Fast 2-impulse non-Keplerian orbit-transfer using the Theory of Functional Connections. (arXiv:2102.11837v1 [astro-ph.EP])
<a href="http://arxiv.org/find/astro-ph/1/au:+Junior_A/0/1/0/all/0/1">Allan K. de Almeida Junior</a>, <a href="http://arxiv.org/find/astro-ph/1/au:+Johnston_H/0/1/0/all/0/1">Hunter Johnston</a>, <a href="http://arxiv.org/find/astro-ph/1/au:+Leake_C/0/1/0/all/0/1">Carl Leake</a>, <a href="http://arxiv.org/find/astro-ph/1/au:+Mortari_D/0/1/0/all/0/1">Daniele Mortari</a>
This study applies a new approach, the Theory of Functional Connections
(TFC), to solve the two-point boundary-value problem (TPBVP) in non-Keplerian
orbit transfer. The perturbations considered are drag, solar radiation
pressure, higher-order gravitational potential harmonic terms, and multiple
bodies. The proposed approach is applied to Earth-to-Moon transfers, and
obtains exact boundary condition satisfaction and with very fast convergence.
Thanks to this highly efficient approach, perturbed pork-chop plots of
Earth-to-Moon transfers are generated, and individual analyses on the
transfers’ parameters are easily done at low computational costs. The minimum
fuel analysis is provided in terms of the time of flight, thrust application
points, and relative geometry of the Moon and Sun. The transfer costs obtained
are in agreement with the literature’s best solutions, and in some cases are
even slightly better.
This study applies a new approach, the Theory of Functional Connections
(TFC), to solve the two-point boundary-value problem (TPBVP) in non-Keplerian
orbit transfer. The perturbations considered are drag, solar radiation
pressure, higher-order gravitational potential harmonic terms, and multiple
bodies. The proposed approach is applied to Earth-to-Moon transfers, and
obtains exact boundary condition satisfaction and with very fast convergence.
Thanks to this highly efficient approach, perturbed pork-chop plots of
Earth-to-Moon transfers are generated, and individual analyses on the
transfers’ parameters are easily done at low computational costs. The minimum
fuel analysis is provided in terms of the time of flight, thrust application
points, and relative geometry of the Moon and Sun. The transfer costs obtained
are in agreement with the literature’s best solutions, and in some cases are
even slightly better.
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