119 bool Run(
bool Holding)
override;
155 double GetNpilot(
int idx)
const {
return vPilotAccelN(idx); }
162 double GetNcg (
int idx)
const {
return vNcg(idx); }
163 double GetNlf (
void)
const;
177 else return BadUnits(); }
179 else return BadUnits(); }
181 else return BadUnits(); }
183 else return BadUnits(); }
185 else return BadUnits(); }
204 double GetVt (
void)
const {
return Vt; }
219 double GetNx (
void)
const {
return Nx; }
222 double GetNy (
void)
const {
return Ny; }
225 double GetNz (
void)
const {
return Nz; }
237 else return BadUnits();
291 double pt, tat, tatc;
308 double qbar, qbarUW, qbarUV;
314 double seconds_in_day;
317 double hoverbcg, hoverbmac;
319 void UpdateWindMatrices(
void);
321 void CalculateRelativePosition(
void);
324 double BadUnits(
void)
const;
325 void Debug(
int from)
override;
double GetqbarUV(void) const
double Getadot(int unit) const
double GetMagBeta(int unit) const
double Getbeta(void) const
bool Run(bool Holding) override
Runs the Auxiliary routines; called by the Executive Can pass in a value indicating if the executive ...
double GetqbarUW(void) const
double GetVtrueFPS() const
Returns the true airspeed in feet per second.
const FGColumnVector3 & GetEulerRates(void) const
void SetSecondsInDay(double sid)
const FGLocation & GetLocationVRP(void) const
double GetMachU(void) const
The mach number calculated using the vehicle X axis velocity.
const FGMatrix33 & GetTw2b(void) const
Calculates and returns the wind-to-body axis transformation matrix.
double GetNlf(void) const
double GetLongitudeRelativePosition(void) const
int GetDayOfYear(void) const
double Getbeta(int unit) const
double GetAeroUVW(int idx) const
double GetTAT_C(void) const
double GetVequivalentKTS(void) const
Returns equivalent airspeed in knots.
double GetVcalibratedFPS(void) const
Returns Calibrated airspeed in feet/second.
double GetGamma(int unit) const
double GetPilotAccel(int idx) const
void SetAeroPQR(const FGColumnVector3 &tt)
double Getadot(void) const
double Getalpha(int unit) const
struct JSBSim::FGAuxiliary::Inputs in
~FGAuxiliary()
Destructor.
double GetTotalPressure(void) const
Returns the total pressure.
double GetNy(void) const
The lateral acceleration in g's of the aircraft center of gravity.
double GetEulerRates(int axis) const
const FGColumnVector3 & GetAeroUVW(void) const
double GetReynoldsNumber(void) const
double GetTotalTemperature(void) const
Returns the total temperature.
double GetVtrueKTS() const
Returns the true airspeed in knots.
double GetHOverBCG(void) const
double GetAeroPQR(int axis) const
const FGColumnVector3 & GetNpilot(void) const
double GetNcg(int idx) const
const FGMatrix33 & GetTb2w(void) const
Calculates and returns the body-to-wind axis transformation matrix.
double Getbdot(int unit) const
double GetVequivalentFPS(void) const
Returns equivalent airspeed in feet/second.
const FGColumnVector3 & GetAeroPQR(void) const
double GetDistanceRelativePosition(void) const
void SetDayOfYear(int doy)
double Getalpha(void) const
const FGColumnVector3 & GetPilotAccel(void) const
double GetVground(void) const
Gets the ground speed in feet per second.
double GetNz(void) const
The vertical acceleration in g's of the aircraft center of gravity.
double GetVt(void) const
Gets the magnitude of total vehicle velocity including wind effects in feet per second.
bool InitModel(void) override
const FGColumnVector3 & GetNcg(void) const
double GetSecondsInDay(void) const
double GetMach(void) const
Gets the Mach number.
double GetNx(void) const
The longitudinal acceleration in g's of the aircraft center of gravity.
double Getbdot(void) const
double GetGroundTrack(void) const
double GetNpilot(int idx) const
double GetGamma(void) const
const FGColumnVector3 & GetNwcg(void) const
double GetHOverBMAC(void) const
FGAuxiliary(FGFDMExec *Executive)
Constructor.
double Getqbar(void) const
double GetLatitudeRelativePosition(void) const
double GetVcalibratedKTS(void) const
Returns Calibrated airspeed in knots.
double GetMagBeta(void) const
This class implements a 3 element column vector.
static constexpr double radtodeg
static constexpr double fpstokts
FGLocation holds an arbitrary location in the Earth centered Earth fixed reference frame (ECEF).
Handles matrix math operations.
FGModel(FGFDMExec *)
Constructor.