class AirDataSensor

Public Methods

AirDataSensor(Atmosphere* a, RigidBody* r)

~AirDataSensor()

void Sense(double dt)

Vector3D GetWindInPoint(const Vector3D r) const

Vector3D Body2Wind(const Vector3D& v) const

Axis transformations

Vector3D Wind2Body(const Vector3D& v) const

Converts a vector expressed in Body frame to Wind axes, using actual Wind Quaternion

inline double GetAlpha() const

Converts a vector expressed in Wind frame to Body axes, using actual Wind Quaternion.

inline double GetBeta() const

inline double GetAlphaTot() const

inline double GetAlphaDot() const

inline double GetBetaDot() const

inline double GetV() const

inline double GetM() const

inline double GetQdyn() const

inline double GetEtaT() const

inline double GetH() const

void OutState()

Private Fields

Atmosphere* atmos

Prints current Aerodynamic State to standard output

RigidBody* rbody

reference to Atmosphere.

Quaternion Qwind

reference to RigidBody.

double h

Needed to convert aerodynamic forces from wind to body axes

double V

Current altitude

double M

Aerodynamic velocity

double qdyn

Mach number

double eta_t

Dynamic pressure

double alpha

eta_t= qdyn_tail/qdyn

double beta

double alphatot

double alphadot

double betadot

Documentation

AirDataSensor(Atmosphere* a, RigidBody* r)

~AirDataSensor()

void Sense(double dt)

Vector3D GetWindInPoint(const Vector3D r) const

Vector3D Body2Wind(const Vector3D& v) const

Axis transformations

Vector3D Wind2Body(const Vector3D& v) const

Converts a vector expressed in Body frame to Wind axes, using actual Wind Quaternion

inline double GetAlpha() const

Converts a vector expressed in Wind frame to Body axes, using actual Wind Quaternion.

inline double GetBeta() const

inline double GetAlphaTot() const

inline double GetAlphaDot() const

inline double GetBetaDot() const

inline double GetV() const

inline double GetM() const

inline double GetQdyn() const

inline double GetEtaT() const

inline double GetH() const

void OutState()

Atmosphere* atmos

Prints current Aerodynamic State to standard output

RigidBody* rbody

reference to Atmosphere.

Quaternion Qwind

reference to RigidBody.

double h

Needed to convert aerodynamic forces from wind to body axes

double V

Current altitude

double M

Aerodynamic velocity

double qdyn

Mach number

double eta_t

Dynamic pressure

double alpha

eta_t= qdyn_tail/qdyn

double beta

double alphatot

double alphadot

double betadot

This class has no child classes.

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