testPropagation.cpp File Reference

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Detailed Description

Sample of an orbit and attitude propagation using components of the SSF.

Author:

Author

cakinli

Version:

Revision

1.1.1.1

Date:

Date

2005/04/26 17:41:00

Definition in file testPropagation.cpp.

#include "Matrix.h"
#include "Rotation.h"
#include "Attitude.h"
#include "Orbit.h"
#include "CombinedNumericPropagator.h"
#include "RungeKuttaIntegrator.h"
#include "orbitmodels/TwoBodyDynamics.h"
#include "EarthCentralBody.h"
#include "OrbitState.h"
#include "AttitudeState.h"
#include "orbitstaterep/PositionVelocity.h"
#include "orbitframes/OrbitFrameIJK.h"
#include "Plot.h"

Include dependency graph for testPropagation.cpp:

Go to the source code of this file.

Functions
NumericPropagator *	SetupPropagator ()
	Sets up a combined numeric propagator, RK4(5) integrator and tolerances.
Environment *	SetupEnvironment ()
Orbit *	SetupOrbit ()
	Creates an initial orbit read in from a file.
Attitude *	SetupAttitude ()
	Creates an initial attitude read in from a file.
void	myOrbitStateConvFunc (const Matrix &_meshPoint, OrbitState &_convertedOrbitState)
void	myAttitudeStateConvFunc (const Matrix &_meshPoint, AttitudeState &_convertedAttitudeState)
int	main ()
Vector	GravityForceFunction (const ssfTime &_currentTime, const OrbitState &_currentOrbitState, const AttitudeState &_currentAttitudeState, const EnvFuncParamaterType &_parameterList)
Vector	DragForceFunction (const ssfTime &_currentTime, const OrbitState &_currentOrbitState, const AttitudeState &_currentAttitudeState, const EnvFuncParamaterType &_parameterList)
Vector	AttituteDynamics (const ssfTime &_time, const Vector &_integratingState, Orbit *_Orbit, Attitude *_Attitude, const Matrix &_parameters, const Functor &_forceFunctorPtr)

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Function Documentation

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

Definition at line 225 of file testPropagation.cpp. References _, O_SESSAME::Functor::Call(), O_SESSAME::eye(), O_SESSAME::Attitude::GetStateObject(), O_SESSAME::Orbit::GetStateObject(), CAMmatrixBase::inverse(), O_SESSAME::Matrix, O_SESSAME::MatrixIndexBase, O_SESSAME::norm2(), O_SESSAME::skew(), O_SESSAME::Vector, and O_SESSAME::VectorIndexBase.

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

Definition at line 118 of file testPropagation.cpp. References _, O_SESSAME::OrbitState::GetState(), O_SESSAME::norm2(), O_SESSAME::Vector, and O_SESSAME::VectorIndexBase.

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

Definition at line 108 of file testPropagation.cpp. References _, O_SESSAME::OrbitState::GetState(), O_SESSAME::norm2(), O_SESSAME::Vector, and O_SESSAME::VectorIndexBase.

int main (   )

Definition at line 33 of file testPropagation.cpp. References _, O_SESSAME::ssfTime::GetSeconds(), O_SESSAME::AttitudeState::GetState(), O_SESSAME::OrbitState::GetState(), O_SESSAME::Attitude::GetStateObject(), O_SESSAME::Orbit::GetStateObject(), O_SESSAME::Matrix, O_SESSAME::MatrixIndexBase, O_SESSAME::Plot2D(), O_SESSAME::Plot3D(), O_SESSAME::NumericPropagator::Propagate(), O_SESSAME::Attitude::SetEnvironment(), O_SESSAME::Orbit::SetEnvironment(), O_SESSAME::Attitude::SetPropagator(), O_SESSAME::Orbit::SetPropagator(), SetupAttitude(), SetupEnvironment(), SetupOrbit(), SetupPropagator(), O_SESSAME::ssfSeconds, and O_SESSAME::tick().

void myAttitudeStateConvFunc (  const Matrix &  _meshPoint, AttitudeState &  _convertedAttitudeState )

void myOrbitStateConvFunc (  const Matrix &  _meshPoint, OrbitState &  _convertedOrbitState )

Attitude* SetupAttitude (   )

Creates an initial attitude read in from a file. Definition at line 188 of file HokieSatSimulation.cpp. References _, O_SESSAME::eye(), CAMmatrixBase::inverse(), O_SESSAME::Matrix, O_SESSAME::AttitudeState::SetAngularVelocity(), O_SESSAME::Attitude::SetDynamicsEq(), O_SESSAME::Attitude::SetParameters(), O_SESSAME::AttitudeState::SetRotation(), O_SESSAME::Attitude::SetStateConversion(), O_SESSAME::Attitude::SetStateObject(), and O_SESSAME::Vector. Referenced by main().

Environment* SetupEnvironment (   )

Orbit* SetupOrbit (   )

Creates an initial orbit read in from a file. Definition at line 159 of file HokieSatSimulation.cpp. References O_SESSAME::Orbit::SetDynamicsEq(), O_SESSAME::OrbitState::SetOrbitFrame(), O_SESSAME::OrbitState::SetState(), O_SESSAME::Orbit::SetStateConversion(), O_SESSAME::Orbit::SetStateObject(), O_SESSAME::OrbitState::SetStateRepresentation(), O_SESSAME::Vector, and O_SESSAME::VectorIndexBase. Referenced by main().

NumericPropagator* SetupPropagator (   )

Sets up a combined numeric propagator, RK4(5) integrator and tolerances. Definition at line 137 of file HokieSatSimulation.cpp. References O_SESSAME::CombinedNumericPropagator::SetAttitudeIntegrator(), O_SESSAME::CombinedNumericPropagator::SetOrbitIntegrator(), O_SESSAME::RungeKuttaFehlbergIntegrator::SetStepSizes(), and O_SESSAME::RungeKuttaFehlbergIntegrator::SetTolerance(). Referenced by main().

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