Orbit keeping control strategy design for the quasi-period orbit with STK/astrogator

For the spacecraft in the Quasi-period orbit of Earth-Moon libration point, the stability of the orbit is decreased obviously because of the perturbation of solar gravity and Moon's elliptical motion around Earth. However the applying of the control strategy that eliminate the velocity component of X axis when the spacecraft crosses the X-Z plane, a valid method in CRTBP, in the E-M rotating coordinate often causes the divergence of the orbit. In this paper, by analyzing the dynamical characteristics of the spacecraft, a control strategy is designed and validated with Satellite Tool Kit (STK) for the long time maintenance of the E-M libration quasi-period orbit. Using the high precision orbit propagating model of STK software and the auto targeting function of the Atrogator module, the simulation scenario is constructed to optimize the control maneuvers of the spacecraft. The simulation result shows that the spacecraft can keep in the orbit for a long time with little fuel consumption.