FOrbKF:

Path: SpacecraftEstimation/OrbitEstimation

% Computes the right-hand-side of the orbit equations for OrbitKalmanFilter. 
 Low-fidelity mode computes about a mass point, high-fidelity mode uses 
 nonlinear orbit equations, planetary perturbations and modeled forces.
 Includes an onboard clock model.
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   Form:
   xDot = FOrbKF( x, t, d )
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   ------
   Inputs
   ------
   x            (n,1)     The state vector [r;v] or [r;v;b;f;...]
   t                      Time
   d            (1,1)     Data structure*
                          .highFidelity        (1,1)   High fidelity flag
                          .planetaryOn         (1,1)   Planetary accelerations flag
                          .forcesOn            (1,1)   Disturbance force modeling
                          .jD                  (1,1)   Julian date
                          .nZonal              (1,1)   Number of zonal harmonics
                          .nTess               (1,1)   Number of tesseral harmonics
                          .gravityModel        (1,1)   Gravity model struct
                          .aExt                (3,1)   External acceleration, ex. thruster firings
                          * Can be left empty for low-fidelity mode

   -------
   Outputs
   -------
   xDot         (n,1)     The derivative of the state vector

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Children:

AC: ACData/ACTConstants
Common: CommonData/Constants
Common: CommonData/SwooshWatermark
Common: CommonData/xSplashSmall
Common: Database/Constant
Common: General/CellToMat
Common: General/DeBlankLT
Common: General/DeleteCell
Common: General/DispWithTitle
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/Mesh2
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PltStyle
Common: Graphics/XLabelS
Common: Graphics/YLabelS
Common: Graphics/ZLabelS
Common: Time/DTSToDTA
Common: Time/Date2JD
Common: Time/JD2000
Common: Time/JD2T
Common: Time/JDToMidnight
Common: Time/T2JD
Math: Linear/DupVect
Math: Linear/Factorl
Math: Linear/Mag
Math: Linear/Unit
Math: MathUtils/R2P5
Math: Trigonometry/CosD
Math: Trigonometry/SinD
Orbit: GravityModels/LoadGEM
Orbit: GravityModels/NormalizationMatrix
Orbit: GravityModels/UnnormalizeGravity
Orbit: OrbitMechanics/AGravityC
Orbit: OrbitMechanics/APlanet
Orbit: OrbitMechanics/PlanetaryAccelerations
SC: BasicOrbit/OrbRate
SC: BasicOrbit/RV2A
SC: Ephem/ECIToPlanet
SC: Ephem/EOfE
SC: Ephem/EarthNut
SC: Ephem/EarthPre
SC: Ephem/EarthRot
SC: Ephem/GMSTime
SC: Ephem/MSidDay
SC: Ephem/MoonRot
SC: Ephem/MoonV1
SC: Ephem/Moons
SC: Ephem/NutDelta
SC: Ephem/ObOfE
SC: Ephem/SunV1
SC: Ephem/TruEarth
SC: SCData/sCTConstants
SC: SCMat/GEMT1

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