Julio C. Sanchez |
Ph.D. Candidate, Universidad de Sevilla, Aerospace Engineering Department, 41092, Sevilla, Spain. | Francisco Gavilan |
Assistant Professor, Universidad de Sevilla, Aerospace Engineering Department, 41092, Sevilla, Spain. | Rafael Vazquez |
Associate Professor, Universidad de Sevilla, Aerospace Engineering Department, 41092, Sevilla, Spain. | Christophe Louembet |
Associate Professor, Laboratoire d'analyse et d'architecture des systèmes, Methods and Algorithms in Control, 31400, Toulouse, France. |
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Abstract:
In this paper the spacecraft rendezvous hovering phase, under circular restricted three-body problem assumptions, is addressed. The objective is to stay close to a Near-Rectilinear Halo Orbit, similar to the one proposed for the future Lunar Orbital Platform-Gateway. The relative dynamics are linearized assuming the vehicles are close enough. Then, a simplified propagation method based on assuming the state matrix as constant is developed. This allows to obtain an analytical approximate solution based on the state matrix eigendecomposition. Using this propagation model, the hovering phase problem is posed and recast as a static program. This static program is solved periodically to update the required control sequence. The numerical results demonstrate the efficiency of the proposed propagation method and the hovering phase mission fulfilment.
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