Abstract
During atmospheric entry, winds and atmospheric uncertainties may result in large dispersions at the beginning of powered landing of reusable rockets. To mitigate the effect of large initial dispersions and uncertainties, an optimal feedback guidance algorithm is presented for the powered landing of reusable rockets. The presented guidance algorithm implements receding-horizon trajectory optimization based on finite-element collocation approaches. The finite-element collocation approach fully discretizes the state and control variables of the powered landing guidance problem, leading to nonlinear programming (NLP) problems addressed by NLP solvers. The optimal trajectory of the powered landing is re-planned in each guidance period using the finite-element collocation approach. Results indicate the proposed optimal feedback guidance algorithm could guide the reusable rocket to land at a specified landing site in the presence of initial dispersion, model uncertainty, and disturbance.
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