Interplanetary Trajectory Design And Control Based On Three-Body Model

In this thesis, interplanetary orbit design and control are investigated based on circular restricted three-body problem model(CRTBP). A transfer between Lyapunov orbits in the neighborhoods of L1 and L2 is constructed by using the simple periodic orbit of the smaller celestial body as an interchange. Orbit control with respect to the reference orbit is implemented by using a low-thrust control scheme.First, the dynamical model of circular restricted three-body problem is constructed, and the five special solutions of the circular restricted three-body model, known as Langrange liberation solutions are obtained. Jacobi energy integral is derived, the possible flight regions of space vehicles are analyzed by using the concept of zero-velocity surface.Second, the stability analysis of liberation points, as well as the analysis of the structure of phase spaces near the liberation points, is conducted. The Richardson three-order approximate solutions are obtained by using Lindstedt-Poincare's method. Taking these approximate solutions as initial values, a simple periodic orbit is calculated by applying the differential correction method. The invariant manifolds near a simple periodic orbit is calculated by using the monodromy matrix method.Then, according to Broucke's classification of simple periodic orbits, the LL2, LL1 and simple periodic orbits in the Earth-Moon system are analyzed. The structure of stable and unstable invariant manifolds near the simple periodic orbits is also investigated. A transfer between a Lyapunov orbit about LL1, a distant prograde orbit about the Moon and a Lyapunov orbit about LL2 is constructed by using the distant prograde orbit about the Moon as an interchange, then a transfer between two liberation points is given. For the transfer of two liberation points, the energies used in a transfer based on the three-body model and in a Hohmann transfer are compared. Finally, orbit control of a spacecraft is designed by using Low-thrust control scheme. A simulation example of simple periodic orbit control near L2 in the Sun-Earth system is given.