Increasing the geocentric energy of a spacecraft by means of lunar perturbations

Details Increasing the geocentric energy of a spacecraft by means of lunar perturbations Increasing the geocentric energy of a spacecraft by means of lunar perturbations

Mar 1980

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1980kosis..18..185e&link_type=abstract

Kosmicheskie Issledovaniia, vol. 18, Mar.-Apr. 1980, p. 185-190. In Russian.

Computer Science

Geocentric Coordinates, Lunar Effects, Orbit Perturbation, Spacecraft Launching, Spacecraft Reentry, Trajectory Analysis, Lunar Flight, Lunar Orbits, Lunar Surface, Lunar Trajectories, Power Gain

Scientific paper

In the present paper, lunar swingby trajectories are calculated by the method of a 'point sphere of influence', i.e., a method based on the assumption that the radius of the lunar sphere of influence is negligibly small as compared to the module of the geocentric radius-vector of the center of the moon. The advantageousness of decreasing the distance between a swingby trajectory from the lunar surface for maximizing the increment in geocentric energy under the action of lunar perturbations is demonstrated, and the value of the maximal increment is calculated.

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