Approximate solutions of Euler-Lambert equation for case of several revolutions about central body

Details Approximate solutions of Euler-Lambert equation for case of several revolutions about central body Approximate solutions of Euler-Lambert equation for case of several revolutions about central body

Sep 1985

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1985rpspr...6...32l&link_type=abstract

In its USSR Rept.: Space (JPRS-USP-85-005) p 32 (SEE N86-14111 04-88) Transl. into ENGLISH from Kosmich. Issled. (Moscow), v.

Physics

Euler-Lambert Equation, Interplanetary Trajectories, Orbit Calculation, Trajectory Optimization, Approximation, Fuel Consumption, Mars (Planet), Venus (Planet)

Scientific paper

Approximate solutions are obtained for the Euler-Lambert equation with
the aim of economizing machine time in the framework of designing
fuel-optimal spacecraft trajectories. The results, obtained for several
revolutions about a central body, are applicable to the
Earth-Venus-Earth and Earth-Mars-Earth trajectories.

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