In this article, after describing a procedure to construct trajectories for a spacecraft in the four‐body model, a method to correct the trajectory violations is presented. To construct the trajectories, periodic orbits as the solutions of the three‐body problem are used. On the other hand, the bicircular model based on the Sun–Earth rotating frame governs the dynamics of the spacecraft and other bodies. A periodic orbit around the first libration‐point L
1 is the destination of the mission which is one of the equilibrium points in the Sun–Earth/Moon three‐body problem. In the way to reach such a far destination, there are a lot of disturbances such as solar radiation and winds that make the plans untrustworthy. However, the solar radiation pressure is considered in the system dynamics. To prevail over these difficulties, considering the whole transfer problem as an optimal control problem makes the designer to be able to correct the unavoidable violations from the pre‐designed trajectory and strategies. The optimal control problem is solved by a direct method, transcribing it into a nonlinear programming problem. This transcription gives an unperturbed optimal trajectory and its sensitivities with respect perturbations. Modeling these perturbations as parameters embedded in a parametric optimal control problem, one can take advantage of the parametric sensitivity analysis of nonlinear programming problem to recalculate the optimal trajectory with a very smaller amount of computation costs. This is obtained by evaluating a first‐order Taylor expansion of the perturbed solution in an iterative process which is aimed to achieve an admissible solution. At the end, the numerical results show the applicability of the presented method.
