Path: Orbit/OrbitPropagator
% High fidelity orbit model designed to work with ode113.
Called by the OrbitPropagator GUI. Uses AGravityC. Uses ECIToPlanet with
high-fidelity option for the Earth using TruEarth. Selects atmosphere model
based on input.
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Form:
vargout = FOrbHFOP( t, x, flag, d )
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Inputs
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t (1,1) Time
x (6,1) The state vector [x;y;z;dx/dt;dy/dt;dz/dt]
flag (1,:) Event flag for ode113
d (.) Data structure
.planet (1,:) Planet name
.jD (1,1) Julian date
.thrustModelOn (1,1) Thrust function flag
.thrustFunction (*) Thrust function name/handle
.thrustFunctionTag (1,1 Thrust function tag
.solarModelOn (1,1) Solar function flag
.solarFunction (*) Solar function name/handle
.solarFunctionTag (1,1) Solar function tag
.aeroModelOn (1,1) Aero function flag
.atmosphere '' Type of atmosphere model
.densFunction (*) Aero function name/handle
.densFunctionTag (1,1) Aero function tag
.propagateEF (1,1) Propagate earth-fixed flag
.propagateECIR (1,1) Propagate ECIR flag
.stopping (:) Stopping condition data structure
.nTess (1,1) Number of tesseral harmonics
.nZonal (1,1) Number of zonal harmonics
.gravityModel (.) Gravity model
.s (:,:) S terms
.c (:,:) C terms
.j (:) m = 0 terms
.mu (1,1) Gravitational parameter (km^3/sec^2)
.a (1,1) Earth radius
.name (1,1) Planet name
.isNormalized (1,1) Boolean for normalization
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Outputs
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xDot (6,1) The state vector derivative [x;y;z;dx/dt;dy/dt;dz/dt]
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AerospaceUtils: AtmosphericCalculations/AtmDens1 AerospaceUtils: AtmosphericCalculations/AtmDens2 AerospaceUtils: Coord/EFToLatLonAlt Orbit: OrbitMechanics/AGravityC Orbit: OrbitMechanics/PlanetaryAccelerations Orbit: OrbitPropagator/StoppingConditions SC: BasicOrbit/FOrbCart SC: Ephem/ECIToPlanet SC: Ephem/SunV1
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