Maximization of the entry corridor and minimization of energy consumption during the injection of a spacecraft into the orbit of an artificial satellite of Jupiter by a combined method

Details Maximization of the entry corridor and minimization of energy consumption during the injection of a spacecraft into the orbit of an artificial satellite of Jupiter by a combined method Maximization of the entry corridor and minimization of energy consumption during the injection of a spacecraft into the orbit of an artificial satellite of Jupiter by a combined method

Jul 1982

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1982kosis..20..529i&link_type=abstract

Kosmicheskie Issledovaniia, vol. 20, July-Aug. 1982, p. 529-541. In Russian.

Physics

Atmospheric Entry, Jupiter (Planet), Orbital Maneuvers, Spacecraft Orbits, Trajectory Optimization, Artificial Satellites, Optimal Control, Spacecraft Control, Spacecraft Motion, Spacecraft Reentry, Spacecraft Trajectories

Scientific paper

The paper examines the control of the injection of a spacecraft into the orbit of an artificial satellite of Jupiter, with preliminary aerodynamic braking in the atmosphere and with the use of additional atmospheric correction of spacecraft motion. A solution is obtained to the variational problems of the search for a maximum width of the entry corridor and a minimum of energy consumption required to achieve the orbit. Quasi-optimal control programs for the atmospheric segment are examined.

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