Path: Orbit/OrbitCoord
% Compute inertial position and velocity given circular orbit elements -------------------------------------------------------------------------- Form: [r,v] = CircularOrbitState( R, inc, ra, M, n ); -------------------------------------------------------------------------- ------ Inputs ------ R (1,:) Distance from planet center inc (1,1) Inclination [rad] ra (1,1) Right ascension [rad] M (1,:) Mean anomaly [rad] n (1,:) Orbit rate ------- Outputs ------- lat (1) Latitude [deg] lon (1) Longitude [deg] alt (1) Altitude [km] --------------------------------------------------------------------------
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