Path: Orbit/OrbitControl
% Perform targeting using the Lambert algorithm.
Takes the states of two spacecraft at an epoch and a transfer time
and performs Lambert targeting. Returns the delta-V and a flag for the
long or short transfer.
See also LambertTOF.
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Form:
[dV,tM,okFlag] = DVTarget(r1,v1,r2,v2,dT)
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Inputs
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r1 (3,1) Position of spacecraft 1 (km)
v1 (3,1) Velocity of spacecraft 1 (km/s)
r2 (3,1) Position of spacecraft 2
v2 (3,1) Velocity of spacecraft 2
dT (1) Transfer time (s)
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Outputs
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dV (:) Struct of delta-Vs
.a (3,1) First delta-V (km/s)
.b (3,1) Second delta-V (km/s)
tM (1) Flag: +/-1 for short/long transfer
okFlag (1) Flag: 1 if maneuver is OK, 0 if hits the Earth
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Orbit: OrbitMechanics/LambertTOF SC: BasicOrbit/E2M SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/RV2El SC: BasicOrbit/RVFromKepler Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/Plot3D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Linear/Cross Math: Linear/Dot Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit
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