Abstract
The design of a lunar landing trajectory which satisfies certain constraints is considered and discussed. The constraints are of two kinds, kinetic constraints, which deal with the relative positions among the Sun, the Moon, the Earth, the spacecraft and tracking stations, and dynamic constraints, which deal with the orbital motion of the spacecraft. After a discussion of the characteristics of lunar flight trajectory, a method of designing standard flight trajectory is suggested that satisfies the constraints. This method is applied to the Chinese lunar landing flight and to the pre-design of the orbit of a lunar satellite.
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