brett_test.cpp File Reference

#include <iostream.h>
#include <iomanip.h>
#include "Rotation.h"
#include "Matrix.h"
#include "Attitude.h"
#include "LinearInterpolator.h"
#include "RungeKuttaIntegrator.h"

Go to the source code of this file.

Functions
Vector	NullFunctor (const ssfTime &_pSSFTime, const OrbitState &_pOrbitState, const AttitudeState &_pAttitudeState)
Vector	EugeneDynamics (const ssfTime &_time, const Vector &_integratingState, Orbit *_Orbit, Attitude *_Attitude, const Matrix &_parameters, const Functor &_forceFunctorPtr)
Vector	AttituteDynamics (const ssfTime &_time, const Vector &_integratingState, Orbit *_Orbit, Attitude *_Attitude, const Matrix &_parameters, const Functor &_forceFunctorPtr)
	Dynamic and Kinematic attitude equations using quaternion and angular velocities.
int	main ()
	Main operating function for HokieSat simulation.

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Function Documentation

Vector NullFunctor (  const ssfTime &  _pSSFTime, const OrbitState &  _pOrbitState, const AttitudeState &  _pAttitudeState )

Examples: testAttitudeIntegration.cpp. Definition at line 11 of file brett_test.cpp.

Vector EugeneDynamics (  const ssfTime &  _time, const Vector &  _integratingState, Orbit *  _Orbit, Attitude *  _Attitude, const Matrix &  _parameters, const Functor &  _forceFunctorPtr )  [static]

Definition at line 16 of file brett_test.cpp.

Vector AttituteDynamics (  const ssfTime &  _time, const Vector &  _integratingState, Orbit *  _pOrbit, Attitude *  _pAttitude, const Matrix &  _parameters, const Functor &  _forceFunctorPtr )  [static]

Dynamic and Kinematic attitude equations using quaternion and angular velocities. Examples: testAttitudeIntegration.cpp, and testPropagation.cpp. Definition at line 42 of file brett_test.cpp.

int main (   )

Main operating function for HokieSat simulation. Author: Andrew Turner Breaks down all object initializations into seperate functions. Definition at line 67 of file brett_test.cpp.

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