GetHillsMats:

Path: FormationFlying/Coord

% Get Hills 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
 Hills frame. They are used in the following equations:

   rH = A*(r1-r0);
   vH = A*(v1-v0) + Adot*(r1-r0);

--------------------------------------------------------------------------
   Form:
   [A, Adot] = GetHillsMats( r0, v0 )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   r0      (3,1)   Position ECI frame
   v0      (3,1)   Velocity ECI frame

   -------
   Outputs
   -------
   A       (3,3)   Rotation matrix (position)
   Adot	(3,3)   Rotation matrix (velocity)
                   Equal to -Cross( OrbRate(Mag(r0), A )

--------------------------------------------------------------------------

Children:

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

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