HokieSatSimulation.h File Reference

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Detailed Description

Include files and function prototypes for HokieSat attitude simulation example.

Author:

Author

cakinli

Version:

Revision

1.1.1.1

Date:

Date

2005/04/26 17:41:00

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"

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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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Function Documentation

Vector ControlTorques (  Matrix  CurrentAttState, Matrix  DesAttState, double  epoch, double  count )

HokieSat magnetic controller algoritm. Author: Hye-Young Kim Definition at line 30 of file AttitudeSimulatorServer.cpp. References B, O_SESSAME::eye(), O_SESSAME::Matrix, O_SESSAME::skew(), and O_SESSAME::Vector. Referenced by main().

Attitude* SetupAttitude (   )

Creates an initial attitude read in from a file. Definition at line 188 of file HokieSatSimulation.cpp.

Environment* SetupEnvironment (  Attitude *  pSatAttitude  )

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. References _, O_SESSAME::Environment::AddForceFunction(), O_SESSAME::EnvFunction::AddParameter(), O_SESSAME::Environment::AddTorqueFunction(), O_SESSAME::CentralBody::GetGravitationalParameter(), O_SESSAME::Attitude::GetParameters(), GravityForceFunction(), GravityGradientTorque(), O_SESSAME::Matrix, O_SESSAME::Environment::SetCentralBody(), and O_SESSAME::CentralBody::SetMagneticModel().

Orbit* SetupOrbit (   )

Creates an initial orbit read in from a file. Definition at line 159 of file HokieSatSimulation.cpp.

NumericPropagator* SetupPropagator (   )

Sets up a combined numeric propagator, RK4(5) integrator and tolerances. Definition at line 137 of file HokieSatSimulation.cpp.

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