Path: CubeSat/Simulation
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Multispacecraft orbit model designed to work with ode113.
You can include aerodynamic, radiation pressure and thrust models. Sun,
earth, and moon perturbations are computed if the planet (Earth or
Moon) is given. Uses SunV1 and MoonV1 for ephemeris.
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Form:
d = FOrbitMultiSpacecraft % data structure
xDot = FOrbitMultiSpacecraft( t, x, d )
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Inputs
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t Time
x (7*n,1) The state vector [r1;v1;m1;r2;v2;m2;...]
d (:) Data structure array
.jD0 (1,1) Julian date at start
This is only needed for planetary disturbances
and if a gravity model is entered:
.planet (1,:) Planet name, 'earth', 'moon'
These are optional:
.thrusterModel (1,:) Thrust function handle
.thrusterData (.) Thrust data structure
.opticalModel (1,:) Optical function handle
.aeroModel (1,:) Aero function handle
.surfData (.) Surface data structure
.gravityModel (.) Gravity model structure
The following are only needed if you want J70, otherwise
AtmDens2 will be used.
.atm.aP (1,1) Geomagnetic index 6.7 hours before the computation
.atm.f (1,1) Daily 10.7 cm solar flux (e-22 watts/m^2/cycle/sec)
.atm.fHat (1,1) 81-day mean of f (e-22 watts/m^2/cycle/sec)
.atm.fHat400 (1,1) fHat 400 days before computation date
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Outputs
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xDot (7*n,1) The state vector derivative [v1;r1Dot;m1Dot...]
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See also CubeSatEnvironment, ECIToPlanet, AGravityC, FOrbCart,
PlanetaryAccelerations CubeSatRadiationPressure, CubeSatAero,
CubeSatPropulsion
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AeroUtils: AtmosphericCalculations/AtmDens2 AeroUtils: AtmosphericCalculations/AtmJ70 Common: Database/Constant Common: Quaternion/QZero Common: Time/JD2000 CubeSat: Utilities/CubeSatAttitude Math: Linear/Mag Math: Linear/Skew Math: Linear/Unit Orbit: OrbitMechanics/AGravityC Orbit: OrbitMechanics/APlanet SC: BasicOrbit/FOrbCart SC: Ephem/ECIToPlanet SC: Ephem/Eclipse SC: Ephem/MoonV1 SC: Ephem/SunV1
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