Detailed Description

Initializes the simulation run.

Takes a set of initial conditions (IC) and provide a kinematically consistent set of body axis velocity components, euler angles, and altitude. This class does not attempt to trim the model i.e. the sim will most likely start in a very dynamic state (unless, of course, you have chosen your IC's wisely, or started on the ground) even after setting it up with this class.

Usage Notes

With a valid object of FGFDMExec and an aircraft model loaded:

FGInitialCondition* fgic = FDMExec->GetIC();
 
// Reset the initial conditions and set VCAS and altitude
fgic->InitializeIC();
fgic->SetVcalibratedKtsIC(vcas);
fgic->SetAltitudeAGLFtIC(altitude);
 
// directly into Run
FDMExec->GetPropagate()->SetInitialState(fgic);
delete fgic;
FDMExec->Run();
 
//or to loop the sim w/o integrating
FDMExec->RunIC();

Alternatively, you can load initial conditions from an XML file:

FGInitialCondition* fgic = FDMExec->GetIC();

fgic->Load(IC_file);

Speed

Since vc, ve, vt, and mach all represent speed, the remaining three are recalculated each time one of them is set (using the current altitude). The most recent speed set is remembered so that if and when altitude is reset, the last set speed is used to recalculate the remaining three. Setting any of the body components forces a recalculation of vt and vt then becomes the most recent speed set.

Alpha,Gamma, and Theta

This class assumes that it will be used to set up the sim for a steady, zero pitch rate condition. Since any two of those angles specifies the third gamma (flight path angle) is favored when setting alpha and theta and alpha is favored when setting gamma. i.e.

set alpha : recalculate theta using gamma as currently set
set theta : recalculate alpha using gamma as currently set
set gamma : recalculate theta using alpha as currently set

The idea being that gamma is most interesting to pilots (since it is indicative of climb rate).

Setting climb rate is, for the purpose of this discussion, considered equivalent to setting gamma.

These are the items that can be set in an initialization file:

ubody (velocity, ft/sec)
vbody (velocity, ft/sec)
wbody (velocity, ft/sec)
vnorth (velocity, ft/sec)
veast (velocity, ft/sec)
vdown (velocity, ft/sec)
latitude (position, degrees)
longitude (position, degrees)
phi (orientation, degrees)
theta (orientation, degrees)
psi (orientation, degrees)
alpha (angle, degrees)
beta (angle, degrees)
gamma (angle, degrees)
roc (vertical velocity, ft/sec)
elevation (local terrain elevation, ft)
altitude (altitude AGL, ft)
altitudeAGL (altitude AGL, ft)
altitudeMSL (altitude MSL, ft)
winddir (wind from-angle, degrees)
vwind (magnitude wind speed, ft/sec)
hwind (headwind speed, knots)
xwind (crosswind speed, knots)
vc (calibrated airspeed, ft/sec)
mach (mach)
vground (ground speed, ft/sec)
trim (0 for no trim, 1 for ground trim, 'Longitudinal', 'Full', 'Ground', 'Pullup', 'Custom', 'Turn')
running (-1 for all engines, 0 ... n-1 for specific engines)

Properties

ic/vc-kts (read/write) Calibrated airspeed initial condition in knots
ic/ve-kts (read/write) Knots equivalent airspeed initial condition
ic/vg-kts (read/write) Ground speed initial condition in knots
ic/vt-kts (read/write) True airspeed initial condition in knots
ic/mach (read/write) Mach initial condition
ic/roc-fpm (read/write) Rate of climb initial condition in feet/minute
ic/gamma-deg (read/write) Flightpath angle initial condition in degrees
ic/alpha-deg (read/write) Angle of attack initial condition in degrees
ic/beta-deg (read/write) Angle of sideslip initial condition in degrees
ic/theta-deg (read/write) Pitch angle initial condition in degrees
ic/phi-deg (read/write) Roll angle initial condition in degrees
ic/psi-true-deg (read/write) Heading angle initial condition in degrees
ic/lat-gc-deg (read/write) Latitude initial condition in degrees
ic/long-gc-deg (read/write) Longitude initial condition in degrees
ic/h-sl-ft (read/write) Height above sea level initial condition in feet
ic/h-agl-ft (read/write) Height above ground level initial condition in feet
ic/sea-level-radius-ft (read/write) Radius of planet at sea level in feet
ic/terrain-elevation-ft (read/write) Terrain elevation above sea level in feet
ic/vg-fps (read/write) Ground speed initial condition in feet/second
ic/vt-fps (read/write) True airspeed initial condition in feet/second
ic/vw-bx-fps (read/write) Wind velocity initial condition in Body X frame in feet/second
ic/vw-by-fps (read/write) Wind velocity initial condition in Body Y frame in feet/second
ic/vw-bz-fps (read/write) Wind velocity initial condition in Body Z frame in feet/second
ic/vw-north-fps (read/write) Wind northward velocity initial condition in feet/second
ic/vw-east-fps (read/write) Wind eastward velocity initial condition in feet/second
ic/vw-down-fps (read/write) Wind downward velocity initial condition in feet/second
ic/vw-mag-fps (read/write) Wind velocity magnitude initial condition in feet/sec.
ic/vw-dir-deg (read/write) Wind direction initial condition, in degrees from north
ic/roc-fps (read/write) Rate of climb initial condition, in feet/second
ic/u-fps (read/write) Body frame x-axis velocity initial condition in feet/second
ic/v-fps (read/write) Body frame y-axis velocity initial condition in feet/second
ic/w-fps (read/write) Body frame z-axis velocity initial condition in feet/second
ic/vn-fps (read/write) Local frame x-axis (north) velocity initial condition in feet/second
ic/ve-fps (read/write) Local frame y-axis (east) velocity initial condition in feet/second
ic/vd-fps (read/write) Local frame z-axis (down) velocity initial condition in feet/second
ic/gamma-rad (read/write) Flight path angle initial condition in radians
ic/alpha-rad (read/write) Angle of attack initial condition in radians
ic/theta-rad (read/write) Pitch angle initial condition in radians
ic/beta-rad (read/write) Angle of sideslip initial condition in radians
ic/phi-rad (read/write) Roll angle initial condition in radians
ic/psi-true-rad (read/write) Heading angle initial condition in radians
ic/lat-gc-rad (read/write) Geocentric latitude initial condition in radians
ic/long-gc-rad (read/write) Longitude initial condition in radians
ic/p-rad_sec (read/write) Roll rate initial condition in radians/second
ic/q-rad_sec (read/write) Pitch rate initial condition in radians/second
ic/r-rad_sec (read/write) Yaw rate initial condition in radians/second

Author: Tony Peden

Definition at line 224 of file FGInitialCondition.h.

#include <FGInitialCondition.h>

Inheritance diagram for FGInitialCondition:

Collaboration diagram for FGInitialCondition:

Public Member Functions
	FGInitialCondition (FGFDMExec *fdmex)
	Constructor.

	~FGInitialCondition ()
	Destructor.

void	bind (FGPropertyManager *pm)

double	GetAlphaDegIC (void) const
	Gets the initial angle of attack. More...

double	GetAlphaRadIC (void) const
	Gets the initial angle of attack. More...

double	GetAltitudeAGLFtIC (void) const
	Gets the initial altitude above ground level. More...

double	GetAltitudeASLFtIC (void) const
	Gets the initial altitude above sea level. More...

double	GetBetaDegIC (void) const
	Gets the initial sideslip angle. More...

double	GetBetaRadIC (void) const
	Gets the initial angle of sideslip. More...

double	GetClimbRateFpmIC (void) const
	Gets the initial climb rate. More...

double	GetClimbRateFpsIC (void) const
	Gets the initial climb rate. More...

double	GetEarthPositionAngleIC (void) const
	Gets the initial Earth position angle. More...

double	GetFlightPathAngleDegIC (void) const
	Gets the initial flight path angle. More...

double	GetFlightPathAngleRadIC (void) const
	Gets the initial flight path angle. More...

double	GetGeodLatitudeDegIC (void) const
	Gets the initial geodetic latitude. More...

double	GetGeodLatitudeRadIC (void) const
	Gets the initial geodetic latitude. More...

double	GetLatitudeDegIC (void) const
	Gets the initial latitude. More...

double	GetLatitudeRadIC (void) const
	Gets the initial latitude. More...

double	GetLongitudeDegIC (void) const
	Gets the initial longitude. More...

double	GetLongitudeRadIC (void) const
	Gets the initial longitude. More...

double	GetMachIC (void) const
	Gets the initial mach. More...

const FGQuaternion &	GetOrientation (void) const
	Gets the initial orientation. More...

double	GetPhiDegIC (void) const
	Gets the initial roll angle. More...

double	GetPhiRadIC (void) const
	Gets the initial roll angle. More...

const FGLocation &	GetPosition (void) const
	Gets the initial position. More...

const FGColumnVector3	GetPQRRadpsIC (void) const
	Gets the initial body rotation rate. More...

double	GetPRadpsIC () const
	Gets the initial body axis roll rate. More...

double	GetPsiDegIC (void) const
	Gets the initial heading angle. More...

double	GetPsiRadIC (void) const
	Gets the initial heading angle. More...

double	GetQRadpsIC () const
	Gets the initial body axis pitch rate. More...

double	GetRRadpsIC () const
	Gets the initial body axis yaw rate. More...

speedset	GetSpeedSet (void) const
	Gets the initial speedset. More...

double	GetTargetNlfIC (void) const
	Gets the target normal load factor set from IC. More...

