Physics
Scientific paper
Apr 1982
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1982jgcd....5..221w&link_type=abstract
Journal of Guidance, Control, and Dynamics, vol. 5, Mar.-Apr. 1982, p. 221-224.
Physics
3
Earth-Mars Trajectories, Solar Propulsion, Spacecraft Trajectories, Time Optimal Control, Trajectory Optimization, Transfer Orbits, Cost Reduction, Hamiltonian Functions, Lagrange Multipliers, Solar Sails
Scientific paper
An analytic proof is presented to show that the orbital transfer times of an earth-to-Mars solar-sail propelled spacecraft trajectory as calculated by Jayaraman (1980) are incorrect. In particular, different boundary conditions are defined, which indicate that a minimization of the Hamiltonian, which Jayaraman used, can yield the wrong stationary solution. Transfer times are calculated using a neighboring extremal algorithm based on numerical differentiation in conjunction with Krogh's variable order, variable step size integrator, resulting in a transfer time of 322 days at 2 mm/sec-sq, with endpoint restraints satisfied to within 1/1 billion. Finally, it is concluded that minimization of flight time is secondary in importance to maximization of delivered payload and minimization of overall mission cost and risk.
Bauer T. P.
Wood James L.
Zondervan K. P.
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