Interplanetary and intermoon tour missions have benefited from the implementation of leveraging maneuvers that efficiently change spacecraft energy relative to a flyby body. In the current work, these v∞ leveraging maneuvers are generalized and reformulated into a boundary-value problem suitable for broad trajectory searches using only one additional continuous degree of freedom. The presented method naturally incorporates noncircular orbits and arbitrary ephemeris locations for bodies as well as leveraging maneuvers between different bodies. These advantages come from using the same boundary conditions as the Lambert problem, which also maintains the Lambert-based outer-loop search architecture used in many trajectory design tools. The general maneuver formulation of the presented method allows it to be used for interplanetary or intermoon trajectories and allows the incorporation of nontangent leveraging transfers. Some examples of the new formulation's utility are also explored using representative transfers; these examples present some of the families of leveraging solutions and show that bielliptic transfers are a special case of interbody leveraging. Presented as AAS Paper 2012-162 at the 22nd AAS/AIAA Space Flight Mechanics Meeting, Charleston, SC, 29 January-2 February 2012


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    Title :

    V -Infinity Leveraging Boundary-Value Problem and Application in Spacecraft Trajectory Design




    Publication date :

    2015




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.60 Raumfahrttechnik
    Local classification TIB:    770/7040