double	GetTerrainElevationFtIC (void) const
	Gets the initial terrain elevation. More...

double	GetThetaDegIC (void) const
	Gets the initial pitch angle. More...

double	GetThetaRadIC (void) const
	Gets the initial pitch angle. More...

double	GetUBodyFpsIC (void) const
	Gets the initial body axis X velocity. More...

const FGColumnVector3	GetUVWFpsIC (void) const
	Gets the initial body velocity. More...

double	GetVBodyFpsIC (void) const
	Gets the initial body axis Y velocity. More...

double	GetVcalibratedKtsIC (void) const
	Gets the initial calibrated airspeed. More...

double	GetVDownFpsIC (void) const
	Gets the initial local frame Z (Down) velocity. More...

double	GetVEastFpsIC (void) const
	Gets the initial local frame Y (East) velocity. More...

double	GetVequivalentKtsIC (void) const
	Gets the initial equivalent airspeed. More...

double	GetVgroundFpsIC (void) const
	Gets the initial ground velocity. More...

double	GetVgroundKtsIC (void) const
	Gets the initial ground speed. More...

double	GetVNorthFpsIC (void) const
	Gets the initial local frame X (North) velocity. More...

double	GetVtrueFpsIC (void) const
	Gets the initial true velocity. More...

double	GetVtrueKtsIC (void) const
	Gets the initial true velocity. More...

double	GetWBodyFpsIC (void) const
	Gets the initial body axis Z velocity. More...

double	GetWindDFpsIC (void) const
	Gets the initial wind velocity in local frame. More...

double	GetWindDirDegIC (void) const
	Gets the initial wind direction. More...

double	GetWindEFpsIC (void) const
	Gets the initial wind velocity in local frame. More...

double	GetWindFpsIC (void) const
	Gets the initial total wind velocity in feet/sec. More...

const FGColumnVector3	GetWindNEDFpsIC (void) const
	Gets the initial wind velocity in the NED local frame. More...

double	GetWindNFpsIC (void) const
	Gets the initial wind velocity in local frame. More...

double	GetWindUFpsIC (void) const
	Gets the initial body axis X wind velocity. More...

double	GetWindVFpsIC (void) const
	Gets the initial body axis Y wind velocity. More...

double	GetWindWFpsIC (void) const
	Gets the initial body axis Z wind velocity. More...

void	InitializeIC (void)
	Initialize the initial conditions to default values.

bool	IsEngineRunning (unsigned int n) const
	Is an engine running ? More...

bool	Load (const SGPath &rstname, bool useStoredPath=true)
	Loads the initial conditions. More...

void	ResetIC (double u0, double v0, double w0, double p0, double q0, double r0, double alpha0, double beta0, double phi0, double theta0, double psi0, double latitudeRad0, double longitudeRad0, double altitudeAGL0, double gamma0)
	Resets the IC data structure to new values. More...

void	SetAlphaDegIC (double a)
	Sets angle of attack initial condition in degrees. More...

void	SetAlphaRadIC (double alpha)
	Sets the initial angle of attack. More...

void	SetAltitudeAGLFtIC (double agl)
	Sets the initial Altitude above ground level. More...

void	SetAltitudeASLFtIC (double altitudeASL)
	Sets the altitude above sea level initial condition in feet. More...

void	SetBetaDegIC (double b)
	Sets angle of sideslip initial condition in degrees. More...

void	SetBetaRadIC (double beta)
	Sets the initial sideslip angle. More...

void	SetClimbRateFpmIC (double roc)
	Sets the climb rate initial condition in feet/minute. More...

void	SetClimbRateFpsIC (double roc)
	Sets the initial climb rate. More...

void	SetCrossWindKtsIC (double cross)
	Sets the initial crosswind speed. More...

void	SetFlightPathAngleDegIC (double gamma)
	Sets the flight path angle initial condition in degrees. More...

void	SetFlightPathAngleRadIC (double gamma)
	Sets the initial flight path angle. More...

void	SetGeodLatitudeDegIC (double glat)
	Sets the initial geodetic latitude. More...

void	SetGeodLatitudeRadIC (double glat)
	Sets the initial geodetic latitude. More...

void	SetHeadWindKtsIC (double head)
	Sets the initial headwind velocity. More...

void	SetLatitudeDegIC (double lat)
	Sets the initial latitude. More...

void	SetLatitudeRadIC (double lat)
	Sets the initial latitude. More...

void	SetLongitudeDegIC (double lon)
	Sets the initial longitude. More...

void	SetLongitudeRadIC (double lon)
	Sets the initial longitude. More...

void	SetMachIC (double mach)
	Set mach initial condition. More...

void	SetPhiDegIC (double phi)
	Sets the roll angle initial condition in degrees. More...

void	SetPhiRadIC (double phi)
	Sets the initial roll angle. More...

void	SetPRadpsIC (double P)
	Sets the initial body axis roll rate. More...

void	SetPsiDegIC (double psi)
	Sets the heading angle initial condition in degrees. More...

void	SetPsiRadIC (double psi)
	Sets the initial heading angle. More...

void	SetQRadpsIC (double Q)
	Sets the initial body axis pitch rate. More...

void	SetRRadpsIC (double R)
	Sets the initial body axis yaw rate. More...

void	SetTargetNlfIC (double nlf)
	Sets the target normal load factor. More...

void	SetTerrainElevationFtIC (double elev)
	Sets the initial terrain elevation. More...

void	SetThetaDegIC (double theta)
	Sets pitch angle initial condition in degrees. More...

void	SetThetaRadIC (double theta)
	Sets the initial pitch angle. More...

void	SetUBodyFpsIC (double ubody)
	Sets the initial body axis X velocity. More...

void	SetVBodyFpsIC (double vbody)
	Sets the initial body axis Y velocity. More...

void	SetVcalibratedKtsIC (double vc)
	Set calibrated airspeed initial condition in knots. More...

void	SetVDownFpsIC (double vd)
	Sets the initial local axis down velocity. More...

void	SetVEastFpsIC (double ve)
	Sets the initial local axis east velocity. More...

void	SetVequivalentKtsIC (double ve)
	Set equivalent airspeed initial condition in knots. More...

void	SetVgroundFpsIC (double vg)
	Sets the initial ground speed. More...

void	SetVgroundKtsIC (double vg)
	Set ground speed initial condition in knots. More...

void	SetVNorthFpsIC (double vn)
	Sets the initial local axis north velocity. More...

void	SetVtrueFpsIC (double vt)
	Sets the initial true airspeed. More...

void	SetVtrueKtsIC (double vtrue)
	Set true airspeed initial condition in knots. More...

void	SetWBodyFpsIC (double wbody)
	Sets the initial body axis Z velocity. More...

void	SetWindDirDegIC (double dir)
	Sets the initial wind direction. More...

void	SetWindDownKtsIC (double wD)
	Sets the initial wind downward speed. More...

void	SetWindMagKtsIC (double mag)
	Sets the initial total wind speed. More...

void	SetWindNEDFpsIC (double wN, double wE, double wD)
	Sets the initial wind velocity. More...

int	TrimRequested (void) const
	Does initialization file call for trim ? More...

Public Member Functions inherited from FGJSBBase
	FGJSBBase ()
	Constructor for FGJSBBase.

virtual	~FGJSBBase ()
	Destructor for FGJSBBase.

void	PutMessage (const Message &msg)
	Places a Message structure on the Message queue. More...

void	PutMessage (const std::string &text)
	Creates a message with the given text and places it on the queue. More...

void	PutMessage (const std::string &text, bool bVal)
	Creates a message with the given text and boolean value and places it on the queue. More...

void	PutMessage (const std::string &text, int iVal)
	Creates a message with the given text and integer value and places it on the queue. More...

void	PutMessage (const std::string &text, double dVal)
	Creates a message with the given text and double value and places it on the queue. More...

int	SomeMessages (void) const
	Reads the message on the queue (but does not delete it). More...

void	ProcessMessage (void)
	Reads the message on the queue and removes it from the queue. More...

Message *	ProcessNextMessage (void)
	Reads the next message on the queue and removes it from the queue. More...

void	disableHighLighting (void)
	Disables highlighting in the console output.

Additional Inherited Members
Public Types inherited from FGJSBBase
enum	{ eL = 1, eM, eN }
	Moments L, M, N.

enum	{ eP = 1, eQ, eR }
	Rates P, Q, R.

enum	{ eU = 1, eV, eW }
	Velocities U, V, W.

enum	{ eX = 1, eY, eZ }
	Positions X, Y, Z.

enum	{ ePhi = 1, eTht, ePsi }
	Euler angles Phi, Theta, Psi.

enum	{ eDrag = 1, eSide, eLift }
	Stability axis forces, Drag, Side force, Lift.

enum	{ eRoll = 1, ePitch, eYaw }
	Local frame orientation Roll, Pitch, Yaw.

enum	{ eNorth = 1, eEast, eDown }
	Local frame position North, East, Down.

enum	{ eLat = 1, eLong, eRad }
	Locations Radius, Latitude, Longitude.

enum	{ inNone = 0, inDegrees, inRadians, inMeters, inFeet }
	Conversion specifiers.

