Abstract
In this paper, a near fuel-optimal, receding horizon based station-keeping strategy is designed and implemented to estimate a two-year average station-keeping cost on a L <sub xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">1</sub> Halo orbit in Sun-Earth Circular Restricted Three-Body problem. Impulsive Model Predictive Static Programming, a finite time, non-linear optimal control technique is used to obtain optimal station-keeping maneuvers. The technique involves calculation of sensitivity matrices which are done in a computationally efficient manner owing to their recursive nature. The algorithm is iterative where the guess station-keeping maneuvers are optimally updated by a closed-form equation until an output terminal constraint as well as an optimal cost function are satisfied. The effect of station-keeping horizon time on the total maneuver cost was analyzed in the presence of Solar Radiation Pressure and uncertainties associated with orbit insertion, tracking and maneuver execution errors.
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