Geometry of halo and Lissajous orbits in the circular restricted three-body problem with drag forces
arXiv:1410.4311 · doi:10.1093/mnras/stu2100
Abstract
In this paper, we determine the effect of radiation pressure, Poynting-Robertson drag and solar wind drag on the Sun-(Earth-Moon) restricted three body problem. Here, we take the larger body of the Sun as a larger primary, and Earth+Moon as a smaller primary. With the help of the perturbation technique, we find the Lagrangian points, and see that the collinear points deviate from the axis joining the primaries, whereas the triangular points remain unchanged in their configuration. We also find that Lagrangian points move towards the Sun when radiation pressure increases. We have also analysed the stability of the triangular equilibrium points and have found that they are unstable because of the drag forces. Moreover, we have computed the halo orbits in the third-order approximation using Lindstedt-Poincar method and have found the effect of the drag forces. According to this prevalence, the Sun-(Earth-Moon) model is used to design the trajectory for spacecraft traveling under the drag forces.
arXiv commentAccepted 2014 October 8. Received 2014 October 2; in original form 2014 May 19
References in corpus (4)
- Equilibrium Points and Zero Velocity Surfaces in the Restricted Four Body Problem with Solar Wind Drag
- The Effect of Radiation Pressure on the Equilibrium Points in the Generalised Photogravitational Restricted Three Body Problem
- Computing Invariant Manifolds and Connecting Orbits in the Circular Restricted Three Body Problem
- Linear Stability of Triangular Equilibrium Points in the Generalized Photogravitational Restricted Three Body Problem with Poynting-Robertson Drag