Path: FormationFlying/Utility
% Compute the future true anomaly (unwrapped) at the specified number of orbits after the initial true anomaly. Since version 7. -------------------------------------------------------------------------- ------ Inputs ------ e (1) Eccentricity nu0 (1) Initial true anomaly [rad] nOrb (1,:) Time vector from initial true anomay [orbit periods] ------- Outputs ------- nuF (1,:) Vector of final true anomalies --------------------------------------------------------------------------