The attitude and trajectory dynamics of a satellite and solid propellant rocket engine, with hypothesis of rigid body mechanics, is modelled and analyzed in an orbital injection. A numerical algorithm based on the model above is set up to minimize the injection errors, taking into account realizable thrust and mass ejection rates for rocket engine. Spacecraft engineering tolerance are discussed as they disturb land area converage (orbit inclination) by the satellite and its lifetime (eccentricity and semi major axis). A classic yo-yo despin device project to null the spacecraft angular motion about its center of mass, in orbital flight is presented, as well as a previous discussion as when to release this gadget.
Dynamic Analysis of Spacecraft Trajectory and Attitude in an Orbital Insertion Analise Dinamica DA Trajetoria E DA Atitude de Um Veiculo Espacial NA Fase de Injecao
1983
232 pages
Report
Keine Angabe
Englisch
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