Path: Orbit/OrbitMechanics
% Calculates orbital elements and perigee radius for a planetary flyby.
Since version 2.
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Form:
[el, rP] = Flyby( vA, vD, vP, muP )
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Inputs
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vA (3,1) Approach velocity of the spacecraft
vD (3,1) Departure velocity of the spacecraft
vP (3,1) Velocity of the planet
muP (1,1) Gravitational parameter of the encountered planet
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Outputs
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el (:) Elements in the planet frame
el.a, el.i, el.w, el.W, el.e, el.M
rP (1,1) Radius of perigee
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Orbit: OrbitCoord/SLR Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/CP2I SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/Axis3D Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Linear/Cross Math: Linear/DupVect Math: Linear/Mag
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