Static Public Member Functions inherited from FGJSBBase
static const std::string &	GetVersion (void)
	Returns the version number of JSBSim. More...

static constexpr double	KelvinToFahrenheit (double kelvin)
	Converts from degrees Kelvin to degrees Fahrenheit. More...

static constexpr double	CelsiusToRankine (double celsius)
	Converts from degrees Celsius to degrees Rankine. More...

static constexpr double	RankineToCelsius (double rankine)
	Converts from degrees Rankine to degrees Celsius. More...

static constexpr double	KelvinToRankine (double kelvin)
	Converts from degrees Kelvin to degrees Rankine. More...

static constexpr double	RankineToKelvin (double rankine)
	Converts from degrees Rankine to degrees Kelvin. More...

static constexpr double	FahrenheitToCelsius (double fahrenheit)
	Converts from degrees Fahrenheit to degrees Celsius. More...

static constexpr double	CelsiusToFahrenheit (double celsius)
	Converts from degrees Celsius to degrees Fahrenheit. More...

static constexpr double	CelsiusToKelvin (double celsius)
	Converts from degrees Celsius to degrees Kelvin. More...

static constexpr double	KelvinToCelsius (double kelvin)
	Converts from degrees Kelvin to degrees Celsius. More...

static constexpr double	FeetToMeters (double measure)
	Converts from feet to meters. More...

static double	PitotTotalPressure (double mach, double p)
	Compute the total pressure in front of the Pitot tube. More...

static double	MachFromImpactPressure (double qc, double p)
	Compute the Mach number from the differential pressure (qc) and the static pressure. More...

static double	VcalibratedFromMach (double mach, double p)
	Calculate the calibrated airspeed from the Mach number. More...

static double	MachFromVcalibrated (double vcas, double p)
	Calculate the Mach number from the calibrated airspeed.Based on the formulas in the US Air Force Aircraft Performance Flight Testing Manual (AFFTC-TIH-99-01). More...

static bool	EqualToRoundoff (double a, double b)
	Finite precision comparison. More...

static bool	EqualToRoundoff (float a, float b)
	Finite precision comparison. More...

static bool	EqualToRoundoff (float a, double b)
	Finite precision comparison. More...

static bool	EqualToRoundoff (double a, float b)
	Finite precision comparison. More...

static constexpr double	Constrain (double min, double value, double max)
	Constrain a value between a minimum and a maximum value.

static constexpr double	sign (double num)

static double	GaussianRandomNumber (void)

Static Public Attributes inherited from FGJSBBase
static char	highint [5] = {27, '[', '1', 'm', '\0' }
	highlights text

static char	halfint [5] = {27, '[', '2', 'm', '\0' }
	low intensity text

static char	normint [6] = {27, '[', '2', '2', 'm', '\0' }
	normal intensity text

static char	reset [5] = {27, '[', '0', 'm', '\0' }
	resets text properties

static char	underon [5] = {27, '[', '4', 'm', '\0' }
	underlines text

static char	underoff [6] = {27, '[', '2', '4', 'm', '\0' }
	underline off

static char	fgblue [6] = {27, '[', '3', '4', 'm', '\0' }
	blue text

static char	fgcyan [6] = {27, '[', '3', '6', 'm', '\0' }
	cyan text

static char	fgred [6] = {27, '[', '3', '1', 'm', '\0' }
	red text

static char	fggreen [6] = {27, '[', '3', '2', 'm', '\0' }
	green text

static char	fgdef [6] = {27, '[', '3', '9', 'm', '\0' }
	default text

static short	debug_lvl = 1

Static Protected Member Functions inherited from FGJSBBase
static std::string	CreateIndexedPropertyName (const std::string &Property, int index)

Static Protected Attributes inherited from FGJSBBase
static Message	localMsg

static std::queue< Message >	Messages

static unsigned int	messageId = 0

static constexpr double	radtodeg = 180. / M_PI

static constexpr double	degtorad = M_PI / 180.

static constexpr double	hptoftlbssec = 550.0

static constexpr double	psftoinhg = 0.014138

static constexpr double	psftopa = 47.88

static constexpr double	ktstofps = 1.68781

static constexpr double	fpstokts = 1.0 / ktstofps

static constexpr double	inchtoft = 1.0/12.0

static constexpr double	fttom = 0.3048

static constexpr double	m3toft3 = 1.0/(fttomfttomfttom)

static constexpr double	in3tom3 = inchtoftinchtoftinchtoft/m3toft3

static constexpr double	inhgtopa = 3386.38

static constexpr double	slugtolb = 32.174049
	Note that definition of lbtoslug by the inverse of slugtolb and not to a different constant you can also get from some tables will make lbtoslug*slugtolb == 1 up to the magnitude of roundoff. More...

static constexpr double	lbtoslug = 1.0/slugtolb

static constexpr double	kgtolb = 2.20462

static constexpr double	kgtoslug = 0.06852168

static const std::string	needed_cfg_version = "2.0"

static const std::string	JSBSim_version = JSBSIM_VERSION " " __DATE__ " " __TIME__

static int	gaussian_random_number_phase = 0

Member Function Documentation

◆ GetAlphaDegIC()

double GetAlphaDegIC ( void ) const

inline

Gets the initial angle of attack.

Returns: Initial alpha in degrees

Definition at line 347 of file FGInitialCondition.h.

347 { return alpha*radtodeg; }

◆ GetAlphaRadIC()

double GetAlphaRadIC ( void ) const

inline

Gets the initial angle of attack.

Returns: Initial alpha in radians

Definition at line 623 of file FGInitialCondition.h.

623 { return alpha; }

◆ GetAltitudeAGLFtIC()

double GetAltitudeAGLFtIC ( void ) const

Gets the initial altitude above ground level.

Returns: Initial altitude AGL in feet

Definition at line 656 of file FGInitialCondition.cpp.

 {
   return fdmex->GetInertial()->GetAltitudeAGL(position);
 }

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◆ GetAltitudeASLFtIC()

double GetAltitudeASLFtIC ( void ) const

Gets the initial altitude above sea level.

Returns: Initial altitude in feet.

Definition at line 649 of file FGInitialCondition.cpp.

 {
   return position.GetRadius() - position.GetSeaLevelRadius();
 }

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◆ GetBetaDegIC()

double GetBetaDegIC ( void ) const

inline

Gets the initial sideslip angle.

Returns: Initial beta in degrees

Definition at line 351 of file FGInitialCondition.h.

351 { return beta*radtodeg; }

◆ GetBetaRadIC()

double GetBetaRadIC ( void ) const

inline

Gets the initial angle of sideslip.

Returns: Initial sideslip angle in radians

Definition at line 627 of file FGInitialCondition.h.

627 { return beta; }

◆ GetClimbRateFpmIC()

double GetClimbRateFpmIC ( void ) const

inline

Gets the initial climb rate.

Returns: Initial climb rate in feet/minute

Definition at line 337 of file FGInitialCondition.h.

338 { return GetClimbRateFpsIC()*60; }

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◆ GetClimbRateFpsIC()

double GetClimbRateFpsIC ( void ) const

inline

Gets the initial climb rate.

Returns: Initial rate of climb in feet/second

Definition at line 518 of file FGInitialCondition.h.

   {
     const FGMatrix33& Tb2l = orientation.GetTInv();
     FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
     return -_vt_NED(eW);
   }

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◆ GetEarthPositionAngleIC()

double GetEarthPositionAngleIC ( void ) const

inline

Gets the initial Earth position angle.

Returns: Initial Earth position angle in radians.

Definition at line 392 of file FGInitialCondition.h.

392 { return epa; }

◆ GetFlightPathAngleDegIC()

double GetFlightPathAngleDegIC ( void ) const

inline

Gets the initial flight path angle.

Returns: Initial flight path angle in degrees

Definition at line 342 of file FGInitialCondition.h.

343 { return GetFlightPathAngleRadIC()*radtodeg; }

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◆ GetFlightPathAngleRadIC()

double GetFlightPathAngleRadIC ( void ) const

inline

Gets the initial flight path angle.

If total velocity is zero, this function returns zero.

Returns: Initial flight path angle in radians

Definition at line 618 of file FGInitialCondition.h.

619 { return (vt == 0.0)?0.0:asin(GetClimbRateFpsIC() / vt); }

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◆ GetGeodLatitudeDegIC()

double GetGeodLatitudeDegIC ( void ) const

inline

Gets the initial geodetic latitude.

Returns: Initial geodetic latitude in degrees

Definition at line 371 of file FGInitialCondition.h.

372 { return position.GetGeodLatitudeDeg(); }

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◆ GetGeodLatitudeRadIC()

double GetGeodLatitudeRadIC ( void ) const

inline

Gets the initial geodetic latitude.

Returns: Initial geodetic latitude in radians

Definition at line 639 of file FGInitialCondition.h.

640 { return position.GetGeodLatitudeRad(); }

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◆ GetLatitudeDegIC()

double GetLatitudeDegIC ( void ) const

inline

Gets the initial latitude.

Returns: Initial geocentric latitude in degrees

Definition at line 367 of file FGInitialCondition.h.

367 { return position.GetLatitudeDeg(); }

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◆ GetLatitudeRadIC()

double GetLatitudeRadIC ( void ) const

inline

Gets the initial latitude.

Returns: Initial latitude in radians

Definition at line 635 of file FGInitialCondition.h.

635 { return position.GetLatitude(); }

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◆ GetLongitudeDegIC()

double GetLongitudeDegIC ( void ) const

inline

Gets the initial longitude.

Returns: Initial longitude in degrees

Definition at line 376 of file FGInitialCondition.h.

376 { return position.GetLongitudeDeg(); }

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◆ GetLongitudeRadIC()

double GetLongitudeRadIC ( void ) const

inline

Gets the initial longitude.

Returns: Initial longitude in radians

Definition at line 644 of file FGInitialCondition.h.

644 { return position.GetLongitude(); }

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◆ GetMachIC()

double GetMachIC ( void ) const

Gets the initial mach.

