Optimum soft landing of a spacecraft on the lunar surface from a circular lunar satellite orbit.

Details Optimum soft landing of a spacecraft on the lunar surface from a circular lunar satellite orbit. Optimum soft landing of a spacecraft on the lunar surface from a circular lunar satellite orbit.

Sep 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992cosre..30..163g&link_type=abstract

Cosmic Res., Vol. 30, No. 2, p. 163 - 169

Computer Science

Scientific paper

Results are presented from a numerical solution using the maximum principle for the problem of optimum soft landing of a spacecraft with high-thrust reactive engine on the lunar surface from a circular lunar satellite orbit in a central Newtonian gravitational field with control of the engine thrust vector. A functional representing a compromise between time and mass expenditures is minimized as are the special cases of minimum landing time and mass used. The shot method is used to obtain exact numerical solutions of the corresponding maximum principle boundary problems. Optimum soft-landing trajectories were calculated for a wide range of orbit heights, specific thrusts, thrust configurations, and compromise coefficients. It is shown that for the problem of most rapid soft landing in the absence of limitations on final mass the thrust is at a maximum and always applied, but with growth in influence within the functional of the component related to mass expenditure, birfurcation of the flight segment with maximum thrust occurs and the optimum landing trajectory consists of three segments: two segments with maximum thrust at the beginning and end of the trajectory and an intermediate segment with thrust switched off.

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