CoplanarOrbit:

Path: Orbit/OrbitManeuver

% Find a coplanar orbit with a different altitude
 Compute the new eccentricity and semimajor axis after adding the delta
 altitude to both the apogee and perigee.
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   Form:
   el2 = CoplanarOrbit( el1, deltaH )
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   ------
   Inputs
   ------
   el1    (1,6) Element set [a i W w e M]
   deltaH (1,1) Altitude change

   -------
   Outputs
   -------
   el2    (1,6) Element set [a i W w e M]

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Children:

Orbit: OrbitCoord/AE2RPRA
Orbit: OrbitCoord/RPRA2AE
Orbit: OrbitMechanics/RVOrbGen
Common: Graphics/Plot2D
Common: Graphics/TimeLabl
Math: Linear/Mag

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