ManeuverDuration:

Path: Orbit/OrbitManeuver

% Compute maneuver duration given constant thrust.
 This routine computes maneuver duration given the desired velocity
 change, exhaust velocity, initial mass and thrust.

 Type ManeuverDuration for a demo.

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   Form:
   [t, mP] = ManeuverDuration( mI, dV, uE, thrust )
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   ------
   Inputs
   ------
   mI      (1,1) Initial mass (kg)
   dV      (1,1) Desired change in velocity (km/s)
   uE      (1,1) Exhaust velocity  (km/s)
   thrust  (1,1) Thrust (N)

   -------
   Outputs
   -------
   t      	(1,1) Maneuver duration (s)
   mP      (1,1) Fuel mass (kg)

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Children:

Common: Graphics/TimeLabl

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