simpleOrbit.cpp File Reference

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Detailed Description

Nonlinear Orbit EOM.

Author:

Author

jayhawk_hokie

Version:

Revision

1.3

Date:

Date

2006/08/25 19:14:17

Definition in file simpleOrbit.cpp.

#include <iostream.h>
#include <iomanip.h>
#include <fstream.h>
#include "attitude/AttitudeModels/QuaternionAngVelDynamics.h"
#include "utils/RungeKuttaIntegrator.h"
#include "datahandling/History.h"
#include "orbit/orbitstaterep/Keplerian.h"
#include <dsacssinterface.h>

Include dependency graph for simpleOrbit.cpp:

Go to the source code of this file.

Defines
#define	PI   M_PI
Functions
Vector	NullFunctor (const ssfTime &_pSSFTime, const OrbitState &_pOrbitState, const AttitudeState &_pAttitudeState)
int	main ()
Variables
const char *	fileName = "DSACSSConfig.xml"
const char *	spacecraft = "SPACECRAFT_1"
const char *	physicalProperties = "PHYSICAL_PROPERTIES"
const char *	attitudeProperties = "ATTITUDE_PROPERTIES"
const char *	hardwareProperties = "HARDWARE_PROPERTIES"
const char *	initialConditions = "INITIAL_CONDITIONS"
const char *	magnetometer = "MAGNETOMETER"
const char *	attribute = "value"

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Define Documentation

#define PI   M_PI

Definition at line 30 of file simpleOrbit.cpp. Referenced by OrbitController::ECEF2ECI(), OrbitObserver::ECEF2NEDVelocity(), OrbitController::ECEF2NEDVelocity(), VisualVector::GetVectorMeasurement(), main(), O_SESSAME::OsculatingOrbitalElements::Mapping(), OrbitObserver::NED2ECEFVelocity(), OrbitController::NED2ECEFVelocity(), O_SESSAME::Keplerian::ReadTwoLineElementSet(), VisualVector::RotationAngleFunc(), and O_SESSAME::Keplerian::SetPositionVelocity().

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Function Documentation

int main (   )

Definition at line 50 of file simpleOrbit.cpp. References attitudeProperties, attribute, checkLoadFile(), checkResponse(), TiXmlHandle::Child(), O_SESSAME::Deg2Rad(), TiXmlHandle::Element(), fileName, TiXmlHandle::FirstChild(), O_SESSAME::Keplerian::GetArgPerigee(), O_SESSAME::Keplerian::GetEccentricity(), O_SESSAME::Keplerian::GetInclination(), O_SESSAME::Keplerian::GetLongAscNode(), O_SESSAME::Keplerian::GetMeanMotion(), O_SESSAME::Keplerian::GetSemimajorAxis(), O_SESSAME::AttitudeState::GetState(), O_SESSAME::Keplerian::GetTrueAnomaly(), initialConditions, O_SESSAME::RungeKuttaIntegrator::Integrate(), TiXmlDocument::LoadFile(), O_SESSAME::Matrix, NullFunctor(), physicalProperties, PI, O_SESSAME::DirectionCosineMatrix::Set(), O_SESSAME::AttitudeState::SetAngularVelocity(), O_SESSAME::RungeKuttaIntegrator::SetNumSteps(), O_SESSAME::AttitudeState::SetRotation(), simulatorInertia(), spacecraft, O_SESSAME::tick(), O_SESSAME::Vector, and O_SESSAME::VectorIndexBase.

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

Definition at line 44 of file simpleOrbit.cpp. References O_SESSAME::Vector.

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Variable Documentation

const char* attitudeProperties = "ATTITUDE_PROPERTIES"

Definition at line 37 of file simpleOrbit.cpp. Referenced by main().

const char* attribute = "value"

Definition at line 41 of file simpleOrbit.cpp. Referenced by TiXmlElement::CopyTo(), and main().

const char* fileName = "DSACSSConfig.xml"

Definition at line 33 of file simpleOrbit.cpp. Referenced by checkLoadFile(), and main().

const char* hardwareProperties = "HARDWARE_PROPERTIES"

Definition at line 38 of file simpleOrbit.cpp. Referenced by main().

const char* initialConditions = "INITIAL_CONDITIONS"

Definition at line 39 of file simpleOrbit.cpp. Referenced by main().

const char* magnetometer = "MAGNETOMETER"

Definition at line 40 of file simpleOrbit.cpp. Referenced by main().

const char* physicalProperties = "PHYSICAL_PROPERTIES"

Definition at line 36 of file simpleOrbit.cpp. Referenced by main().

const char* spacecraft = "SPACECRAFT_1"

Definition at line 35 of file simpleOrbit.cpp. Referenced by main().

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