HokieSatSimulation.cpp File Reference

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Detailed Description

Demonstrates the use of Open-SESSAME for simulating HokieSat.

Author:

Author

cakinli

Version:

Revision

1.1.1.1

Date:

Date

2005/04/26 17:41:00

Definition in file HokieSatSimulation.cpp.

#include "HokieSatSimulation.h"

Include dependency graph for HokieSatSimulation.cpp:

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

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

Definition at line 220 of file HokieSatSimulation.cpp. References O_SESSAME::Vector.

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. References _, O_SESSAME::AttitudeHistory::GetHistory(), O_SESSAME::OrbitHistory::GetHistory(), O_SESSAME::Attitude::GetHistoryObject(), O_SESSAME::Orbit::GetHistoryObject(), O_SESSAME::OrbitStateRepresentation::GetPositionVelocity(), O_SESSAME::ssfTime::GetSeconds(), O_SESSAME::AttitudeState::GetState(), O_SESSAME::Attitude::GetStateObject(), O_SESSAME::Orbit::GetStateObject(), O_SESSAME::OrbitState::GetStateRepresentation(), 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().

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 (  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.

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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