Returns: Initial mach number

Definition at line 983 of file FGInitialCondition.cpp.

 {
   double altitudeASL = GetAltitudeASLFtIC();
   double soundSpeed = Atmosphere->GetSoundSpeed(altitudeASL);
   return vt / soundSpeed;
 }

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◆ GetOrientation()

const FGQuaternion& GetOrientation ( void ) const

inline

Gets the initial orientation.

Returns: Initial orientation

Definition at line 648 of file FGInitialCondition.h.

648 { return orientation; }

◆ GetPhiDegIC()

double GetPhiDegIC ( void ) const

inline

Gets the initial roll angle.

Returns: Initial phi in degrees

Definition at line 359 of file FGInitialCondition.h.

359 { return orientation.GetEulerDeg(ePhi); }

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◆ GetPhiRadIC()

double GetPhiRadIC ( void ) const

inline

Gets the initial roll angle.

Returns: Initial roll angle in radians

Definition at line 652 of file FGInitialCondition.h.

652 { return orientation.GetEuler(ePhi); }

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◆ GetPosition()

const FGLocation& GetPosition ( void ) const

inline

Gets the initial position.

Returns: Initial location

Definition at line 631 of file FGInitialCondition.h.

631 { return position; }

◆ GetPQRRadpsIC()

const FGColumnVector3 GetPQRRadpsIC ( void ) const

inline

Gets the initial body rotation rate.

Returns: Initial body rotation rate in radians/second

Definition at line 558 of file FGInitialCondition.h.

558 { return vPQR_body; }

◆ GetPRadpsIC()

double GetPRadpsIC ( ) const

inline

Gets the initial body axis roll rate.

Returns: Initial body axis roll rate in radians/second

Definition at line 562 of file FGInitialCondition.h.

562 { return vPQR_body(eP); }

◆ GetPsiDegIC()

double GetPsiDegIC ( void ) const

inline

Gets the initial heading angle.

Returns: Initial psi in degrees

Definition at line 363 of file FGInitialCondition.h.

363 { return orientation.GetEulerDeg(ePsi); }

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◆ GetPsiRadIC()

double GetPsiRadIC ( void ) const

inline

Gets the initial heading angle.

Returns: Initial heading angle in radians

Definition at line 660 of file FGInitialCondition.h.

660 { return orientation.GetEuler(ePsi); }

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◆ GetQRadpsIC()

double GetQRadpsIC ( ) const

inline

Gets the initial body axis pitch rate.

Returns: Initial body axis pitch rate in radians/second

Definition at line 566 of file FGInitialCondition.h.

566 { return vPQR_body(eQ); }

◆ GetRRadpsIC()

double GetRRadpsIC ( ) const

inline

Gets the initial body axis yaw rate.

Returns: Initial body axis yaw rate in radians/second

Definition at line 570 of file FGInitialCondition.h.

570 { return vPQR_body(eR); }

◆ GetSpeedSet()

speedset GetSpeedSet ( void ) const

inline

Gets the initial speedset.

Returns: Initial speedset

Definition at line 664 of file FGInitialCondition.h.

664 { return lastSpeedSet; }

◆ GetTargetNlfIC()

double GetTargetNlfIC ( void ) const

inline

Gets the target normal load factor set from IC.

Returns: target normal load factor set from IC

Definition at line 668 of file FGInitialCondition.h.

668 { return targetNlfIC; }

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◆ GetTerrainElevationFtIC()

double GetTerrainElevationFtIC ( void ) const

Gets the initial terrain elevation.

Returns: Initial terrain elevation in feet

Definition at line 663 of file FGInitialCondition.cpp.

 {
   FGColumnVector3 normal, v, w;
   FGLocation contact;
   double a = fdmex->GetInertial()->GetSemimajor();
   double b = fdmex->GetInertial()->GetSemiminor();
   contact.SetEllipse(a, b);
   fdmex->GetInertial()->GetContactPoint(position, contact, normal, v, w);
   return contact.GetGeodAltitude();
 }

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◆ GetThetaDegIC()

double GetThetaDegIC ( void ) const

inline

Gets the initial pitch angle.

Returns: Initial pitch angle in degrees

Definition at line 355 of file FGInitialCondition.h.

355 { return orientation.GetEulerDeg(eTht); }

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◆ GetThetaRadIC()

double GetThetaRadIC ( void ) const

inline

Gets the initial pitch angle.

Returns: Initial pitch angle in radians

Definition at line 656 of file FGInitialCondition.h.

656 { return orientation.GetEuler(eTht); }

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◆ GetUBodyFpsIC()

double GetUBodyFpsIC ( void ) const

inline

Gets the initial body axis X velocity.

Returns: Initial body axis X velocity in feet/second.

Definition at line 534 of file FGInitialCondition.h.

534 { return GetBodyVelFpsIC(eU); }

◆ GetUVWFpsIC()

const FGColumnVector3 GetUVWFpsIC ( void ) const

inline

Gets the initial body velocity.

Returns: Initial body velocity in feet/second.

Definition at line 527 of file FGInitialCondition.h.

                                                 {
     const FGMatrix33& Tl2b = orientation.GetT();
     return Tl2b * vUVW_NED;
   }

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◆ GetVBodyFpsIC()

double GetVBodyFpsIC ( void ) const

inline

Gets the initial body axis Y velocity.

Returns: Initial body axis Y velocity in feet/second.

Definition at line 538 of file FGInitialCondition.h.

538 { return GetBodyVelFpsIC(eV); }

◆ GetVcalibratedKtsIC()

double GetVcalibratedKtsIC ( void ) const

Gets the initial calibrated airspeed.

Returns: Initial calibrated airspeed in knots

Definition at line 961 of file FGInitialCondition.cpp.

 {
   double altitudeASL = GetAltitudeASLFtIC();
   double pressure = Atmosphere->GetPressure(altitudeASL);
   double soundSpeed = Atmosphere->GetSoundSpeed(altitudeASL);
   double mach = vt / soundSpeed;
  
   return fpstokts * VcalibratedFromMach(mach, pressure);
 }

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◆ GetVDownFpsIC()

double GetVDownFpsIC ( void ) const

inline

Gets the initial local frame Z (Down) velocity.

Returns: Initial local frame Z (Down) axis velocity in feet/second.

Definition at line 554 of file FGInitialCondition.h.

554 { return vUVW_NED(eW); }

◆ GetVEastFpsIC()

double GetVEastFpsIC ( void ) const

inline

Gets the initial local frame Y (East) velocity.

Returns: Initial local frame Y (East) axis velocity in feet/second.

Definition at line 550 of file FGInitialCondition.h.

550 { return vUVW_NED(eV); }

◆ GetVequivalentKtsIC()

double GetVequivalentKtsIC ( void ) const

Gets the initial equivalent airspeed.

Returns: Initial equivalent airspeed in knots

Definition at line 973 of file FGInitialCondition.cpp.

 {
   double altitudeASL = GetAltitudeASLFtIC();
   double rho = Atmosphere->GetDensity(altitudeASL);
   double rhoSL = Atmosphere->GetDensitySL();
   return fpstokts * vt * sqrt(rho/rhoSL);
 }

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◆ GetVgroundFpsIC()

double GetVgroundFpsIC ( void ) const

inline

Gets the initial ground velocity.

Returns: Initial ground velocity in feet/second

Definition at line 470 of file FGInitialCondition.h.

470 { return vUVW_NED.Magnitude(eU, eV); }

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◆ GetVgroundKtsIC()

double GetVgroundKtsIC ( void ) const

inline

Gets the initial ground speed.

Returns: Initial ground speed in knots

Definition at line 325 of file FGInitialCondition.h.

325 { return GetVgroundFpsIC() * fpstokts; }

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◆ GetVNorthFpsIC()

double GetVNorthFpsIC ( void ) const

inline

Gets the initial local frame X (North) velocity.

Returns: Initial local frame X (North) axis velocity in feet/second.

Definition at line 546 of file FGInitialCondition.h.

546 { return vUVW_NED(eU); }

◆ GetVtrueFpsIC()

double GetVtrueFpsIC ( void ) const

inline

Gets the initial true velocity.

Returns: Initial true velocity in feet/second

Definition at line 474 of file FGInitialCondition.h.

474 { return vt; }

◆ GetVtrueKtsIC()

double GetVtrueKtsIC ( void ) const

inline

Gets the initial true velocity.

Returns: Initial true airspeed in knots.

Definition at line 329 of file FGInitialCondition.h.

329 { return vt*fpstokts; }

◆ GetWBodyFpsIC()

double GetWBodyFpsIC ( void ) const

inline

Gets the initial body axis Z velocity.

Returns: Initial body axis Z velocity in feet/second.

Definition at line 542 of file FGInitialCondition.h.

542 { return GetBodyVelFpsIC(eW); }

◆ GetWindDFpsIC()

double GetWindDFpsIC ( void ) const

inline

Gets the initial wind velocity in local frame.

Returns: Initial wind velocity downwards in feet/second

Definition at line 506 of file FGInitialCondition.h.

506 { return GetNEDWindFpsIC(eZ); }

◆ GetWindDirDegIC()

double GetWindDirDegIC ( void ) const

Gets the initial wind direction.

Returns: Initial wind direction in feet/second

Definition at line 915 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 _vWIND_NED = _vt_NED - vUVW_NED;
  
   return _vWIND_NED(eV) == 0.0 ? 0.0
                                : atan2(_vWIND_NED(eV), _vWIND_NED(eU))*radtodeg;
 }

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◆ GetWindEFpsIC()

double GetWindEFpsIC ( void ) const

inline

Gets the initial wind velocity in local frame.

