LunarOrbitInsertion:

% Computes parameters for a lunar orbit insertion.

 Computes the total velocity change, the vector direction for the burn
 and the duration of the burn.

 Type LunarOrbitInsertion for a demo.
   
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	Form:
	[deltaV, uECI, tBurn] = LunarOrbitInsertion( hLunarOrbit, dR, dV, mI, uE, thrust )
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   ------
   Inputs
   ------
   hLunarOrbit	(1,1)	Perigee altitude
   dR          (3,1)	Relative position vector at start (km)
   dV          (3,1)	Relative velocity vector at start (km/s)
   mI          (1,1)	Initial mass (kg)
   uE          (1,1) Exhaust velocity (m/s)
   thrust      (1,1) Thrust (N)

   -------
   Outputs
   -------
   deltaV  (1,1)   Velocity change (km/s)
   uECI    (3,1)   Vector for burn
   tBurn   (1,1)   Burn duration (sec)

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Children:

Common: Database/Constant
Math: Linear/Mag
Math: Linear/Unit
Orbit: OrbitCoord/RARP2A
SC: BasicOrbit/VOrbit