Periodic orbits in the elliptic restricted three-body problem
Jet Propulsion Laboratory, California Institute of Technology, 1969 - Science - 125 pages
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Computation of Periodic Orbits
Families of Periodic Orbits
40 other sections not shown
0.5 Variable APOAPSIS aua2 Birkhoff coordinates circular problem circular restricted three-body coefficients computer programs conditions for family coordinates x,y corresponding differential equations DOUBLE PRECISION eccentric anomaly eigenvalues ejection orbits elliptic problem elliptic restricted three-body equal masses equations of motion families of periodic Family 8P final conditions FORTRAN four fundamental matrix geocentric independent variable inertial axes inertial coordinates Initial and final initial conditions input integration step Lagrangian Eq Lagrangian equation linear main program MASS RATIO ECC numerical integration obtained OSSIZIO*O partial derivatives PERIAPSIS periodic collision orbits primaries pulsating coordinates RATIO ECC 61 recapitulation cards rectilinear recurrence relations recurrent power series region regularized RESTR.PROBL restricted three-body problem roots rotating axes rotating coordinates rotating-pulsating coordinates Runge-Kutta satellite solving stability Subroutine DERIV symmetric periodic orbits syzygy-axis Table 22 contd tions transformation true anomaly values variational equations XI YD0T1 MASS XO YDOTO XI YD0T0 XI YD0T1 MASS RATIO YDOTO XI YD0T1