A method for solving the so-called low-thrust Lambert problem is proposed. After formulating it as a two-point boundary value problem, where initial and final positions are provided in terms of equinoctial variables, a first-order perturbative approach is used for investigating the variation of orbital elements generated by the low-thrust propulsion system, which acts as a perturbing parameter with respect to the zero-order Keplerian motion. An implicit algebraic problem is obtained, which allows for the determination of the low-thrust transfer trajectory that drives the equinoctial parameters from the initial to the final values in a prescribed time. Three test cases are presented, which demonstrate the flexibility of the method for different mission scenarios: an interplanetary transfer from Earth to Mars, a spiral multirevolution transfer from low Earth orbit to the International Space Station, and a maneuver to a highly elliptical orbit with large plane change.


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    Title :

    Solution of Low-Thrust Lambert Problem with Perturbative Expansions of Equinoctial Elements


    Contributors:
    Avanzini, G. (author) / Palmas, A. (author) / Vellutini, E. (author)

    Published in:

    Publication date :

    2015-09-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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