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] --------------------------------------------------------------------------
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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