Todo List

Member O_SESSAME::ASCIIConverter::Export (const ConversionForm &_exportConvForm): figure out how to store & load matrix without storing the size in the text file.

Class O_SESSAME::Attitude: Verify attitude is inheritable. testAttitudeIntegration.cpp testPropagation.cpp

Member O_SESSAME::Attitude::~Attitude (): determine how to clean up the attitude pointers without leaving references hanging if(m_pEnvironment) delete m_pEnvironment; if(m_pPropagator) delete m_pPropagator;

Member O_SESSAME::Attitude::SetControlTorques (const Vector &_ControlTorques): add error checking

Member O_SESSAME::AttitudeHistory::AppendHistory (const vector< ssfTime > &_appendTime, const vector< AttitudeState > &_appendAttitudeState): figure out how to append a large chunk of one vector<> to another

Member O_SESSAME::AttitudeHistory::AppendHistory (const vector< ssfTime > &_appendTime, const vector< Rotation > &_appendRotation, const vector< Vector > &_appendAngVel): Determine if the multiple AppendHistory's can be combined in some smart way.

Member O_SESSAME::AttitudeHistory::GetState (const ssfTime &_requestedTime, Rotation &_returnRotation, Vector &_returnAngVelVector): implement better error handling strategy

Member O_SESSAME::AttitudeState::~AttitudeState (): delete AttitudeState data members

Member O_SESSAME::AttitudeState::SetAttitudeFrame (AttitudeFrame *_pNewAttitudeFrame): add conversion of Rotation to the new frame

Member O_SESSAME::AttitudeState::GetRotation2Orbital (const OrbitState &_orbState) const: Implement algorithm.

Member O_SESSAME::CentralBody::ReleaseReference (): Check how to verify the number of references & delete the object

Member O_SESSAME::CombinedNumericPropagator::~CombinedNumericPropagator (): figure out how to delete m_pIntegrator only when it is not being used

Member O_SESSAME::CombinedNumericPropagator::Propagate (const vector< ssfTime > &_propTime, const Vector &_orbitInitConditions, const Vector &_attInitConditions): Determine what prop times exist and what times are req'd to recalc

Member O_SESSAME::CombinedNumericPropagator::PropagateOrbit (const vector< ssfTime > &_propTime, const Vector &_initConditions)

determine if having vector<State> in Propagate is polymorphic

Append the requested time steps in the appropriate component history

Determine if the updated attitude & orbit should be set in Propagator

Member O_SESSAME::CombinedNumericPropagator::PropagateAttitude (const vector< ssfTime > &_propTime, const Vector &_initConditions): Append the requested time steps in the appropriate component history

Member O_SESSAME::DirectionCosineMatrix::GetEulerAngles (const int &_Sequence) const: Implement DCM::GetEulerAngles function

Member O_SESSAME::Environment::AddForceFunction (const EnvFunction &_forceFunc): Check to prevent overlapping force functions

Member O_SESSAME::Environment::AddTorqueFunction (const EnvFunction &_torqueFunc): Check to prevent overlapping torque functions

Class O_SESSAME::Functor: make Functors for variety of function types

Member O_SESSAME::Keplerian::SetPositionVelocity (const Vector &_Position, const Vector &_Velocity): implement Keplerian conversion functions

Member O_SESSAME::Keplerian::SetPositionVelocity (const Vector &_PositionVelocity): implement Keplerian conversion functions

Member O_SESSAME::Keplerian::SetPositionVelocity (const Vector &_Position, const Vector &_Velocity, const OrbitFrame &_OrbFrame): implement Keplerian conversion functions

Member O_SESSAME::Keplerian::SetPositionVelocity (const Vector &_PositionVelocity, const OrbitFrame &_OrbFrame): implement Keplerian conversion functions

Member O_SESSAME::Keplerian::GetEccentricAnomalyFromMeanAnomaly (const double &_MeanAnomaly): Allow user to specify tolerance for numerical convergence.

Member O_SESSAME::Keplerian::GetEccentricAnomalyFromMeanAnomaly (const double &_MeanAnomaly): Allow user to specify tolerance for numerical convergence.

Member O_SESSAME::Keplerian::ReadTwoLineElementSet (const string &_TwoLineElementSet)

Error checking for syntactically correct TLEs, including endlines, carriage returns.

Include full year info logic as per the tle standard, wherein 57-99 --> 19__ and 00-56 --> 20__.

verify that RAAN = longitude of the ascending node.

Member O_SESSAME::ModifiedRodriguezParameters::Set (const Vector &_EulerAngles, const int &_Sequence): Change implementation to calculate directly from Euler angles and not create a DCM?

Member O_SESSAME::ModifiedRodriguezParameters::Set (const Angle &_Angle1, const Angle &_Angle2, const Angle &_Angle3, const int &_Sequence): Fix Change implementation to calculate directly from Euler angles and not create a DCM?

Member O_SESSAME::ModifiedRodriguezParameters::GetEulerAngles (int _Sequence) const: Implement ModifiedRodriguezParameters::GetEulerAngles Function

Member O_SESSAME::ModifiedRodriguezParameters::GetEulerAxisAngle (Vector &_EulerAxis, Angle &_EulerAngle) const: Implement to directly convert and not use a temporary quaternion

Member O_SESSAME::NumericPropagator::~NumericPropagator (): figure out how to delete m_pIntegrator only when it is not being used

Member O_SESSAME::NumericPropagator::Propagate (const vector< ssfTime > &_propTime, const Vector &_orbitInitConditions, const Vector &_attInitConditions)

Determine what prop times exist and what times are req'd to recalc

determine if having vector<State> in Propagate is polymorphic

Append the requested time steps in the appropriate component history

Determine if the updated attitude & orbit should be set in Propagator

Member O_SESSAME::Orbit::~Orbit (): determine how to clean up the orbit pointers without leaving references hanging if(m_pEnvironment) delete m_pEnvironment; if(m_pPropagator) delete m_pPropagator;

Member O_SESSAME::Orbit::SetParameters (const Matrix &_Parameters): determine what physical parameters are pertinent.

