Eventos Anais de eventos
ENCIT 2016
16th Brazilian Congress of Thermal Sciences and Engineering
FLIGHT MECHANICS AND MONTE CARLO ANALYSIS FOR A STUDENT SOUNDING ROCKET
Submission Author:
Eduardo Jourdan , SP
Co-Authors:
Matheus Ferraz, Dalton Menezes
Presenter: Eduardo Jourdan
doi://10.26678/ABCM.ENCIT2016.CIT2016-0156
Abstract
During these past five years a group in ITA (Instituto Tecnológico de Aeronáutica) called ITA Rocket Design has been developing and flying high-power rockets in order to participate in an international college engineering competition called IREC that is held every year in the United States. The mission of this competition is to design, build, test and fly experimental sounding rockets to achieve as close as possible 10000 ft with 10 lb of payload and recover it. Their flight envelope involves a very high acceleration from launch, no guidance and control during ascent and a smooth descent and recovery via parachutes. This present work describes the analysis of flight mechanics and flight path performed in order to do system design and to derive subsystem requirements. A computational framework was made in Matlab and C++ language to perform point-mass simulations to determine propellant and structural mass, a in-plane 3 degree of freedom (DOF) for aerodynamics stability requirement analysis and a fully 6 DOF for Monte Carlo simulations. The results were compared to each other and also with previous flight tests realized by this group. For the 6 DOF software, experimental data were used as mass model, and an aerodynamic three dimensional look-up table was created with a semi-empirical software called Missile Datcom. Either only static or as well as dynamic aerodynamics coefficient were considered and their results compared. The influence of wind was also included and tested, resulting in precious data for the flight operation team to choose the launch azimuth. Finally, the Monte Carlo simulations performed gave the sensitivity of the apogee altitude, maximum velocity and maximum touchdown range regarding parameters uncertainties, including aerodynamic model and motor thrust.
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