Small Lunar Probe Track Design

In the new century, our country is planning to launch lunar detector. This detector will be assumed to enter 300-kilometer high moon-circling polar orbit. This paper involves design a best transfer orbit from earth according to least energy considering our country actuality. At first, preliminary analysis of the problem of launching lunar detector is given using patched-conic technique. Then, precise analysis is given in a four-body mathematical model and numerical integration. This paper gives a method of direct transfer and finds a best transfer trajectory. At the same time, launch window, flight procedure and tracking arc of this trajectory are analyzing. At last, using STK (Satellite Tool Kits) soft simulates the whole trajectory.