Analysis of trajectory sensitivity in restricted three-body problem

In the context of circular restricted three-body problem, the trajectory sensitivity to disturbances of different kinds, different magnitude, and different direction are analyzed. Firstly, a method based on eigenvalues of state transition matrix is improved to achieve computational efficiency. Secondly, a method based on error in configuration space is proposed to calculate trajectory local stability in detail. Based on this method, the maximum unstable direction of any point on the trajectory can be decided. As an example, the trajectory sensitivity of Earth-Moon L1 point Lyapunov orbit is calculated and discussed in detail. Finally, this method is extended to calculate the sensitivity of a non-periodical trajectory, and the result is presented. Information gained from the trajectory sensitivity analysis can be used to guide the measurement and navigation process in practical space missions.