Returns: Initial wind velocity eastwards in feet/second

Definition at line 502 of file FGInitialCondition.h.

502 { return GetNEDWindFpsIC(eY); }

◆ GetWindFpsIC()

double GetWindFpsIC ( void ) const

Gets the initial total wind velocity in feet/sec.

Returns: Initial wind velocity in feet/second

Definition at line 938 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 _vWIND_NED = _vt_NED - vUVW_NED;
  
   return _vWIND_NED.Magnitude(eU, eV);
 }

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◆ GetWindNEDFpsIC()

const FGColumnVector3 GetWindNEDFpsIC ( void ) const

inline

Gets the initial wind velocity in the NED local frame.

Returns: Initial wind velocity in NED frame in feet/second

Definition at line 490 of file FGInitialCondition.h.

                                                     {
     const FGMatrix33& Tb2l = orientation.GetTInv();
     FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
     return _vt_NED - vUVW_NED;
   }

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◆ GetWindNFpsIC()

double GetWindNFpsIC ( void ) const

inline

Gets the initial wind velocity in local frame.

Returns: Initial wind velocity toward north in feet/second

Definition at line 498 of file FGInitialCondition.h.

498 { return GetNEDWindFpsIC(eX); }

◆ GetWindUFpsIC()

double GetWindUFpsIC ( void ) const

inline

Gets the initial body axis X wind velocity.

Returns: Initial body axis X wind velocity in feet/second

Definition at line 478 of file FGInitialCondition.h.

478 { return GetBodyWindFpsIC(eU); }

◆ GetWindVFpsIC()

double GetWindVFpsIC ( void ) const

inline

Gets the initial body axis Y wind velocity.

Returns: Initial body axis Y wind velocity in feet/second

Definition at line 482 of file FGInitialCondition.h.

482 { return GetBodyWindFpsIC(eV); }

◆ GetWindWFpsIC()

double GetWindWFpsIC ( void ) const

inline

Gets the initial body axis Z wind velocity.

Returns: Initial body axis Z wind velocity in feet/second

Definition at line 486 of file FGInitialCondition.h.

486 { return GetBodyWindFpsIC(eW); }

◆ IsEngineRunning()

bool IsEngineRunning ( unsigned int n ) const

inline

Is an engine running ?

Parameters

index of the engine to be checked

Returns: true if the engine is running.

Definition at line 679 of file FGInitialCondition.h.

679 { return (enginesRunning & (1 << n)) != 0; }

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◆ Load()

bool Load	(	const SGPath &	rstname,
		bool	useStoredPath = `true`
	)

Loads the initial conditions.

Parameters

rstname	The name of an initial conditions file
useStoredPath	true if the stored path to the IC file should be used

Returns: true if successful

Definition at line 1002 of file FGInitialCondition.cpp.

 {
   SGPath init_file_name;
   if(useStoredPath && rstfile.isRelative()) {
     init_file_name = fdmex->GetFullAircraftPath()/rstfile.utf8Str();
   } else {
     init_file_name = rstfile;
   }
  
   FGXMLFileRead XMLFileRead;
   Element* document = XMLFileRead.LoadXMLDocument(init_file_name);
  
   // Make sure that the document is valid
   if (!document) {
     stringstream s;
     s << "File: " << init_file_name << " could not be read.";
     cerr << s.str() << endl;
     throw BaseException(s.str());
   }
  
   if (document->GetName() != string("initialize")) {
     stringstream s;
     s << "File: " << init_file_name << " is not a reset file.";
     cerr << s.str() << endl;
     throw BaseException(s.str());
   }
  
   double version = HUGE_VAL;
   bool result = false;
  
   if (document->HasAttribute("version"))
     version = document->GetAttributeValueAsNumber("version");
  
   if (version == HUGE_VAL) {
     result = Load_v1(document); // Default to the old version
   } else if (version >= 3.0) {
     const string s("Only initialization file formats 1 and 2 are currently supported");
     cerr << document->ReadFrom() << endl << s << endl;
     throw BaseException(s);
   } else if (version >= 2.0) {
     result = Load_v2(document);
   } else if (version >= 1.0) {
     result = Load_v1(document);
   }
  
   // Check to see if any engines are specified to be initialized in a running state
   Element* running_elements = document->FindElement("running");
   while (running_elements) {
     int engineNumber = int(running_elements->GetDataAsNumber());
     enginesRunning |= engineNumber == -1 ? engineNumber : 1 << engineNumber;
     running_elements = document->FindNextElement("running");
   }
  
   return result;
 }

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◆ ResetIC()

void ResetIC	(	double	u0,
		double	v0,
		double	w0,
		double	p0,
		double	q0,
		double	r0,
		double	alpha0,
		double	beta0,
		double	phi0,
		double	theta0,
		double	psi0,
		double	latitudeRad0,
		double	longitudeRad0,
		double	altitudeAGL0,
		double	gamma0
	)

Resets the IC data structure to new values.

Parameters

u,v,w,...

Definition at line 83 of file FGInitialCondition.cpp.

 {
   double calpha = cos(alpha0), cbeta = cos(beta0);
   double salpha = sin(alpha0), sbeta = sin(beta0);
  
   InitializeIC();
  
   vPQR_body = {p0, q0, r0};
   alpha = alpha0;  beta = beta0;
  
   position.SetLongitude(lonRad0);
   position.SetLatitude(latRad0);
   fdmex->GetInertial()->SetAltitudeAGL(position, altAGLFt0);
   lastLatitudeSet = setgeoc;
   lastAltitudeSet = setagl;
  
   orientation = FGQuaternion(phi0, theta0, psi0);
   const FGMatrix33& Tb2l = orientation.GetTInv();
  
   vUVW_NED = Tb2l * FGColumnVector3(u0, v0, w0);
   vt = vUVW_NED.Magnitude();
   lastSpeedSet = setuvw;
  
   Tw2b = { calpha*cbeta, -calpha*sbeta,  -salpha,
                   sbeta,         cbeta,      0.0,
            salpha*cbeta, -salpha*sbeta,   calpha };
   Tb2w = Tw2b.Transposed();
  
   SetFlightPathAngleRadIC(gamma0);
 }

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◆ SetAlphaDegIC()

void SetAlphaDegIC ( double a )

inline

Sets angle of attack initial condition in degrees.

Parameters

a	Alpha in degrees

Definition at line 254 of file FGInitialCondition.h.

254 { SetAlphaRadIC(a*degtorad); }

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◆ SetAlphaRadIC()

void SetAlphaRadIC ( double alpha )

Sets the initial angle of attack.

Parameters

alpha Initial angle of attack in radians

Definition at line 312 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   calcThetaBeta(alfa, _vt_NED);
 }

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◆ SetAltitudeAGLFtIC()

void SetAltitudeAGLFtIC ( double agl )

Sets the initial Altitude above ground level.

Parameters

agl	Altitude above ground level in feet

Definition at line 676 of file FGInitialCondition.cpp.

 {
   double altitudeASL = GetAltitudeASLFtIC();
   double pressure = Atmosphere->GetPressure(altitudeASL);
   double soundSpeed = Atmosphere->GetSoundSpeed(altitudeASL);
   double rho = Atmosphere->GetDensity(altitudeASL);
   double rhoSL = Atmosphere->GetDensitySL();
  
   double mach0 = vt / soundSpeed;
   double vc0 = VcalibratedFromMach(mach0, pressure);
   double ve0 = vt * sqrt(rho/rhoSL);
  
   switch(lastLatitudeSet) {
   case setgeod:
     fdmex->GetInertial()->SetAltitudeAGL(position, agl);
     break;
   case setgeoc:
     {
       double a = fdmex->GetInertial()->GetSemimajor();
       double b = fdmex->GetInertial()->GetSemiminor();
       double e2 = 1.0-b*b/(a*a);
       double tanlat = tan(position.GetLatitude());
       double n = e2;
       double prev_n = 1.0;
       int iter = 0;
       double longitude = position.GetLongitude();
       double alt = position.GetGeodAltitude();
       double h = -2.0*max(a,b);
       double geodLat;
       while ((fabs(n-prev_n) > 1E-15 || fabs(h-agl) > 1E-10) && iter < 10) {
         geodLat = atan(tanlat/(1-n));
         position.SetPositionGeodetic(longitude, geodLat, alt);
         h = GetAltitudeAGLFtIC();
         alt += agl-h;
         double sinGeodLat = sin(geodLat);
         double N = a/sqrt(1-e2*sinGeodLat*sinGeodLat);
         prev_n = n;
         n = e2*N/(N+alt);
         iter++;
       }
     }
     break;
   }
  
   altitudeASL = GetAltitudeASLFtIC();
   soundSpeed = Atmosphere->GetSoundSpeed(altitudeASL);
   rho = Atmosphere->GetDensity(altitudeASL);
   pressure = Atmosphere->GetPressure(altitudeASL);
  
   switch(lastSpeedSet) {
     case setvc:
       mach0 = MachFromVcalibrated(vc0, pressure);
       SetVtrueFpsIC(mach0 * soundSpeed);
       break;
     case setmach:
       SetVtrueFpsIC(mach0 * soundSpeed);
       break;
     case setve:
       SetVtrueFpsIC(ve0 * sqrt(rhoSL/rho));
       break;
     default: // Make the compiler stop complaining about missing enums
       break;
   }
  
   lastAltitudeSet = setagl;
 }

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◆ SetAltitudeASLFtIC()

void SetAltitudeASLFtIC ( double altitudeASL )

Sets the altitude above sea level initial condition in feet.

