Orbital maneuver optimization using time-explicit power series

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Original Article


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.


Orbital maneuver optimization Lambert problem Orbital mission planning Thorne series solution of lambert problem 


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Copyright information

© The Author(s) 2011

Authors and Affiliations

  1. 1.System Evaluation DivisionInstitute for Defense AnalysesAlexandriaUSA

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