Path: FormationFlying/Coord
% Generate LVLH transformation matrices
This function takes the position and velocity of a satellite in the ECI frame,
and returns the A and Adot matrices used for transformation to the LVLH frame.
They are used in the following equations:
rL = A*(r1-r0);
vL = A*(v1-v0) + Adot*(r1-r0);
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Form:
[A, Adot] = GetLVLHMats( ro, vo )
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Inputs
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ro (3,1) r, ECI frame
vo (3,1) v, ECI frame
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Outputs
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A (3,3) Rotation matrix (position)
Adot (3,3) Rotation matrix (velocity)
Equal to -cross( orbrate(mag(ro), A )
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SC: BasicOrbit/E2M SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/RV2El Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/Cross Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit
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