Parameters

altitudeASL Altitude above sea level in feet

Definition at line 748 of file FGInitialCondition.cpp.

 {
   double altitudeASL = GetAltitudeASLFtIC();
   double pressure = Atmosphere->GetPressure(altitudeASL);
   double soundSpeed = Atmosphere->GetSoundSpeed(altitudeASL);
   double rho = Atmosphere->GetDensity(altitudeASL);
   double rhoSL = Atmosphere->GetDensitySL();
  
   double mach0 = vt / soundSpeed;
   double vc0 = VcalibratedFromMach(mach0, pressure);
   double ve0 = vt * sqrt(rho/rhoSL);
  
   switch(lastLatitudeSet) {
   case setgeod:
     {
       // Given an altitude above the mean sea level (or a position radius which
       // is the same) and a geodetic latitude, compute the geodetic altitude.
       double a = fdmex->GetInertial()->GetSemimajor();
       double b = fdmex->GetInertial()->GetSemiminor();
       double e2 = 1.0-b*b/(a*a);
       double geodLatitude = position.GetGeodLatitudeRad();
       double cosGeodLat = cos(geodLatitude);
       double sinGeodLat = sin(geodLatitude);
       double N = a/sqrt(1-e2*sinGeodLat*sinGeodLat);
       double geodAlt = 0.0;
       double n = e2;
       double prev_n = 1.0;
       int iter = 0;
       // Use tan or cotan to solve the geodetic altitude to avoid floating point
       // exceptions.
       if (cosGeodLat > fabs(sinGeodLat)) { // tan() can safely be used.
         double tanGeodLat = sinGeodLat/cosGeodLat;
         double x0 = N*e2*cosGeodLat;
         double x = 0.0;
         while (fabs(n-prev_n) > 1E-15 && iter < 10) {
           double tanLat = (1-n)*tanGeodLat; // See Stevens & Lewis 1.6-14
           double cos2Lat = 1./(1.+tanLat*tanLat);
           double slr = b/sqrt(1.-e2*cos2Lat);
           double R = slr + alt;
           x = R*sqrt(cos2Lat); // OK, cos(latitude) is always positive.
           prev_n = n;
           n = x0/x;
           iter++;
         }
         geodAlt = x/cosGeodLat-N;
       }
       else { // better use cotan (i.e. 1./tan())
         double cotanGeodLat = cosGeodLat/sinGeodLat;
         double z0 = N*e2*sinGeodLat;
         double z = 0.0;
         while (fabs(n-prev_n) > 1E-15 && iter < 10) {
           double cotanLat = cotanGeodLat/(1-n);
           double sin2Lat = 1./(1.+cotanLat*cotanLat);
           double cos2Lat = 1.-sin2Lat;
           double slr = b/sqrt(1.-e2*cos2Lat);
           double R = slr + alt;
           z = R*sign(cotanLat)*sqrt(sin2Lat);
           prev_n = n;
           n = z0/(z0+z);
           iter++;
         }
         geodAlt = z/sinGeodLat-N*(1-e2);
       }
  
       double longitude = position.GetLongitude();
       position.SetPositionGeodetic(longitude, geodLatitude, geodAlt);
     }
     break;
   case setgeoc:
     {
       double slr = position.GetSeaLevelRadius();
       position.SetRadius(slr+alt);
     }
     break;
   }
  
   altitudeASL = position.GetGeodAltitude();
   soundSpeed = Atmosphere->GetSoundSpeed(altitudeASL);
   rho = Atmosphere->GetDensity(altitudeASL);
   pressure = Atmosphere->GetPressure(altitudeASL);
  
   switch(lastSpeedSet) {
     case setvc:
       mach0 = MachFromVcalibrated(vc0, pressure);
       SetVtrueFpsIC(mach0 * soundSpeed);
       break;
     case setmach:
       SetVtrueFpsIC(mach0 * soundSpeed);
       break;
     case setve:
       SetVtrueFpsIC(ve0 * sqrt(rhoSL/rho));
       break;
     default: // Make the compiler stop complaining about missing enums
       break;
   }
  
   lastAltitudeSet = setasl;
 }

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◆ SetBetaDegIC()

void SetBetaDegIC ( double b )

inline

Sets angle of sideslip initial condition in degrees.

Parameters

B	Beta in degrees

Definition at line 258 of file FGInitialCondition.h.

258 { SetBetaRadIC(b*degtorad);}

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◆ SetBetaRadIC()

void SetBetaRadIC ( double beta )

Sets the initial sideslip angle.

Parameters

beta	Initial angle of sideslip in radians.

Definition at line 397 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 vOrient = orientation.GetEuler();
  
   beta = bta;
   double calpha = cos(alpha), salpha = sin(alpha);
   double cbeta = cos(beta), sbeta = sin(beta);
   double cphi = orientation.GetCosEuler(ePhi), sphi = orientation.GetSinEuler(ePhi);
   FGMatrix33 TphiInv(1.,   0.,   0.,
                      0., cphi,-sphi,
                      0., sphi, cphi);
  
   Tw2b = { calpha*cbeta, -calpha*sbeta,  -salpha,
                   sbeta,         cbeta,      0.0,
            salpha*cbeta, -salpha*sbeta,   calpha };
   Tb2w = Tw2b.Transposed();
  
   FGColumnVector3 vf = TphiInv * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 v0xy(_vt_NED(eX), _vt_NED(eY), 0.);
   FGColumnVector3 v1xy(sqrt(v0xy(eX)*v0xy(eX)+v0xy(eY)*v0xy(eY)-vf(eY)*vf(eY)),vf(eY),0.);
   v0xy.Normalize();
   v1xy.Normalize();
  
   if (vf(eX) < 0.) v0xy(eX) *= -1.0;
  
   double sinPsi = (v1xy * v0xy)(eZ);
   double cosPsi = DotProduct(v0xy, v1xy);
   vOrient(ePsi) = atan2(sinPsi, cosPsi);
   FGMatrix33 Tpsi( cosPsi, sinPsi, 0.,
                   -sinPsi, cosPsi, 0.,
                       0.,     0., 1.);
  
   FGColumnVector3 v2xz = Tpsi * _vt_NED;
   FGColumnVector3 vfxz = vf;
   v2xz(eV) = vfxz(eV) = 0.0;
   v2xz.Normalize();
   vfxz.Normalize();
   double sinTheta = (v2xz * vfxz)(eY);
   vOrient(eTht) = -asin(sinTheta);
  
   orientation = FGQuaternion(vOrient);
 }

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◆ SetClimbRateFpmIC()

void SetClimbRateFpmIC ( double roc )

inline

Sets the climb rate initial condition in feet/minute.

Parameters

roc	Rate of Climb in feet/minute

Definition at line 281 of file FGInitialCondition.h.

281 { SetClimbRateFpsIC(roc/60.0); }

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◆ SetClimbRateFpsIC()

void SetClimbRateFpsIC ( double roc )

Sets the initial climb rate.

Parameters

roc	Initial Rate of climb in feet/second

Definition at line 283 of file FGInitialCondition.cpp.

 {
   if (fabs(hdot) > vt) {
     cerr << "The climb rate cannot be higher than the true speed." << endl;
     return;
   }
  
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 _WIND_NED = _vt_NED - vUVW_NED;
   double hdot0 = -_vt_NED(eW);
  
   if (fabs(hdot0) < vt) { // Is this check really needed ?
     double scale = sqrt((vt*vt-hdot*hdot)/(vt*vt-hdot0*hdot0));
     _vt_NED(eU) *= scale;
     _vt_NED(eV) *= scale;
   }
   _vt_NED(eW) = -hdot;
   vUVW_NED = _vt_NED - _WIND_NED;
  
   // Updating the angles theta and beta to keep the true airspeed amplitude
   calcThetaBeta(alpha, _vt_NED);
 }

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◆ SetCrossWindKtsIC()

void SetCrossWindKtsIC ( double cross )

Sets the initial crosswind speed.

Parameters

cross Initial crosswind speed, positive from left to right

Definition at line 527 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 _vWIND_NED = _vt_NED - vUVW_NED;
   FGColumnVector3 _vCROSS(-orientation.GetSinEuler(ePsi), orientation.GetCosEuler(ePsi), 0.);
  
   // Gram-Schmidt process is used to remove the existing cross wind component
   _vWIND_NED -= DotProduct(_vWIND_NED, _vCROSS) * _vCROSS;
   // Which is now replaced by the new value. The input cross wind is expected
   // in knots, so first convert to fps, which is the internal unit used.
   _vWIND_NED += (cross * ktstofps) * _vCROSS;
   _vt_NED = vUVW_NED + _vWIND_NED;
   vt = _vt_NED.Magnitude();
  
   calcAeroAngles(_vt_NED);
 }

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◆ SetFlightPathAngleDegIC()

void SetFlightPathAngleDegIC ( double gamma )

inline

Sets the flight path angle initial condition in degrees.

Parameters

gamma Flight path angle in degrees

Definition at line 285 of file FGInitialCondition.h.

286 { SetClimbRateFpsIC(vt*sin(gamma*degtorad)); }

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◆ SetFlightPathAngleRadIC()

void SetFlightPathAngleRadIC ( double gamma )

inline

Sets the initial flight path angle.

Parameters

gamma Initial flight path angle in radians

Definition at line 574 of file FGInitialCondition.h.

