Other
Scientific paper
May 2001
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2001acasn..42..161h&link_type=abstract
Acta Astronomica Sinica, vol.42, no.2, p. 161-172.
Other
Lunar-Landing Trajectory, Orbit Design
Scientific paper
This article presents a method to design a Lunar-landing trajectory under certain constraints. The meaning of the constraints is analyzed and reduced to manageable forms. The constrains are classified into two categories: kinetic constraints deal with the relative configurations among Sun, Moon, Earth, spacecraft and tracking stations, while dynamic constrains concern the orbit of the spacecraft. Kinetic constraints generally select the launching dates of a month to satisfy the tracking network constraint and the landing hours of a day to satisfy the illumination constraint. Dynamic constraints reduce the 6 degrees of freedom for a spacecraft to 3 and impose limits on the adjustment of the 3 free parameters. To find the proper initial parameters for the trajectory search, a Lunar-landing trajectory is approximately treated as a combination of two separate perturbed two-body orbits. With the analytic solution for a two-body problem and the numerical solution for a perturbed problem available, the search can be simplified by first requiring the trajectory enter the Hill radius of the Moon, and then fine-tune the parameters to satisfy all the constraints. Although it is unlikely the standard trajectory this paper obtains will be materialized due to the unrealistic constraints, as explained in the context, the method of searching standard flight trajectories can be generalized to treat other Lunar-landing missions under different constraints.
Hu Xiao-Gong
Huang Chan Chun
Li Xiaoliang
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