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Dynamics and Mission Design Near Libration Points

Fundamentals - The Case of Triangular 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, L 1, 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 qua

The periods found are equal to the period of revolution of the Sun in the Earth-
Moon synodical system and to three times this period. The period must be a
multiple of the period of revolution. The bicircular problem is far from the real one.