Path: Orbit/LowEnergyManeuver
% Transform from km and sec to Jacobi coordinates for circular restricted Transforms a state vector from units associated with Jacobi coordinates of the Circular Restricted Three Body Problem to units of km and sec -------------------------------------------------------------------------- Form: [stateOut,mu,sec2tu] = Kms2CRTBP(stateIn,distanceUnit,muPrimary,muSecondary); -------------------------------------------------------------------------- ------ Inputs ------ stateIn (1,6) Initial state vector distanceUnit (1) Distance from the Primary to the Secondary muPrimary (1) Gravitational Parameter of the Primary muSecondary (1) Gravitational Parameter of the Secondary ------- Outputs ------- stateOut (1,6) Output state vector mu (1) Gravitational Parameter of the CRTBP sec2tu (1) Scaling factor for time --------------------------------------------------------------------------
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