Modeling and Simulation of Aerobee-150A Sounding Rocket

摘要

This paper presents modeling and simulation studies for an Aerobee-150A sounding rocket. The model consists of 6 degree of freedom motion model accompanied with various subsystems such as yo-yo despin model, cold gas thruster model, and recovery system model. A pulse-width pulse-frequency (PWPF) modulator is employed for attitude control. A large portion of the model parameters are obtained from the publicly shared NASA reports. Simulation results show that the performance parameters (e.g. burn-out velocity and apogee etc.) of the sounding rocket model introduced in this study match closely with the data presented in NASA reports.