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SUPPORT SITE |
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SUPPORT SITE |
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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. Form: dV = DVOrbitDrag( el, nu, b, planet ) ------------------------------------------------------------------------ ------ Inputs ------ 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 ------- Outputs ------- 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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