This paper develops the mathematical framework to use higher-order state transition tensor (STT) approximations of nonlinear dynamics to design impulsive spacecraft maneuvers incorporating the effects of state uncertainty. Several semi-analytic formulations are derived strictly as a function of a reference STT expansion, including minimum-energy, minimum-covariance, and maximum-covariance cost functions; mean state constraints; state chance constraints; and control-linear maneuver execution errors. Analytical gradients are derived for most of the formulations, which can be used to speed up optimization procedures developed with these equations. A tractable approximation of the nonlinear covariance propagation equations is also derived to further speed up these calculations. Example applications for each of the formulations are provided for a multi-impulse, highly nonlinear transfer in the Earth–moon system. The proposed methodology can be used to efficiently compute a variety of maneuvers accounting for the effects of spacecraft state uncertainty using a single STT expansion. This can enable more flexible and rapid maneuver planning in reaction to changing mission priorities, navigation errors, and maneuver execution errors.


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    Title :

    Nonlinear Formulations for Spacecraft Maneuver Design Under Uncertainty


    Contributors:


    Publication date :

    2025-06-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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