Physics
Scientific paper
Jul 1992
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992kosis..30..483g&link_type=abstract
Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 30, no. 4, p. 483-494.
Physics
Circular Orbits, Lunar Landing, Lunar Surface, Optimization, Soft Landing Spacecraft, Lunar Satellites, Rocket Engines, Thrust-Weight Ratio, Trajectory Optimization
Scientific paper
Three types of problems concerning the optimal soft landing of a spacecraft with a high-thrust rocket engine from a circular moon satellite orbit at a specified point on the lunar surface are investigated numerically using the maximum principle. In particular, consideration is given to minimum-time landing, landing with minimum mass consumption, and landing with a minimum functional representing a trade-off between the time and mass requirements. The optimal trajectories are calculated for a wide range of initial orbit heights, angular distances of the landing point, thrust-to-weight ratios of the spacecraft, specific thrusts, and tradeoff ratios.
Grigor'ev K. G.
Zapletin M. P.
Zapletina E. V.
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