Path: Orbit/LowEnergyManeuver
% Transform a state vector from the J2000 reference frame to a rotating pulsating reference frame centered at the barycenter of the secondary body's system. Since version 9. -------------------------------------------------------------------------- Form: stateOut = J20002RotPulsPlanetMoon(stateIn,primaryEph,muPrimary,secondaryEph); -------------------------------------------------------------------------- ------ InputsP ------ stateIn (6,1) Initial state vector primaryEph (6,1) State vector of Primary Object muPrimary (1) Gravitational Parameter of Object secondaryEph (6,1) State vector of Secondary Object ------- Outputs ------- stateOut (6,1) Output state vector --------------------------------------------------------------------------
Math: Linear/Mag Math: Linear/Unit
Back to the Orbit Module page