Path: Orbit/OrbitMechanics

% Compute the drag loss over an orbit arc in planetary orbit.
 All the built in constants are for the Earth. If no outputs are 
 specified it will plot the drag acceleration. This function assumes
 that the velocity remains that of the unperturbed orbit. This 
 approximation is only valid when the drag loss is low or there is
 a drag makeup system in operation. The planets are limited by
 the ones available in AtmDens1 which are

  'mercury', 'venus', 'mars', 'pluto', 'europa'

 If Earth is selected the function uses the more accurate AtmDens2.
 nu should be between -pi and pi.

 Type DVOrbitDrag for an example of slightly elliptical orbits around
 Earth and Mars.
 dV = DVOrbitDrag( el, nu, b, planet )

 el      (1,6)	[a i w W e M] w is argument of perigee, W ascending node
 nu      (1,2)	True anomaly [start finish] 
 b       (1,1) Ballistic coefficient drag coefficient*area/mass (m^2/kg)
 planet  (1,1) Planet name

 dV	(1,1)	Total drag loss (km/s)



AerospaceUtils: AtmosphericCalculations/AtmDens1
AerospaceUtils: AtmosphericCalculations/AtmDens2
Common: Database/Constant
Common: Graphics/Plot2D
Common: Graphics/TimeLabl
Math: Linear/Mag
Orbit: OrbitMechanics/RVOrbGen
SC: BasicOrbit/Nu2M
SC: BasicOrbit/Period

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