for 20 seconds, could launch a 15 kg maximum take-off weight vehicle to the desired altitude of 3,000 m AGL.