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- W54313497 abstract "The perturbation of the earth oblateness on the maneuver orbit is unignorable,so it has sense to investigate the design approach of maneuver trajectory when the earth oblateness is taken into account.The achievement is helpful to implement the fast,autonomous maneuver on the spacecraft.The shooting procedure was chosen in the paper to finish the work because of its good performance in resolving the two-boundary value problem.In the process of numerical simulation,it was found that,although in most cases the iterative arithmetic converged,the shooting procedure diverged when the transfer angle is close to π.Other approaches,like Satellite Tools Kit(STK),Quasi-Mean Elements Theory etc.,also validated the outcome.Finally,theoretical manipulation verified that under the assumption of two transfer impulses,when the transfer angle is close to π,the maneuver orbit is sensitive to the terminal boundary conditions.Some means are suggested to solve the problem accordingly." @default.
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- W54313497 date "2008-07-01" @default.
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- W54313497 title "Maneuver trajectory design with J_2 correction based on shooting procedure" @default.
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