The optimal launching of a space vehicle from the surface of the moon to a fixed point on the circular orbit of its artificial satellite

Details The optimal launching of a space vehicle from the surface of the moon to a fixed point on the circular orbit of its artificial satellite The optimal launching of a space vehicle from the surface of the moon to a fixed point on the circular orbit of its artificial satellite

Jun 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992kosis..30..321g&link_type=abstract

Kosmicheskie Issledovaniya (ISSN 0023-4206), vol. 30, no. 3, p. 321-332.

Computer Science

Circular Orbits, Lunar Surface, Satellite Orbits, Spacecraft Trajectories, Trajectory Optimization, Transfer Orbits, Rocket Thrust, Thrust-Weight Ratio

Scientific paper

The paper presents an analysis and results of a numerical solution, based on the maximum principle, of three types of problems concerning the optimal launching of a space vehicle with a high-thrust rocket engine from the lunar surface to a fixed point on the circular orbit of a lunar artificial satellite. Attention is given to the problems of the fastest possible launching time, launching with minimal mass expenditure, and minimal trade-off functional (a compromise between expenditures for launch time and mass). The shooting method is used to obtain exact numerical solutions for the appropriate maximum principle boundary problems.

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