Optimal launch of a spacecraft from the lunar surface into circular lunar orbit

Details Optimal launch of a spacecraft from the lunar surface into circular lunar orbit Optimal launch of a spacecraft from the lunar surface into circular lunar orbit

Sep 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991kosis..29..695g&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 29, Sept.-Oct. 1991, p. 695-704. In Russian.

Physics

Circular Orbits, Lunar Satellites, Lunar Surface, Satellite Orbits, Spacecraft Launching, Trajectory Optimization, Lunar Gravitation, Rocket Engines, Thrust-Weight Ratio

Scientific paper

The paper presents results of a numerical solution for the optimal injection of a spacecraft from the lunar surface into a circular lunar orbit. The functions that are controlled are the direction and magnitude of the rocket thrust; the spacecraft is equipped with a high thrust engine. The functional that is minimized represents a tradeoff between the orbital injection time and the mass expenditure. The problem is solved using the maximum principle. Optimal trajectories are calculated in a wide range of orbit altitudes, thrust-to-weight ratios, and net specific thrusts.

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