FOrbHFOP:

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.
--------------------------------------------------------------------------
   Form:
   vargout = FOrbHFOP( t, x, flag, d )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   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

   -------
   Outputs
   -------
   xDot	(6,1)     The state vector derivative [x;y;z;dx/dt;dy/dt;dz/dt]

--------------------------------------------------------------------------

Children:

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

Back to the Orbit Module page