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.
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Form:
DVOrbitDrag; % demo
dV = DVOrbitDrag( el, nu, b, planet )
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Inputs
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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
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Outputs
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dV (1,1) Total drag loss (km/s)
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AerospaceUtils: AtmosphericCalculations/AtmDens1 AerospaceUtils: AtmosphericCalculations/AtmDens2 Orbit: OrbitMechanics/Nu2M Orbit: OrbitMechanics/Period Orbit: OrbitSim/RVOrbGen Common: Database/Constant Common: Graphics/Plot2D Common: Graphics/TimeLabl Math: Linear/Mag
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