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Path: Orbit/RHSOrbit
% High fidelity orbit model right-hand-side.
Includes higher harmonics of the earth's gravitational field and sun and
moon accelerations as options.
The drag option = drag coefficient * area / mass where the area is in m^2
The sun option = area / mass
The moon option is 0 or 1
See also AGravity, APlanet, AtmDens2, SolarF, and FOrb.
Since version 1.
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Form:
xDot = FOrbHF( x, t, options, jD, aExt, mu, s, c, j, a )
xDot = FOrbHF( t, x, options, jD, aExt, mu, s, c, j, a ) (for ode113)
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Inputs
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x (6,1) The state vector [x;y;z;dx/dt;dy/dt;dz/dt]
t Time
options (5) [Highest zonal harmonic,Highest tesseral harmonic,
Sun,Moon,Drag]
jD Julian date
aExt (3) External acceleration vector [x;y;z] ECI
mu Spherical gravitational potential
s (36,36) S terms
c (36,36) C terms
j (36) m = 0 terms
a Earth radius
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Outputs
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xDot (6,1) The derivative of the state state vector
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AerospaceUtils: AtmosphericCalculations/AtmDens2 AerospaceUtils: AtmosphericCalculations/AtmJ70 AerospaceUtils: Coord/ECIToEF Common: Time/JD2T Math: Linear/Cross Math: Linear/Mag Math: Linear/Unit Orbit: OrbitMechanics/AGravity Orbit: OrbitMechanics/APlanet SC: BasicOrbit/FOrbCart SC: Disturbances/SolarF SC: Ephem/Eclipse SC: Ephem/MoonV1 SC: Ephem/SunV1
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