The optimal soft landing of a spacecraft on the lunar surface from the lunar satellite circular orbit

Details The optimal soft landing of a spacecraft on the lunar surface from the lunar satellite circular orbit The optimal soft landing of a spacecraft on the lunar surface from the lunar satellite circular orbit

Mar 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992kosis..30..203g&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 30, no. 2, Mar.-Apr. 1992, p. 203-211. In Russian.

Computer Science

Circular Orbits, Lunar Landing, Lunar Surface, Satellite Orbits, Soft Landing, Spacecraft Landing, Gravitational Fields, Lunar Satellites, Maximum Principle, Thrust Vector Control, Thrust-Weight Ratio

Scientific paper

Results are presented of a numerical solution, based on the maximum principle, of the problem of the optimal soft landing of a spacecraft with a high-thrust rocket engine from the lunar satellite circular orbit to the lunar surface in its central Newtonian gravitational field with thrust vector control. The functional, which represents a tradeoff between landing time and mass expenditures, is minimized. The 'shooting' method is used to obtain an exact numerical solution to the corresponding maximum principle boundary problems. Calculations of optimal trajectories of a soft landing are carried out in a wide range of orbit heights, net specific thrusts, thrust-to-weight ratios, and tradeoff coefficients. It is shown that in the problem of the fastest soft landing in the absence of a restriction on final mass, the thrust is maximum and is generated continuously; however, with the growth of the effect in the functional of the component linked with mass expenditures, a bifurcation of the flight sector with maximum thrust occurs.

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