caa a22 4500 445863439 CHVBK 20180317145450.0 cr unu---uuuuu 170323e20110501xx s 000 0 eng 10.1007/s10569-011-9336-4 doi (NATIONALLICENCE)springer-10.1007/s10569-011-9336-4 Thorne James System Evaluation Division, Institute for Defense Analyses, 22311, Alexandria, VA, USA aut Orbital maneuver optimization using time-explicit power series [Elektronische Daten] [James Thorne] Orbital maneuver transfer time optimization is traditionally accomplished using direct numerical sampling to find the mission design with the lowest delta-v requirements. The availability of explicit time series solutions to the Lambert orbit determination problem allows for the total delta-v of a series of orbital maneuvers to be expressed as an algebraic function of only the individual transfer times. The delta-v function is then minimized for a series of maneuvers by finding the optimal transfer times for each orbital arc. Results are shown for the classical example of the Hohmann transfer, a noncoplanar transfer as well as an interplanetary fly-by mission to the asteroids Pallas and Juno. The Author(s), 2011 Orbital maneuver optimization nationallicence Lambert problem nationallicence Orbital mission planning nationallicence Thorne series solution of lambert problem nationallicence Celestial Mechanics and Dynamical Astronomy Springer Netherlands 110/1(2011-05-01), 31-42 0923-2958 110:1<31 2011 110 10569 https://doi.org/10.1007/s10569-011-9336-4 text/html Onlinezugriff via DOI 1 research-article jats NATIONALLICENCE 856 40 https://doi.org/10.1007/s10569-011-9336-4 text/html Onlinezugriff via DOI NATIONALLICENCE 100 1- Thorne James System Evaluation Division, Institute for Defense Analyses, 22311, Alexandria, VA, USA aut NATIONALLICENCE 773 0- Celestial Mechanics and Dynamical Astronomy Springer Netherlands 110/1(2011-05-01), 31-42 0923-2958 110:1<31 2011 110 10569 Metadata rights reserved Springer special CC-BY-NC licence nationallicence BK010053 XK010053 XK010000 NATIONALLICENCE NATIONALLICENCE NL-springer