TimeOfFlightHyperbola:

Path: Orbit/OrbitMechanics

% Time of flight in a hyperbola
 This function gives the time of flight between two true anomalies.
 This function only works for hyperbolas. It will throw an error
 if either true anomaly is outside the maximum true anomaly for the 
 hyperbola.

 Type TimeOfFlightHyperbola for a demo in lunar orbit.

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   Form:
   t = TimeOfFlightHyperbola(a,e,nu1,nu2,mu)
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   ------
   Inputs
   ------
   a   (1,1)   Semi-major axis
   e  	(1,1)   Eccentricity
   nu1	(1,1)   Initial true anomaly (rad)
   nu2	(1,:)   Final true anomaly (rad)
   mu  (1,1)   Gravitational parameter

   -------
   Outputs
   -------
   t   (1,1)   Time of flight

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   Reference: http://www.braeunig.us/space/orbmech.htm equation 4.86
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