Path: Orbit/OrbitSim

% High fidelity orbit simulation with drag and planetary perturbations.

   ? Spherical harmonic earth gravitational model
   ? Sun and moon
   ? Atmospheric drag

   If t is omitted one orbit will be computed with 100 points.
   If jD is omitted a Keplerian orbit will be generated.
   If options is omitted the simplified model will be used.

   If no outputs are specified it will plot the orbit and the deviation
   from a Keplerian orbit.


   Highest zonal harmonic    - 0 through n
   Highest tesseral harmonic - 0 through m
   Sun                       - 0 equals off, 1 equals on
   Moon                      - 0 equals off, 1 equals on
   Drag                      - CD*A/m

   Since version 1.
   [rP, vP] = RVOrbHF( r, v, jD, options, t, aExt, tol, s, c, j, mu, a )

   r             (3,1)  Initial position vector (km)
   v             (3,1)  Initial velocity vector (km)
   jD                   Julian date of the start
   options         (5)  [Highest zonal harmonic,Highest tesseral harmonic,Sun,Moon,Drag] 
   t               (n)  Times at which the new r and v are to be computed?need not be uniform
   aExt        (3,n|1)  External acceleration vector [x;y;z] ECI
   tol                  Tolerance for the integration
   s           (36,36)  S terms
   c           (36,36)  C terms
   j              (36)  m = 0 terms
   mu                   Gravitational parameter (km^3/sec^2)
   a                    Earth radius

   rP                  Position vectors at times t
   vP                  Velocity vectors at times t



Common: Graphics/AxesCart
Common: Graphics/Axis3D
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/TimeLabl
Common: Graphics/XLabelS
Common: Graphics/YLabelS
Common: Graphics/ZLabelS
Common: Time/JD2000
Math: Integration/RK45
Math: Linear/DupVect
Orbit: GravityModels/LoadGEM
Orbit: OrbitMechanics/RVOrbGen
SC: BasicOrbit/E2M
SC: BasicOrbit/Nu2E
SC: BasicOrbit/RV2El
SC: Ephem/SunV1

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