Member O_SESSAME::OrbitHistory::GetHistory (): Grab the history depending on the desired state return type (elements, position, velocity, etc.)

Member O_SESSAME::OrbitHistory::GetState (const ssfTime &_requestedTime, OrbitState &_returnOrbitState): implement better error handling strategy

Class O_SESSAME::OrbitState: should OrbitState contain an ssfTime object?
change to be a template class of the Representation Types

Member O_SESSAME::OrbitState::~OrbitState (): determine how to delete OrbitState pointers

Member O_SESSAME::OrbitState::OrbitState (const OrbitState &_OrbStateCopy): Determine if the OrbitState copy function is req'd or hacked.

Member O_SESSAME::OrbitState::SetOrbitFrame (OrbitFrame *_pnewOrbitFrame): Implement the orbit representation conversion due to an orbit frame change.

Member O_SESSAME::OrbitState::SetOrbitFrame (OrbitFrame *_pnewOrbitFrame): add conversion of OrbitStateRepresentation to the new frame

Class O_SESSAME::Plot: Finish documenting API

Member O_SESSAME::Quaternion::Set (const Vector &_EulerAngles, const int &_Sequence): Implement Quaternion::Set(EulerAngles, Sequence) as individual calcs instead of multiple conversions

Member O_SESSAME::Quaternion::GetEulerAngles (const int &_Sequence) const: Implement Quaternion::GetEulerAngles function

Member O_SESSAME::Quaternion::Normalize (): Add Normalize() to Vector Class

Class O_SESSAME::Rotation: Write description of rotation class.

Member O_SESSAME::Rotation::Set (const Matrix &_inMatrix): Add testing for other types of matrix inputs

Member O_SESSAME::Rotation::GetRotation (const RotationType &_type, const int &_Sequence=123) const: completely document various rotation return types

Class O_SESSAME::RungeKuttaFehlbergIntegrator: document algorithm

Class O_SESSAME::RungeKuttaIntegrator: document algorithm testAttitudeIntegration.cpp testOrbitIntegration.cpp

Member O_SESSAME::RungeKuttaIntegrator::Integrate (const vector< ssfTime > &_propTime, odeFunctor _odeFunctorPtr, const Vector &_initialConditions, Orbit *_Orbit, Attitude *_Attitude, const Matrix &_constants, const Functor &_functorPtr): pull out RungeKuttaIntegrator::Step function

Member O_SESSAME::ssfTime::operator== (const ssfTime &rhs) const: Determine if it needs to compare the Epoch times as well.

Member O_SESSAME::ssfTime::operator!= (const ssfTime &rhs) const: Determine if it needs to compare the Epoch times as well.

File Attitude.h

Make Attitude derivable for diff't types of attitude representations (point-to, etc)

Implement export & import plug-ins (STK, matlab, excel...)

Add Attitude history storage

File Matrix.h: Add overloading of operators
Reference cammva documentation

File QuaternionDynamics.h: document the QuaternionDynamics function

File QuaternionKinematics.h: document the QuaternionKinematics class

File RungeKutta.h: Add test cases

File RungeKuttaIntegrator.cpp: Add test cases

Namespace O_SESSAME: Add test cases

Member O_SESSAME::eye (int _rowColumns): Implement eye as part of Vector or CAMdoubleVector class

Member O_SESSAME::trace (const Matrix &_inMatrix): Implement trace as part of Vector or CAMdoubleVector class

Member O_SESSAME::norm2 (const Vector &_inVector): Implement norm2 as part of Vector or CAMdoubleVector class

Member O_SESSAME::normalize (Vector &_inVector): Implement normalize as part of Vector or CAMdoubleVector class

Member O_SESSAME::normInf (const Vector &_inVector): Implement normInf as part of Vector or CAMdoubleVector class

Member O_SESSAME::skew (const Vector &_inVector): Implement skew as part of Vector or CAMdoubleVector class

Member O_SESSAME::crossP (const Vector &_v1, const Vector &_v2): Implement crossP as part of Vector or CAMdoubleVector class

Member SolarRadiationPressureForceFunction (const ssfTime &_currentTime, const OrbitState &_currentOrbitState, const AttitudeState &_currentAttitudeState, const EnvFuncParamaterType &_parameterList): Add checking for eclipse.

Page Installation Instructions: Document Windows installation
Document Library installation

Page Introduction to the Open-Sessame Framework

A better, faster, powerful matrix/vector library. Should handle all typical linear algebra functionality (matrix mult, vector mult, matrix*vector mult, inverse, transpose, norm, etc). Error handling would be nice with options for command line debugging (outputting the type/size of matrix, characterization of error (wrong mult sizes, singular) and possibly where the error occured (function, code line).
More force functions: solar radiation pressure, advanced atmospheric model, higher-order gravity model
More torque functions: magnetic field, higher-order gravity gradient, micrometeorites
Need to implement frames, both orbit & attitude.
A store and restore mechanism. Needs to be cross-platform, prefer something like XML formatting. Also need to be able to export/import with MatLab, Satellite ToolKit (STK), Excel (CSV), and others.

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