Optimal soft landing of a spacecraft from a circular orbit of an artificial satellite of the Moon onto a specified point of its surface.

Details Optimal soft landing of a spacecraft from a circular orbit of an artificial satellite of the Moon onto a specified point of its surface. Optimal soft landing of a spacecraft from a circular orbit of an artificial satellite of the Moon onto a specified point of its surface.

Jan 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993cosre..30..392g&link_type=abstract

Cosmic Res., Vol. 30, No. 4, p. 392 - 402

Computer Science

Scientific paper

Based on the principle of the maximum, three types of problems of optimal soft landing of a spacecraft with a high thrust rocket engine from a circular orbit of an artificial satellite of the Moon onto a point specified in the orbit plane of the Moon's surface with a controlled thrust vector have been investigated numerically. The Moon's gravitational field is assumed to be a central Newtonian one. The problems of landing in the shortest time, landing with minimum mass expenditure, and one with a minimum value of a functional which represents a compromise between expenditures of time and mass for a landing have been considered. Accurate numerical solutions of the corresponding boundary value problems for the principle of the maximum have been obtained by a shooting method. Calculations of optimal trajectories have been made over a broad range of varying the height of the initial orbit, the angular distance of the landing point, the spacecraft's thrust to weight ratio, specific impulse, and the compromise coefficients.

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