Path: Interplanetary/RHSFunctions
% Orbit dynamics with spherical harmonic models of the Earth and Moon gravity.
Includes a point mass sun model. Uses MoonV1 and SunV1 for ephemeris,
EarthRot, MoonRot, and AGravityC for the gravity models, and APlanet for the
sun perturbation.
Note that MoonV1 and SunV1 are low accuracy ephemeris models. For actual
mission planning you will need to use more accurate solar and lunar
ephemerides. In addition, you may need more accurate moon and earth rotation
models. These models are suitable for mission design since the required
delta-Vs won't change much but timing will. In addition, if you compare
results using this model to models with different ephemerides, the results
will not match.
Designed to be called by ode113. See also EarthMoonSunSim.
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Form:
varargout = FEarthMoonSun( t, x, flag, d )
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Inputs
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t Time (sec)
x (:,1) The state vector [r;v]
d (.) Data structure
.mass (1,1) Mass
.force (3,1) External force
.earth (1,1)
.mu (1.1) Gravitational potential
.nZ (1.1) Number of zonal harmonics
.nT (1.1) Number of tesseral harmonics
.s (:,:) S terms
.c (:,:) C terms
.j (:) m = 0 terms
.a (1.1) Planet radius
.moon (1,1)
.mu (1.1) Gravitational potential
.nZ (1.1) Number of zonal harmonics
.nT (1.1) Number of tesseral harmonics
.s (:,:) S terms
.c (:,:) C terms
.j (1,:) m = 0 terms
.a (1.1) Planet radius
.jDStart
.muSun
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Outputs
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vargout (:,:) Depends on flag
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LunarMissions: LunarEphemeris/MoonRot Orbit: OrbitMechanics/AGravityC Orbit: OrbitMechanics/APlanet SC: Ephem/EarthRot SC: Ephem/MoonV1 SC: Ephem/SunV1 Common: Time/JD2T
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