HokieSatSimulation.cpp File Reference

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Detailed Description

Demonstrates the use of Open-SESSAME for simulating HokieSat.

Author:

Author

nilspace

Version:

Revision

1.4

Date:

Date

2003/06/12 23:05:55

Definition in file HokieSatSimulation.cpp.

#include "HokieSatSimulation.h"

Go to the source code of this file.

Functions
int	main ()
	Main operating function for HokieSat simulation.
Environment *	SetupEnvironment (Attitude *pSatAttitude)
	Creates an Earth environment with point-mass, two-body gravity, gravity-gradient torque, and a tilted-dipole magnetic field model.
NumericPropagator *	SetupPropagator ()
	Sets up a combined numeric propagator, RK4(5) integrator and tolerances.
Orbit *	SetupOrbit ()
	Creates an initial orbit read in from a file.
Attitude *	SetupAttitude ()
	Creates an initial attitude read in from a file.
Vector	ControlTorques (const ssfTime &_currentTime, const OrbitState &_currentOrbitState, const AttitudeState &_currentAttitudeState, const EnvFuncParamaterType &_parameterList)

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Function Documentation

int main (   )

Main operating function for HokieSat simulation. Author: Andrew Turner Breaks down all object initializations into seperate functions. Definition at line 19 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. Examples: testDynamics.cpp, and testPropagation.cpp. Definition at line 95 of file HokieSatSimulation.cpp.

NumericPropagator * SetupPropagator (   )

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

Orbit * SetupOrbit (   )

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

Attitude * SetupAttitude (   )

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

Vector ControlTorques (  const ssfTime &  _currentTime, const OrbitState &  _currentOrbitState, const AttitudeState &  _currentAttitudeState, const EnvFuncParamaterType &  _parameterList )

Definition at line 220 of file HokieSatSimulation.cpp.

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