WsfRocketOrbitalManeuvering::Stage Class Reference

#include <WsfRocketOrbitalManeuvering.hpp>

Public Member Functions
	Stage ()
	~Stage ()=default
bool	Initialize ()
bool	ProcessInput (UtInput &aInput)
double	GetDuration (double aTotalMass, double aDeltaV) const
double	GetDeltaV (double aTotalMass, double aDuration) const
double	GetAvailableDeltaV (double aTotalMass) const
double	GetAvailableDuration () const
double	GetEmptyMass () const
double	GetFuelMass () const
double	GetTotalMass () const
double	GetBurnRate () const
double	GetThrust () const
double	GetSpecificImpulse () const
double	GetExhaustVelocity () const
double	Thrust (double aTotalMass, double aDuration, double &aDeltaV)

Protected Attributes
double	mEmptyMass
double	mFuelMass
double	mTotalMass
double	mBurnRate
	The rate of fuel expenditure (Kg/Sec); this can be provided or derived from the exhaust velocity.
double	mThrust
	The thrust (N); this must be provided.
double	mExhaustVelocity
	The exhaust velocity (m/s); this can be provided or derived from the burn rate.

Constructor & Destructor Documentation

Stage()

WsfRocketOrbitalManeuvering::Stage::Stage

(

)

References mBurnRate, mEmptyMass, mExhaustVelocity, mFuelMass, mThrust, and mTotalMass.

~Stage()

WsfRocketOrbitalManeuvering::Stage::~Stage ( )

default

References GetAvailableDeltaV(), GetDeltaV(), GetDuration(), Initialize(), and ProcessInput().

Member Function Documentation

GetAvailableDeltaV()

double WsfRocketOrbitalManeuvering::Stage::GetAvailableDeltaV

(

double

aTotalMass

)

const

References GetFuelMass(), and mExhaustVelocity.

Referenced by ~Stage().

GetAvailableDuration()

double WsfRocketOrbitalManeuvering::Stage::GetAvailableDuration ( ) const

inline

References mBurnRate, and mFuelMass.

GetBurnRate()

double WsfRocketOrbitalManeuvering::Stage::GetBurnRate ( ) const

inline

References mBurnRate.

Referenced by GetDuration().

GetDeltaV()

double WsfRocketOrbitalManeuvering::Stage::GetDeltaV	(	double	aTotalMass,
		double	aDuration ) const

References mBurnRate, and mExhaustVelocity.

Referenced by Thrust(), and ~Stage().

GetDuration()

double WsfRocketOrbitalManeuvering::Stage::GetDuration	(	double	aTotalMass,
		double	aDeltaV ) const

References GetBurnRate(), and mExhaustVelocity.

Referenced by ~Stage().

GetEmptyMass()

double WsfRocketOrbitalManeuvering::Stage::GetEmptyMass ( ) const

inline

References mEmptyMass.

GetExhaustVelocity()

double WsfRocketOrbitalManeuvering::Stage::GetExhaustVelocity ( ) const

inline

References mExhaustVelocity.

GetFuelMass()

double WsfRocketOrbitalManeuvering::Stage::GetFuelMass ( ) const

inline

References mFuelMass.

Referenced by GetAvailableDeltaV().

GetSpecificImpulse()

double WsfRocketOrbitalManeuvering::Stage::GetSpecificImpulse

(

)

const

References mExhaustVelocity.

GetThrust()

double WsfRocketOrbitalManeuvering::Stage::GetThrust ( ) const

inline

References mThrust.

GetTotalMass()

double WsfRocketOrbitalManeuvering::Stage::GetTotalMass ( ) const

inline

References mTotalMass.

Initialize()

bool WsfRocketOrbitalManeuvering::Stage::Initialize

(

)

References mBurnRate, mEmptyMass, mExhaustVelocity, mFuelMass, mThrust, mTotalMass, and ok.

Referenced by ~Stage().

ProcessInput()

bool WsfRocketOrbitalManeuvering::Stage::ProcessInput

(

UtInput &

aInput

)

References mBurnRate, mEmptyMass, mExhaustVelocity, mFuelMass, mThrust, and mTotalMass.

Referenced by WsfRocketOrbitalManeuvering::Rocket::ProcessInput(), and ~Stage().

Thrust()

double WsfRocketOrbitalManeuvering::Stage::Thrust	(	double	aTotalMass,
		double	aDuration,
		double &	aDeltaV )

References GetDeltaV(), mBurnRate, mFuelMass, and mTotalMass.

Member Data Documentation

mBurnRate

double WsfRocketOrbitalManeuvering::Stage::mBurnRate

protected

The rate of fuel expenditure (Kg/Sec); this can be provided or derived from the exhaust velocity.

Referenced by GetAvailableDuration(), GetBurnRate(), GetDeltaV(), Initialize(), ProcessInput(), Stage(), and Thrust().

mEmptyMass

double WsfRocketOrbitalManeuvering::Stage::mEmptyMass

protected

Mass of the THIS stage minus the mass of the fuel on THIS.

Note

This does NOT include the mass of the subsequent stages.

Referenced by GetEmptyMass(), Initialize(), ProcessInput(), and Stage().

mExhaustVelocity

double WsfRocketOrbitalManeuvering::Stage::mExhaustVelocity

protected

The exhaust velocity (m/s); this can be provided or derived from the burn rate.

Referenced by GetAvailableDeltaV(), GetDeltaV(), GetDuration(), GetExhaustVelocity(), GetSpecificImpulse(), Initialize(), ProcessInput(), and Stage().

mFuelMass

double WsfRocketOrbitalManeuvering::Stage::mFuelMass

protected

Mass of just the fuel on THIS stage.

Note

This does NOT include the mass of the subsequent stages.

Referenced by GetAvailableDuration(), GetFuelMass(), Initialize(), ProcessInput(), Stage(), and Thrust().

mThrust

double WsfRocketOrbitalManeuvering::Stage::mThrust

protected

The thrust (N); this must be provided.

Referenced by GetThrust(), Initialize(), ProcessInput(), and Stage().

mTotalMass

double WsfRocketOrbitalManeuvering::Stage::mTotalMass

protected

The total mass of the THIS stage (empty mass plus fuel mass).

Note

This does NOT include the mass of the subsequent stages.

Referenced by GetTotalMass(), Initialize(), ProcessInput(), Stage(), and Thrust().

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The documentation for this class was generated from the following files:

• WsfRocketOrbitalManeuvering.hpp
• WsfRocketOrbitalManeuvering.cpp