AbstractThe multistep adaptive control algorithms with trajectory prediction for Mars orbiter insertion by use of atmospheric deceleration are described. The navigation task is proposed to be solved simultaneously with defining the control law throughout the entry. The stabilization algorithm ensures a low fuel consumption and acceptability of transient process, even under a considerable disturbing aerodynamic torque. Digital computer simulation has been used for the algorithm development and evaluation. The simulation results have shown high effectiveness of the proposed control methods.
Mars orbiter insertion by use of atmospheric deceleration
Acta Astronautica ; 5 , 10 ; 765-780
1978-03-20
16 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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