• 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.


Equilibrium Point Lagrangian Point Halo Orbit Scalar Constant Advance Composition Explorer 
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© Birkhäuser Boston 2007

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