Dynamics and Mission Design Near Libration Points

This book studies several problems related to the analysis of planned or possible spacecraft missions. It is divided into four chapters. The first chapter is devoted to the computation of quasiperiodic solutions for the motion of a spacecraft near the equilateral points of the Earth–Moon system. The second chapter gives a complete description of the orbits near the collinear point, L1, between the Earth and the Sun in the restricted three-body problem (RTBP) model. In the third chapter, methods are developed to compute the nominal orbit and to design and test the control strategy for the quasiperiodic halo orbits. In the last chapter, the transfer from the Earth to a halo orbit is studied. Contents:Quasi-periodic Solutions Near the Equilateral Points of the Earth-Moon SystemGlobal Description of the Orbits Near the L1 Point of the Earth–Sun System in the RTBPQuasi-periodic Halo OrbitsTransfer from the Earth to a Halo OrbitAppendices:The JPL ModelReference Systems and Equations of MotionThe Model Equations Near the Equilateral Points in the Earth–Moon SystemTransfer Between Halo Orbits of the RTBP Readership: Applied mathematicians, computational physicists and aerospace engineers. Keywords:Fourier Analysis and Analytical Models near Libration Points;Quasi-periodic Solutions near Triangular Points;Reduction to the Centre Manifold for the RTBP;Global Behaviour near Collinear Libration Points;Halo, Quasihalo, Vertical and Lissajous Orbits;Nominal Orbits of a Reallistic Model by Numerical Refinement;Station Keeping Strategies for Orbits near Collinear Points;Stable Manifolds and Transfer Orbits;Transfers Between Halo Orbits