The solutions to Lambert problem are mostly based on two-body supposition, which may bring inconvenience to accurately control of orbital transfer. Therefore, an approach to amend the impulses of Lambert transfer is presented. In terms of the perturbation, the precise dynamical model of spacecraft is established. Based on the result of Lambert algorithm, Quasi-Newton iterative method is employed to correct the impulses and reduce the errors of final state in orbital transfer. The approach is then used in the problem of time-fixed accurate impulse transfer. Finally, a two hierarchical programming model is established to solve the problem, which was proved to be right by an example.