Path: CubeSat/Utilities
% Propagate orbital elements with J2 gravity term Integrates the orbit using RHSGeoJ2 and ode45. Using the J2 term requires a Julian date as the inertial state must be converted to Earth-fixed at every timestep. RHSGeoJ2 uses ECIToEF which is fast and of moderate precision. -------------------------------------------------------------------------- Form: [r, v, t] = RVWithJ2( el, jD0, time, j2 ) -------------------------------------------------------------------------- ------ Inputs ------ el (1,6) Initial Keplerian elements jD0 (1,1) Initial Julian Date [JD] time (1,:) Time vector [sec] ------- Outputs ------- r (3,:) Position vectors for times t v (3,:) Velocity vectors for times t t (1,:) Times at which r and v are calculated -------------------------------------------------------------------------- See also: RHSGeoJ2, El2RV --------------------------------------------------------------------------
CubeSat: Visualization/PlotOrbit Orbit: RHSOrbit/RHSGeoJ2 SC: BasicOrbit/El2RV SC: BasicOrbit/Period Common: Time/Date2JD
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