Definition in file HokieSatSimulation.h.
#include "Matrix.h"
#include "Rotation.h"
#include "CombinedNumericPropagator.h"
#include "RungeKuttaFehlbergIntegrator.h"
#include "Orbit.h"
#include "OrbitState.h"
#include "orbitmodels/TwoBodyDynamics.h"
#include "orbitstaterep/PositionVelocity.h"
#include "orbitframes/OrbitFrameIJK.h"
#include "Attitude.h"
#include "AttitudeState.h"
#include "AttitudeModels/QuaternionAngVelDynamics.h"
#include "CentralBody/EarthCentralBody.h"
#include "CentralBody/Models/TiltedDipoleMagneticModel.h"
#include "Disturbances/GravityFunctions.h"
#include "Disturbances/SimpleAerodynamicDisturbances.h"
#include "Plot.h"
#include "MathUtils.h"
Go to the source code of this file.
Functions | |
| NumericPropagator * | SetupPropagator () |
| Sets up a combined numeric propagator, RK4(5) integrator and tolerances. | |
| Environment * | SetupEnvironment (Attitude *pSatAttitude) |
| Creates an Earth environment with point-mass, two-body gravity, gravity-gradient torque, and a tilted-dipole magnetic field model. | |
| Orbit * | SetupOrbit () |
| Creates an initial orbit read in from a file. | |
| Attitude * | SetupAttitude () |
| Creates an initial attitude read in from a file. | |
| Vector | ControlTorques (Matrix CurrentAttState, Matrix DesAttState, double epoch, double count) |
| HokieSat magnetic controller algoritm. | |
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Sets up a combined numeric propagator, RK4(5) integrator and tolerances.
Definition at line 137 of file HokieSatSimulation.cpp. |
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Creates an Earth environment with point-mass, two-body gravity, gravity-gradient torque, and a tilted-dipole magnetic field model.
Definition at line 95 of file HokieSatSimulation.cpp. |
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Creates an initial orbit read in from a file.
Definition at line 159 of file HokieSatSimulation.cpp. |
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Creates an initial attitude read in from a file.
Definition at line 188 of file HokieSatSimulation.cpp. |
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HokieSat magnetic controller algoritm.
Definition at line 30 of file AttitudeSimulatorServer.cpp. |
1.3