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Abstract

  • To model the problem of three bodies in mutual gravitational attaction and present its general solution by Lagrange.

  • To develop the restricted three-body problem for modeling the flight of a spacecraft under the gravitational influence of two massive bodies.

  • To discuss the solvability, equilibrium points, and numerical solutions of the restricted three-body problem with examples of earth-moon-spacecraft trajectories.

Keywords

Equilibrium Point Lagrangian Point Halo Orbit Scalar Constant Advance Composition Explorer 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Birkhäuser Boston 2007

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