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Path: Orbit/RHSOrbit
% 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 (1,1) 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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Common: Time/JD2T Orbit: OrbitMechanics/AGravityC Orbit: OrbitMechanics/APlanet SC: Ephem/EarthRot SC: Ephem/MoonRot SC: Ephem/MoonV1 SC: Ephem/SunV1
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