Path: Orbit/LowEnergyManeuver
% Transform from J2000 frame to rotating-pulsating Transform a state vector from the J2000 reference frame to a rotating-pulsating reference frame centered on the secondary body. -------------------------------------------------------------------------- Form: stateOut = J20002RotPuls(stateIn,primaryEph,muPrimary) -------------------------------------------------------------------------- ------ Inputs ------ stateIn (6,1) Initial state vector primaryEph (6,1) State vector of Primary muPrimary (1,1) Gravitational Parameter the Primary ------- Outputs ------- stateOut (6,1) Output state vector --------------------------------------------------------------------------
Math: Linear/Mag Math: Linear/Unit
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