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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Three body problem periodic solutions, considering near equilibrium conservative Hamiltonian system consisting of two harmonic oscillators with rationally related frequencies
Three body problem of two heavy mass particles oscillatory motion in periodic orbits on straight line under Newtonian attraction
Three body problem by hamilton-jacobi perturbation theory - guidance systems
Elliptic restricted three body problem singularities dynamical meaning and character, presenting regularization transformations for equations of motion
Elliptic restricted three-body problem solved for eigenvalues and orbital series solutions of Lagrangian triangular point
Lagrange theory of three-body problem - celestial mechanics
Restricted three-body problem is solved using solutions of eulers problem of two fixed centers
One-dimensional three-body problem, noting shell model for two particles and coordinate transformation
Two-center problem orbit as intermediate orbit for restricted three-body problem
Periodic orbits in restricted three-body problem
Three body problem solution in terms of independent variable, using convergent power series
Two dimensional elliptic restricted three body problem, considering regularization mechanism and periodic collision orbits
The classical restricted three-body problem is extended to account for the effects of radiation pressure and the Poynting-Robertson effect on a particle with a surface-to-volume relation such that radiation pressure forces are nonnegligible moving in the gravitational field of two larger, orbiting bodies. The positions of the L4 and L5 Lagrangian points are found as functions of the ratio of radiational to gravitational forces. The inclusion of the Poynting-Robertson effect, however, is found to render the L4 and L5 points unstable on a time scale which is long compared to the rotation period of the two massive bodies. The results imply that space colonies with solar facing adjustable sails may be able to remain stationary at any heliocentric distance between a planet and the sun, and may provide a mechanism for producing asymmetries in the interplanetary dust cloud.
Equilateral triangle solution of three-body problem for Apollo Earth-Moon libration point missions
Integrals of motion in three-dimensional restricted three-body problem as generalizations of angular momentum
Numerical residual perturbation solution for prediction of satellite position in restricted three-body problem
Higher order perturbations of elements in three- body problem determined using methods of Krylov- Bogoliubov and Poincare