Path: Orbit/OrbitManeuver
% Computes the heliocentric departure vector for a spacecraft.
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Form:
b = VDA( d )
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Inputs
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d (:) Input data structure
d.rInjection (1,:) Injection radius
d.planet (1,:) Planet name
d.jD (1,1) Julian date
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Outputs
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b (:) Data structure
.v (3,1) Departure velocity
.dV (1,1) Delta V
.el (1,6) Elements
.
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SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: Ephem/Planets SC: Ephem/SolarSys Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TextS Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/JD2T Math: Linear/DupVect
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