Path: Orbit/OrbitMechanics
% Propagate an ECI state into the future with the J2 perturbation. Uses FOrbCartH with the GEMT1.geo Earth gravity model, specifying only the second zonal harmonic, nN = 2, nM = 0. -------------------------------------------------------------------------- Form: x = J2Prop( x0, jD, time, gM, showWaitBar ) -------------------------------------------------------------------------- ------ Inputs ------ x0 (6,1) Initial state [km; km/s] jD (1,1) Initial Julian Date [JD] time (1,:) Time vector [sec] gM (.) Gravity Model showWaitBar (1,1) Flag. Set to 1 to show wait bar. Default 0. ------- Outputs ------- x (6,:) Time history of ECI states [km; km/s] --------------------------------------------------------------------------
Orbit: GravityModels/LoadGravityModel Orbit: OrbitMechanics/J2OrbitEffects Orbit: RHSOrbit/FOrbCartH SC: BasicOrbit/El2RV SC: BasicOrbit/Period SC: BasicOrbit/RV2El Common: Graphics/Plot3D Common: Time/Date2JD Math: Integration/RK45
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