Path: Interplanetary/OrbitInsertion
% Starting true anomaly to reach a true anomaly in time t Utilizes fminbnd to find the solution. Type TrueAnomalyStartHyperbola for a demo in lunar orbit. -------------------------------------------------------------------------- Form: nu1 = TrueAnomalyStartHyperbola(a,e,t,nu2,mu) -------------------------------------------------------------------------- ------ Inputs ------ a (1,1) Semi-major axis e (1,1) Eccentricity t (1,1) Time of flight nu2 (1,1) True anomaly (rad) mu (1,1) Gravitational parameter ------- Outputs ------- nu1 (1,1) True anomaly (rad) --------------------------------------------------------------------------
Orbit: OrbitMechanics/TimeOfFlightHyperbola
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