• 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 


Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

Copyright information

© Birkhäuser Boston 2007

Personalised recommendations