Path: Orbit/LowEnergyManeuver
% Transform a state vector from a rotating pulsating reference frame to J2000 Transforms from a rotating frame centered on the secondary body of a sun/planet system to the J2000 reference frame with the same center. -------------------------------------------------------------------------- Form: stateOut = RotPuls2J2000( stateIn, primary, muPrimary); -------------------------------------------------------------------------- ------ Inputs ------ stateIn (6,1) Current state vector [r;v] primary (6,1) State vector of Primary muPrimary (1) Gravitational Parameter of Primary ------- Outputs ------- stateOut (1,6) Output state vector --------------------------------------------------------------------------
Math: Linear/Cross Math: Linear/Mag Math: Linear/Unit
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