575 { SetClimbRateFpsIC(vt*sin(gamma)); }

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◆ SetGeodLatitudeDegIC()

void SetGeodLatitudeDegIC ( double glat )

inline

Sets the initial geodetic latitude.

This method modifies the geodetic altitude in order to keep the altitude above sea level unchanged.

Parameters

glat	Initial geodetic latitude in degrees

Definition at line 308 of file FGInitialCondition.h.

309 { SetGeodLatitudeRadIC(glat*degtorad); }

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◆ SetGeodLatitudeRadIC()

void SetGeodLatitudeRadIC ( double glat )

Sets the initial geodetic latitude.

This method modifies the geodetic altitude in order to keep the altitude above sea level unchanged.

Parameters

glat	Initial geodetic latitude in radians

Definition at line 849 of file FGInitialCondition.cpp.

 {
   double lon = position.GetLongitude();
   lastLatitudeSet = setgeod;
  
   switch (lastAltitudeSet)
   {
   case setagl:
     {
       double agl = GetAltitudeAGLFtIC();
       position.SetPositionGeodetic(lon, geodLatitude, 0.);
       fdmex->GetInertial()->SetAltitudeAGL(position, agl);
     }
     break;
   case setasl:
     {
       double asl = GetAltitudeASLFtIC();
       position.SetPositionGeodetic(lon, geodLatitude, 0.);
       SetAltitudeASLFtIC(asl);
     }
     break;
   }
 }

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◆ SetHeadWindKtsIC()

void SetHeadWindKtsIC ( double head )

Sets the initial headwind velocity.

Parameters

head	Initial headwind speed in knots

Definition at line 550 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 _vWIND_NED = _vt_NED - vUVW_NED;
   // This is a head wind, so the direction vector for the wind
   // needs to be set opposite to the heading the aircraft
   // is taking. So, the cos and sin of the heading (psi)
   // are negated in the line below.
   FGColumnVector3 _vHEAD(-orientation.GetCosEuler(ePsi), -orientation.GetSinEuler(ePsi), 0.);
  
   // Gram-Schmidt process is used to remove the existing head wind component
   _vWIND_NED -= DotProduct(_vWIND_NED, _vHEAD) * _vHEAD;
   // Which is now replaced by the new value. The input head wind is expected
   // in knots, so first convert to fps, which is the internal unit used.
   _vWIND_NED += (head * ktstofps) * _vHEAD;
   _vt_NED = vUVW_NED + _vWIND_NED;
  
   vt = _vt_NED.Magnitude();
  
   calcAeroAngles(_vt_NED);
 }

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◆ SetLatitudeDegIC()

void SetLatitudeDegIC ( double lat )

inline

Sets the initial latitude.

Parameters

lat	Initial latitude in degrees

Definition at line 302 of file FGInitialCondition.h.

302 { SetLatitudeRadIC(lat*degtorad); }

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◆ SetLatitudeRadIC()

void SetLatitudeRadIC ( double lat )

Sets the initial latitude.

Parameters

lat	Initial latitude in radians

Definition at line 875 of file FGInitialCondition.cpp.

 {
   double altitude;
  
   lastLatitudeSet = setgeoc;
  
   switch(lastAltitudeSet) {
   case setagl:
     altitude = GetAltitudeAGLFtIC();
     position.SetLatitude(lat);
     SetAltitudeAGLFtIC(altitude);
     break;
   default:
     altitude = GetAltitudeASLFtIC();
     position.SetLatitude(lat);
     SetAltitudeASLFtIC(altitude);
     break;
   }
 }

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◆ SetLongitudeDegIC()

void SetLongitudeDegIC ( double lon )

inline

Sets the initial longitude.

Parameters

lon	Initial longitude in degrees

Definition at line 313 of file FGInitialCondition.h.

313 { SetLongitudeRadIC(lon*degtorad); }

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◆ SetLongitudeRadIC()

void SetLongitudeRadIC ( double lon )

Sets the initial longitude.

Parameters

lon	Initial longitude in radians

Definition at line 897 of file FGInitialCondition.cpp.

 {
   double altitude;
  
   switch(lastAltitudeSet) {
   case setagl:
     altitude = GetAltitudeAGLFtIC();
     position.SetLongitude(lon);
     SetAltitudeAGLFtIC(altitude);
     break;
   default:
     position.SetLongitude(lon);
     break;
   }
 }

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◆ SetMachIC()

void SetMachIC ( double mach )

Set mach initial condition.

Parameters

mach	Mach number

Definition at line 163 of file FGInitialCondition.cpp.

 {
   double altitudeASL = GetAltitudeASLFtIC();
   double soundSpeed = Atmosphere->GetSoundSpeed(altitudeASL);
   SetVtrueFpsIC(mach*soundSpeed);
   lastSpeedSet = setmach;
 }

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◆ SetPhiDegIC()

void SetPhiDegIC ( double phi )

inline

Sets the roll angle initial condition in degrees.

Parameters

phi	roll angle in degrees

Definition at line 273 of file FGInitialCondition.h.

273 { SetPhiRadIC(phi*degtorad);}

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◆ SetPhiRadIC()

void SetPhiRadIC ( double phi )

inline

Sets the initial roll angle.

Parameters

phi	Initial roll angle in radians

Definition at line 587 of file FGInitialCondition.h.

587 { SetEulerAngleRadIC(ePhi, phi); }

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◆ SetPRadpsIC()

void SetPRadpsIC ( double P )

inline

Sets the initial body axis roll rate.

Parameters

P	Initial roll rate in radians/second

Definition at line 428 of file FGInitialCondition.h.

428 { vPQR_body(eP) = P; }

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◆ SetPsiDegIC()

void SetPsiDegIC ( double psi )

inline

Sets the heading angle initial condition in degrees.

Parameters

psi	Heading angle in degrees

Definition at line 277 of file FGInitialCondition.h.

277 { SetPsiRadIC(psi*degtorad); }

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◆ SetPsiRadIC()

void SetPsiRadIC ( double psi )

inline

Sets the initial heading angle.

Parameters

psi	Initial heading angle in radians

Definition at line 595 of file FGInitialCondition.h.

595 { SetEulerAngleRadIC(ePsi, psi); }

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◆ SetQRadpsIC()

void SetQRadpsIC ( double Q )

inline

Sets the initial body axis pitch rate.

Parameters

Q	Initial pitch rate in radians/second

Definition at line 432 of file FGInitialCondition.h.

432 { vPQR_body(eQ) = Q; }

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◆ SetRRadpsIC()

void SetRRadpsIC ( double R )

inline

Sets the initial body axis yaw rate.

Parameters

R	initial yaw rate in radians/second

Definition at line 436 of file FGInitialCondition.h.

436 { vPQR_body(eR) = R; }

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◆ SetTargetNlfIC()

void SetTargetNlfIC ( double nlf )

inline

Sets the target normal load factor.

Parameters

nlf	Normal load factor

Definition at line 613 of file FGInitialCondition.h.

613 { targetNlfIC=nlf; }

◆ SetTerrainElevationFtIC()

void SetTerrainElevationFtIC ( double elev )

Sets the initial terrain elevation.

Parameters

elev	Initial terrain elevation in feet

Definition at line 638 of file FGInitialCondition.cpp.

 {
   double agl = GetAltitudeAGLFtIC();
   fdmex->GetInertial()->SetTerrainElevation(elev);
  
   if (lastAltitudeSet == setagl)
     SetAltitudeAGLFtIC(agl);
 }

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◆ SetThetaDegIC()

void SetThetaDegIC ( double theta )

inline

Sets pitch angle initial condition in degrees.

Parameters

theta Theta (pitch) angle in degrees

Definition at line 262 of file FGInitialCondition.h.

262 { SetThetaRadIC(theta*degtorad); }

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◆ SetThetaRadIC()

void SetThetaRadIC ( double theta )

inline

Sets the initial pitch angle.

Parameters

theta Initial pitch angle in radians

Definition at line 591 of file FGInitialCondition.h.

591 { SetEulerAngleRadIC(eTht, theta); }

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◆ SetUBodyFpsIC()

void SetUBodyFpsIC ( double ubody )

inline

Sets the initial body axis X velocity.

Parameters

ubody Initial X velocity in feet/second

Definition at line 404 of file FGInitialCondition.h.

404 { SetBodyVelFpsIC(eU, ubody); }

◆ SetVBodyFpsIC()

void SetVBodyFpsIC ( double vbody )

inline

Sets the initial body axis Y velocity.

Parameters

vbody Initial Y velocity in feet/second

Definition at line 408 of file FGInitialCondition.h.

408 { SetBodyVelFpsIC(eV, vbody); }

◆ SetVcalibratedKtsIC()

void SetVcalibratedKtsIC ( double vc )

Set calibrated airspeed initial condition in knots.

Parameters

vc	Calibrated airspeed in knots

Definition at line 173 of file FGInitialCondition.cpp.

 {
   double altitudeASL = GetAltitudeASLFtIC();
   double pressure = Atmosphere->GetPressure(altitudeASL);
   double mach = MachFromVcalibrated(fabs(vcas)*ktstofps, pressure);
   double soundSpeed = Atmosphere->GetSoundSpeed(altitudeASL);
  
   SetVtrueFpsIC(mach * soundSpeed);
   lastSpeedSet = setvc;
 }

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◆ SetVDownFpsIC()

void SetVDownFpsIC ( double vd )

inline

Sets the initial local axis down velocity.

Parameters

vd	Initial down velocity in feet/second

Definition at line 424 of file FGInitialCondition.h.

