This paper studies the application of photonic laser propulsion (PLP) system to the trajectory analysis in a space mission. The PLP system is an innovative technology proposed by Dr. Bae. With repeated reflections of laser beam, it can generate continuous and tremendous power by consuming very small energy. When applying to the trajectory analysis in space flight, we model the problem as a circular restricted three-body problem, and the corresponded Jacobi integral is found. A contour of zero-velocity lines is presented. Equilibrium points under this system are also discussed and found. Numerical simulations are presented to show the validity of our derivations. The results obtained in this paper are directly applicable to the usage of the PLP thrust in the future, and potentially helpful to various space missions, including interplanetary traveling.
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