| In this dissertation, the design and optimization of lunar probe orbit has been studied by using the theory and method of spacecraft orbital dynamics, aiming at to launch polar moon satellite from the earth parking orbit, and considering synthetically the problems about the launcher energy, flying time, launch window and orbit navigation. The flying conditions, program and orbit of the lunar probe are given. Chapter 1 introduces three kinds of typical restrictive conditions which are the restrictions of orbital kinematics, ground observation, sunlight illumination. The restriction of orbital kinematics includes that of earth parking paths earth-moon transfer path, and lunar satellite path. Chapter 2 introduces a method for preliminary orbital design using double two-body hypothesis. A fast design metod for earth-moon transfer orbit is presented. By analyzing and computing, it is educed that the minimum-energy orbit is geo-direct motion and seleno-direct motion orbit. Chapter 3 analyzes numerically the effects for orbit calculation caused by orbital perturbation, parameter error and so on. A precise mathematical model of orbit calculation is given. Chapter 4 sets up a ariable step size to-and-fro bill climbing?method for precise orbit designing rapidly, under the precise orbital model. Chapter 5 discusses on launch window. First, according to the hypothesis of two body problem, a series of formula are deduced for analyzing the efforts causing by every restrict conditions and sketchy windows, which are about 2-3 days every month. Then, utilizing the precise orbit model, the precise windows are computed, which are only ~everal minutes. Chapter 6 provides the numbers and the distributions of the available GPS satellites, the space-time characteristics about GPS signals, and the optimal guidance time. Chapter 7 introduces the software tool kit of lunar orbital design. Chapter 8 sums up whole work about the paper, some new ideas about the orbital design of lunar probe are presented farther. |
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