#include <FGAuxiliary.h>
Inherits FGModel.
The theory behind pilot-sensed calculations is presented:
For purposes of discussion and calculation, assume for a minute that the pilot is in space and motionless in inertial space. She will feel no accelerations. If the aircraft begins to accelerate along any axis or axes (without rotating), the pilot will sense those accelerations. If any rotational moment is applied, the pilot will sense an acceleration due to that motion in the amount:
[wdot X R] + [w X (w X R)] Term I Term II
where:
wdot = omegadot, the rotational acceleration rate vector w = omega, the rotational rate vector R = the vector from the aircraft CG to the pilot eyepoint
The sum total of these two terms plus the acceleration of the aircraft body axis gives the acceleration the pilot senses in inertial space. In the presence of a large body such as a planet, a gravity field also provides an accelerating attraction. This acceleration can be transformed from the reference frame of the planet so as to be expressed in the frame of reference of the aircraft. This gravity field accelerating attraction is felt by the pilot as a force on her tushie as she sits in her aircraft on the runway awaiting takeoff clearance.
In JSBSim the acceleration of the body frame in inertial space is given by the F = ma relation. If the vForces vector is divided by the aircraft mass, the acceleration vector is calculated. The term wdot is equivalent to the JSBSim vPQRdot vector, and the w parameter is equivalent to vPQR. The radius R is calculated below in the vector vToEyePt.
Definition at line 111 of file FGAuxiliary.h.
Public Member Functions | |
| FGAuxiliary (FGFDMExec *Executive) | |
| Constructor. | |
| double | Getadot (int unit) const |
| double | Getadot (void) const |
| const FGColumnVector3 & | GetAeroPQR (void) const |
| double | GetAeroPQR (int axis) const |
| double | GetAeroUVW (int idx) const |
| const FGColumnVector3 & | GetAeroUVW (void) const |
| double | Getalpha (int unit) const |
| double | Getalpha (void) const |
| double | Getbdot (int unit) const |
| double | Getbdot (void) const |
| double | Getbeta (int unit) const |
| double | Getbeta (void) const |
| double | GetCrossWind (void) const |
| int | GetDayOfYear (void) const |
| double | GetDistanceRelativePosition (void) const |
| const FGColumnVector3 & | GetEulerRates (void) const |
| double | GetEulerRates (int axis) const |
| double | GetGamma (void) const |
| double | GetGroundTrack (void) const |
| double | GetHeadWind (void) const |
| double | GetHOverBCG (void) const |
| double | GetHOverBMAC (void) const |
| double | GethVRP (void) const |
| double | GetLatitudeRelativePosition (void) const |
| const FGLocation & | GetLocationVRP (void) const |
| double | GetLongitudeRelativePosition (void) const |
| double | GetMach (void) const |
| Gets the Mach number. | |
| double | GetMachU (void) const |
| The mach number calculated using the vehicle X axis velocity. | |
| double | GetMagBeta (int unit) const |
| double | GetMagBeta (void) const |
| const FGColumnVector3 & | GetNpilot (void) const |
| double | GetNpilot (int idx) const |
| double | GetNz (void) const |
| The vertical acceleration in g's of the aircraft center of gravity. | |
| const FGColumnVector3 & | GetPilotAccel (void) const |
| double | GetPilotAccel (int idx) const |
| double | Getqbar (void) const |
| double | GetqbarUV (void) const |
| double | GetqbarUW (void) const |
| double | GetReynoldsNumber (void) const |
| double | GetSecondsInDay (void) const |
| double | GetTAT_C (void) const |
| double | GetTotalPressure (void) const |
| Returns the total pressure. | |
| double | GetTotalTemperature (void) const |
| Returns the total temperature. | |
| double | GetVcalibratedFPS (void) const |
| Returns Calibrated airspeed in feet/second. | |
| double | GetVcalibratedKTS (void) const |
| Returns Calibrated airspeed in knots. | |
| double | GetVequivalentFPS (void) const |
| Returns equivalent airspeed in feet/second. | |
| double | GetVequivalentKTS (void) const |
| Returns equivalent airspeed in knots. | |
| double | GetVground (void) const |
| Gets the ground speed in feet per second. | |
| double | GetVt (void) const |
| Gets the magnitude of total vehicle velocity including wind effects in feet per second. | |
| bool | InitModel (void) |
| bool | Run (void) |
| Runs the Auxiliary routines; called by the Executive. | |
| void | SetAB (double t1, double t2) |
| void | Setadot (double tt) |
| void | SetAeroPQR (FGColumnVector3 tt) |
| void | SetAeroUVW (FGColumnVector3 tt) |
| void | Setalpha (double tt) |
| void | Setbdot (double tt) |
| void | Setbeta (double tt) |
| void | SetDayOfYear (int doy) |
| void | SetGamma (double tt) |
| void | SetMach (double tt) |
| void | Setqbar (double tt) |
| void | SetqbarUV (double tt) |
| void | SetqbarUW (double tt) |
| void | SetSecondsInDay (double sid) |
| void | SetVt (double tt) |
| ~FGAuxiliary () | |
| Destructor. | |
| FGAuxiliary | ( | FGFDMExec * | Executive | ) |
| Executive | a pointer to the parent executive object |
Definition at line 66 of file FGAuxiliary.cpp.
| double GetMach | ( | void | ) | const [inline] |
Definition at line 200 of file FGAuxiliary.h.
| double GetMachU | ( | void | ) | const [inline] |
Definition at line 203 of file FGAuxiliary.h.
| double GetNz | ( | void | ) | const [inline] |
Definition at line 206 of file FGAuxiliary.h.
| double GetTotalPressure | ( | void | ) | const [inline] |
Total pressure is freestream total pressure for subsonic only. For supersonic it is the 1D total pressure behind a normal shock.
Definition at line 142 of file FGAuxiliary.h.
| double GetTotalTemperature | ( | void | ) | const [inline] |
The total temperature ("tat", isentropic flow) is calculated:
tat = sat*(1 + 0.2*Mach*Mach)
Definition at line 151 of file FGAuxiliary.h.
| double GetVcalibratedFPS | ( | void | ) | const [inline] |
Definition at line 130 of file FGAuxiliary.h.
| double GetVcalibratedKTS | ( | void | ) | const [inline] |
Definition at line 132 of file FGAuxiliary.h.
| double GetVequivalentFPS | ( | void | ) | const [inline] |
Definition at line 134 of file FGAuxiliary.h.
| double GetVequivalentKTS | ( | void | ) | const [inline] |
Definition at line 136 of file FGAuxiliary.h.
| double GetVground | ( | void | ) | const [inline] |
The magnitude is the square root of the sum of the squares (RSS) of the vehicle north and east velocity components.
Definition at line 197 of file FGAuxiliary.h.
| double GetVt | ( | void | ) | const [inline] |
Definition at line 191 of file FGAuxiliary.h.
| bool Run | ( | void | ) | [virtual] |
Reimplemented from FGModel.
Definition at line 134 of file FGAuxiliary.cpp.
1.5.5