Computation of optimal earth-Mars and earth-Venus trajectories

Details Computation of optimal earth-Mars and earth-Venus trajectories Computation of optimal earth-Mars and earth-Venus trajectories

Sep 1977

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1977itaes..13..549p&link_type=abstract

IEEE Transactions on Aerospace and Electronic Systems, vol. AES-13, Sept. 1977, p. 549, 550

Computer Science

Earth-Mars Trajectories, Earth-Venus Trajectories, Flight Time, Time Optimal Control, Trajectory Optimization, Transfer Orbits, Algorithms, Boundary Value Problems, Computerized Simulation, Coplanarity, Newton Methods, Trajectory Analysis

Scientific paper

Two algorithms are employed to solve the minimum time earth-Mars and earth-Venus low-thrust coplanar transfer problems. First a conjugate gradient method (CGM) with a two-dimensional search involving the control search direction length and final time as parameters is used, and then the CGM solutions are employed to obtain first guesses for a very accurate solution of the two-point boundary value problem by a shooting-Newton method. The results of the latter simulations gave different trajectories, with shorter times, than those presented by Jayaraman and Alam (1975).

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