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SUPPORT SITE |
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SUPPORT SITE |
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Path: Orbit/RHSOrbit
% High fidelity orbit model designed to work with ode113.
Inputs to this function are in the data structure d
1. The primary planet about which the spacecraft is orbiting
2. Julian date in days
3. Models:
Thrust model
Solar Pressure model
Aerodynamic model
Each model has three inputs
1. Flag (1 == on)
2. Tag to the GUI (see the example functions)
3. Function name
4. Propagate earth fixed flag (1 == true)
5. Propagate ECI reference to earth fixed at start (1 == true)
6. Data structure for the stopping condition (not needed if you aren't using
stopping conditions.
7. Number of tesseral and sectoral harmonics
8. Number of zonal (0,2,3, ...)
9. Planetary accelerations on (for the earth/moon/sun system only)
10. Gravity model data structure
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Form:
vargout = FOrbHF2( t, x, flag, d )
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Inputs
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t Time
x (6,1) The state vector [x;y;z;dx/dt;dy/dt;dz/dt]
flag (1,:) Flags for ode113
d (1,1) Data structure
.planet (1,:) Planet name string
.jD (1,1) Julian date (days)
.thrustModelOn (1,1) Thrust function flag
.thrustFunction (1,:) Thrust function name
.thrustFunctionTag (1,1) Thrust function tag
.solarModelOn (1,1) Solar function flag
.solarFunction (1,:) Solar function name
.solarFunctionTag (1,1) Solar function tag
.aeroModelOn (1,1) Aero function flag
.aeroFunction (1,:) Aero function name
.aeroFunctionTag (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
.planetaryDisturbancesOn (1,1) Turn on planetary disturbances for earth/moon/sun system
.gravityModel (1,1)
.s (36,36) S terms
.c (36,36) C terms
.j (36) m = 0 terms
.mu Gravitational parameter (km^3/sec^2)
.a Earth radius
.name Planet name
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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 Common: Transform/RPhiTheta2Cart Math: Linear/Mag Orbit: OrbitMechanics/AGravity Orbit: OrbitMechanics/PlanetaryAccelerations Orbit: OrbitPropagator/StoppingConditions SC: BasicOrbit/FOrbCart SC: Ephem/ECIToPlanet SC: Ephem/SunV1
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