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An integrated nonlinear planning(NLP) model is built for space station long-duration orbital missions considering both the vehicle visiting schedules and the interaction effects between target phasing,vehicle return adjusting and Earth observation aiming.A two-level optimization approach is proposed to solve this complicated problem.The up-level problem employs the launch times of visiting vehicles as design variables,considers the constraints of crew rotations,resource resupplies and rendezvous launch windows,and is solved by a genetic algorithm.The low-level problems employ the maneuver impulses and burn times within each orbital mission as design variables,and a high-efficient shooting iteration method is proposed based on an analytical equation for the phase angle correction considering the J 2 perturbation.The results indicate that the integrated NLP model for space station long-duration orbital missions is effective,and the proposed optimization approach can obtain the optimal solutions that satisfy the multiple constraints and reduce the total propellant consumption.
An integrated nonlinear planning (NLP) model is built for space station long-duration orbital movement considering both the vehicle visiting schedules and the interaction effects between target phasing, vehicle return adjusting and Earth observation aiming. A two-level optimization approach is proposed to solve this complicated problem.The up-level problem employs the launch times of visiting vehicles as design variables, considers the constraints of crew rotations, resource resupplies and rendezvous launch windows, and is solved by a genetic algorithm. the low-level problems employ the maneuver impulses and burn times within each orbital mission as design variables, and a high-efficient shooting iteration method is proposed based on an analytical equation for the phase angle correction correction the j 2 perturbation. The results that results that integrated NLP model for space station long -duration orbital missions is effective, and the proposed optimization approach can obtain the optimal so lutions that satisfy the multiple constraints and reduce the total propellant consumption.