2014/10/31 by Ashok Kumar Pal, Badam Singh Kushvah · 37 citations
Engineering · Physics and Astronomy · #Aerodynamic drag #Astro and Planetary Science #Astronomy #Astrophysics #Astrophysics and Star Formation Studies #Circular orbit #Classical mechanics #Drag #Drag coefficient #Halo #Halo orbit #Lagrangian point #Mechanics #Perturbation (astronomy) #Physics #Radiation pressure #Spacecraft Dynamics and Control #Three-body problem #Tidal force #astro-ph.EP #msc:70F15 #msc:70M20
paper · pdf · doi:10.1093/mnras/stu2100
published in Monthly Notices of the Royal Astronomical Society 446(1), 959-972 (Oxford University Press) · Accepted 2014 October 8. Received 2014 October 2; in original form 2014 May 19
openalex publication_date 2014/11/14 · arxiv created 2014/11/20 · arxiv updated 2014/11/21 · openalex created_date 2016/06/24 · openalex updated_date 2026/08/05
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 the 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 the Lindstedt–Poincaré 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 travelling under drag forces.