|
SUPPORT SITE |
|
|
|
SUPPORT SITE |
|
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. Options: 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. -------------------------------------------------------------------------- Form: [rP, vP] = RVOrbHF( r, v, jD, options, t, aExt, tol, s, c, j, mu, a ) -------------------------------------------------------------------------- ------ Inputs ------ 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 ------- Outputs ------- 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
Back to the Orbit Module page