Path: Orbit/OrbitMechanics

% Finds the inclination rate and orbit normal vector.

 Computes the inclination change rate and orbit normal vector. This
 shows where in the orbit inclination changes fastest with a normal

 Type InclinationRate for a demo.
   [dI, uN, dIMax] = InclinationRate( x, mu )

   x     (6,:)  [r;v]
   mu    (1,1) Gravitational potential (km^3/s^2)

   dI    (1,:) Inclination rate (rad/sec)
   uN    (3,:) Orbit normal
   dIMax (1,1) Maximum inclination rate (rad/sec)

   Reference: 	Robert Falck and Leon Gefert," A Method of Efficient 
               Inclination Changes for Low-Thrust Spacecraft," 
               Astrodynamics Specialist Conference and Exhibit,
               Monterey, CA, United States, 2002.


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/M2Nu
SC: BasicOrbit/M2NuPb
SC: BasicOrbit/Nu2E
SC: BasicOrbit/Nu2M
SC: BasicOrbit/Period
SC: BasicOrbit/RV2El
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
Math: Linear/Unit

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