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In this paper, we determine the effect of radiation pressure,Poynting-Robertson drag and solar wind drag on the Sun-(Earth-Moon) restrictedthree body problem. Here, we take the larger body of the Sun as a largerprimary, and Earth+Moon as a smaller primary. With the help of the perturbationtechnique, we find the Lagrangian points, and see that the collinear pointsdeviate from the axis joining the primaries, whereas the triangular pointsremain unchanged in their configuration. We also find that  Lagrangian points move towards the Sun when radiation pressure increases. Wehave also analysed the stability of the triangular equilibrium points and havefound that they are unstable because of the drag forces. Moreover, we havecomputed the halo orbits in the third-order approximation usingLindstedt-Poincar$\acute{e}$ method and have found the effect of the dragforces. According to this prevalence, the Sun-(Earth-Moon) model is used todesign the trajectory for spacecraft traveling under the drag forces.

Geometry of halo and Lissajous orbits in the circular restricted three-body problem with drag forces