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adaptive_Runge_Kutta_Fehlberg_orbit

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Prokop
Hapala
Simulation of satelite orbits arround massive body integrated by Runge-Kutta-Fehlberg ( RKF45 ) method with adaptive time step and precission 1e-9. Big dots are time steps of RKF45 indepenet for each body, while small dots are interpolated by cubic polynon to obtain bodies state at the same global time. Ploted is number of steps required for simulation 1 unit of time for each body (more eliptic orbits needs more steps) RKF45 solver took here https://code.google.com/p/exoflight/source/browse/trunk/Exoflight/src/com/fasterlight/exo/orbit/integ/RungeKuttaFehlberg45.java
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