424 { SetNEDVelFpsIC(eW, vd); }

◆ SetVEastFpsIC()

void SetVEastFpsIC ( double ve )

inline

Sets the initial local axis east velocity.

Parameters

ve	Initial east velocity in feet/second

Definition at line 420 of file FGInitialCondition.h.

420 { SetNEDVelFpsIC(eV, ve); }

◆ SetVequivalentKtsIC()

void SetVequivalentKtsIC ( double ve )

Set equivalent airspeed initial condition in knots.

Parameters

ve	Equivalent airspeed in knots

Definition at line 152 of file FGInitialCondition.cpp.

 {
   double altitudeASL = GetAltitudeASLFtIC();
   double rho = Atmosphere->GetDensity(altitudeASL);
   double rhoSL = Atmosphere->GetDensitySL();
   SetVtrueFpsIC(ve*ktstofps*sqrt(rhoSL/rho));
   lastSpeedSet = setve;
 }

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◆ SetVgroundFpsIC()

void SetVgroundFpsIC ( double vg )

Sets the initial ground speed.

Parameters

vg	Initial ground speed in feet/second

Definition at line 235 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 _vWIND_NED = _vt_NED - vUVW_NED;
  
   vUVW_NED(eU) = vg * orientation.GetCosEuler(ePsi);
   vUVW_NED(eV) = vg * orientation.GetSinEuler(ePsi);
   vUVW_NED(eW) = 0.;
   _vt_NED = vUVW_NED + _vWIND_NED;
   vt = _vt_NED.Magnitude();
  
   calcAeroAngles(_vt_NED);
  
   lastSpeedSet = setvg;
 }

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◆ SetVgroundKtsIC()

void SetVgroundKtsIC ( double vg )

inline

Set ground speed initial condition in knots.

Parameters

vg	Ground speed in knots

Definition at line 246 of file FGInitialCondition.h.

246 { SetVgroundFpsIC(vg*ktstofps); }

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◆ SetVNorthFpsIC()

void SetVNorthFpsIC ( double vn )

inline

Sets the initial local axis north velocity.

Parameters

vn	Initial north velocity in feet/second

Definition at line 416 of file FGInitialCondition.h.

416 { SetNEDVelFpsIC(eU, vn); }

◆ SetVtrueFpsIC()

void SetVtrueFpsIC ( double vt )

Sets the initial true airspeed.

Parameters

vt	Initial true airspeed in feet/second

Definition at line 259 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 _vWIND_NED = _vt_NED - vUVW_NED;
  
   if (vt > 0.1)
     _vt_NED *= vtrue / vt;
   else
     _vt_NED = Tb2l * Tw2b * FGColumnVector3(vtrue, 0., 0.);
  
   vt = vtrue;
   vUVW_NED = _vt_NED - _vWIND_NED;
  
   calcAeroAngles(_vt_NED);
  
   lastSpeedSet = setvt;
 }

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◆ SetVtrueKtsIC()

void SetVtrueKtsIC ( double vtrue )

inline

Set true airspeed initial condition in knots.

Parameters

vtrue True airspeed in knots

Definition at line 242 of file FGInitialCondition.h.

242 { SetVtrueFpsIC(vtrue*ktstofps); }

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◆ SetWBodyFpsIC()

void SetWBodyFpsIC ( double wbody )

inline

Sets the initial body axis Z velocity.

Parameters

wbody Initial Z velocity in feet/second

Definition at line 412 of file FGInitialCondition.h.

412 { SetBodyVelFpsIC(eW, wbody); }

◆ SetWindDirDegIC()

void SetWindDirDegIC ( double dir )

Sets the initial wind direction.

Parameters

dir	Initial direction wind is coming from in degrees

Definition at line 620 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 _vWIND_NED = _vt_NED - vUVW_NED;
   double mag = _vWIND_NED.Magnitude(eU, eV);
   FGColumnVector3 _vHEAD(mag*cos(dir*degtorad), mag*sin(dir*degtorad), 0.);
  
   _vWIND_NED(eU) = _vHEAD(eU);
   _vWIND_NED(eV) = _vHEAD(eV);
   _vt_NED = vUVW_NED + _vWIND_NED;
   vt = _vt_NED.Magnitude();
  
   calcAeroAngles(_vt_NED);
 }

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◆ SetWindDownKtsIC()

void SetWindDownKtsIC ( double wD )

Sets the initial wind downward speed.

Parameters

wD	Initial downward wind speed in knots

Definition at line 578 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
  
   _vt_NED(eW) = vUVW_NED(eW) + wD;
   vt = _vt_NED.Magnitude();
  
   calcAeroAngles(_vt_NED);
 }

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◆ SetWindMagKtsIC()

void SetWindMagKtsIC ( double mag )

Sets the initial total wind speed.

Parameters

mag	Initial wind velocity magnitude in knots

Definition at line 594 of file FGInitialCondition.cpp.

 {
   const FGMatrix33& Tb2l = orientation.GetTInv();
   FGColumnVector3 _vt_NED = Tb2l * Tw2b * FGColumnVector3(vt, 0., 0.);
   FGColumnVector3 _vWIND_NED = _vt_NED - vUVW_NED;
   FGColumnVector3 _vHEAD(_vWIND_NED(eU), _vWIND_NED(eV), 0.);
   double windMag = _vHEAD.Magnitude();
  
   if (windMag > 0.001)
     _vHEAD *= (mag*ktstofps) / windMag;
   else
     _vHEAD = {mag*ktstofps, 0., 0.};
  
   _vWIND_NED(eU) = _vHEAD(eU);
   _vWIND_NED(eV) = _vHEAD(eV);
   _vt_NED = vUVW_NED + _vWIND_NED;
   vt = _vt_NED.Magnitude();
  
   calcAeroAngles(_vt_NED);
 }

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◆ SetWindNEDFpsIC()

void SetWindNEDFpsIC	(	double	wN,
		double	wE,
		double	wD
	)

Sets the initial wind velocity.

Parameters

wN	Initial wind velocity in local north direction, feet/second
wE	Initial wind velocity in local east direction, feet/second
wD	Initial wind velocity in local down direction, feet/second

Definition at line 514 of file FGInitialCondition.cpp.

 {
   FGColumnVector3 _vt_NED = vUVW_NED + FGColumnVector3(wN, wE, wD);
   vt = _vt_NED.Magnitude();
  
   calcAeroAngles(_vt_NED);
 }

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◆ TrimRequested()

int TrimRequested ( void ) const

inline

Does initialization file call for trim ?

Returns: Trim type, if any requested (version 1).

Definition at line 683 of file FGInitialCondition.h.

683 { return trimRequested; }

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

Detailed Description

Usage Notes

Speed

Alpha,Gamma, and Theta

Properties

Public Member Functions

Additional Inherited Members

Member Function Documentation

◆ GetAlphaDegIC()

◆ GetAlphaRadIC()

◆ GetAltitudeAGLFtIC()

◆ GetAltitudeASLFtIC()

◆ GetBetaDegIC()

◆ GetBetaRadIC()

◆ GetClimbRateFpmIC()

◆ GetClimbRateFpsIC()

◆ GetEarthPositionAngleIC()

◆ GetFlightPathAngleDegIC()

◆ GetFlightPathAngleRadIC()

◆ GetGeodLatitudeDegIC()

◆ GetGeodLatitudeRadIC()

◆ GetLatitudeDegIC()

◆ GetLatitudeRadIC()

◆ GetLongitudeDegIC()

◆ GetLongitudeRadIC()

◆ GetMachIC()

◆ GetOrientation()

◆ GetPhiDegIC()

◆ GetPhiRadIC()

◆ GetPosition()

◆ GetPQRRadpsIC()

◆ GetPRadpsIC()

◆ GetPsiDegIC()

◆ GetPsiRadIC()

◆ GetQRadpsIC()

◆ GetRRadpsIC()

◆ GetSpeedSet()

◆ GetTargetNlfIC()

◆ GetTerrainElevationFtIC()

◆ GetThetaDegIC()

◆ GetThetaRadIC()

◆ GetUBodyFpsIC()

◆ GetUVWFpsIC()

◆ GetVBodyFpsIC()

◆ GetVcalibratedKtsIC()

◆ GetVDownFpsIC()

◆ GetVEastFpsIC()

◆ GetVequivalentKtsIC()

◆ GetVgroundFpsIC()

◆ GetVgroundKtsIC()

◆ GetVNorthFpsIC()

◆ GetVtrueFpsIC()

◆ GetVtrueKtsIC()

◆ GetWBodyFpsIC()

◆ GetWindDFpsIC()

◆ GetWindDirDegIC()

◆ GetWindEFpsIC()

◆ GetWindFpsIC()

◆ GetWindNEDFpsIC()

◆ GetWindNFpsIC()

◆ GetWindUFpsIC()

◆ GetWindVFpsIC()

◆ GetWindWFpsIC()

◆ IsEngineRunning()

◆ Load()

◆ ResetIC()

◆ SetAlphaDegIC()

◆ SetAlphaRadIC()

◆ SetAltitudeAGLFtIC()

◆ SetAltitudeASLFtIC()

◆ SetBetaDegIC()

◆ SetBetaRadIC()

◆ SetClimbRateFpmIC()

◆ SetClimbRateFpsIC()

◆ SetCrossWindKtsIC()

◆ SetFlightPathAngleDegIC()

◆ SetFlightPathAngleRadIC()

◆ SetGeodLatitudeDegIC()

◆ SetGeodLatitudeRadIC()

◆ SetHeadWindKtsIC()