Solution to a variational problem of spacecraft flight between terrestrial and lunar satellite orbits

Details Solution to a variational problem of spacecraft flight between terrestrial and lunar satellite orbits Solution to a variational problem of spacecraft flight between terrestrial and lunar satellite orbits

Mar 1979

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1979kosis..17..234g&link_type=abstract

Kosmicheskie Issledovaniia, vol. 17, Mar.-Apr. 1979, p. 234-245. In Russian.

Physics

1

Earth Orbits, Lunar Orbits, Spacecraft Trajectories, Trajectory Optimization, Transfer Orbits, Acceleration (Physics), Algorithms, Asphericity, Earth-Moon System, Functionals, Orbital Mechanics, Three Dimensional Motion

Scientific paper

Optimization of a spacecraft flight trajectory between earth orbit and lunar orbit in terms of minimum characteristic velocity is analyzed. The problem is solved in an exact formulation (with allowance for the effects of asphericity of the earth, moon, and sun) by using a numerical optimization algorithm. It is shown that absolutely optimum trajectories will have two active-flight phases, one near the earth and the other near the moon, in the case of two-dimensional acceleration of the spacecraft out of earth orbit and two- or three-dimensional transfers to lunar orbit. A characteristic velocity of less than 10 m/s is determined.

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