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Typedefs
typedef long int	F_LOGICAL

typedef char	F_CHAR

typedef long int	F_INTEGER

Functions
int __FC_DECL__()	ad_inputgate (F_CHAR *input_file)

int __FC_DECL__()	adinputgate (void)

int __FC_DECL__()	elemout (void)

int __FC_DECL__()	aerofrcintrface (F_LOGICAL FirstLoop, F_INTEGER JElem, F_REAL DFN, F_REAL DFT, F_REAL *PMA)

int __FC_DECL__()	getrotorparams (F_REAL Omega, F_REAL gamma, F_REAL VHUB, F_REAL tau)

int __FC_DECL__()	getbladeparams (F_REAL *psi)

int __FC_DECL__()	getelemparams (F_INTEGER MulTabLoc, F_REAL phi, F_REAL radius, F_REAL XGRND, F_REAL YGRND, F_REAL ZGRND)

int __FC_DECL__()	getvnvt (F_REAL VX, F_REAL VY, F_REAL VZ, F_REAL VT, F_REAL VNW, F_REAL VNE)

int __FC_DECL__()	usrmes (F_LOGICAL Logical, F_CHAR msg[], F_INTEGER code, F_CHAR level[])

int __FC_DECL__()	ad_abort (void)

int __FC_DECL__()	mbdyn_init (F_CHAR Version, F_INTEGER nblades, F_REAL *rotradius)

int __FC_DECL__()	mbdyn_ad_inputgate (F_CHAR ifname, F_INTEGER ifnamelen, F_CHAR efname, F_INTEGER efnamelen)

int __FC_DECL__()	mbdyn_true (F_LOGICAL *val)

int __FC_DECL__()	mbdyn_false (F_LOGICAL *val)

int __FC_DECL__()	mbdyn_com_data (F_INTEGER c_blade, F_INTEGER c_elem)

int __FC_DECL__()	mbdyn_sim_time (doublereal *c_time)

int __FC_DECL__()	mbdyn_time_step (F_REAL *dt)

int __FC_DECL__()	mbdyn_get_tl_const (F_REAL RLOCAL, F_INTEGER Cur_elem)

int __FC_DECL__()	mbdyn_get_hl_const (F_REAL RLOCAL, F_INTEGER Cur_elem, F_REAL *RHub)

Typedef Documentation

typedef char F_CHAR

Definition at line 64 of file NREL_AeroDyn.h.

typedef long int F_INTEGER

Definition at line 65 of file NREL_AeroDyn.h.

typedef long int F_LOGICAL

Definition at line 63 of file NREL_AeroDyn.h.

Function Documentation

int __FC_DECL__() ad_abort ( void )

int __FC_DECL__() ad_inputgate ( F_CHAR * input_file )

int __FC_DECL__() adinputgate ( void )

int __FC_DECL__() aerofrcintrface	(	F_LOGICAL *	FirstLoop,
		F_INTEGER *	JElem,
		F_REAL *	DFN,
		F_REAL *	DFT,
		F_REAL *	PMA
	)

Referenced by AeroDynModule::AssRes().

int __FC_DECL__() elemout ( void )

Referenced by getrotorparams().

int __FC_DECL__() getbladeparams ( F_REAL * psi )

Definition at line 1021 of file module-aerodyn.cc.

References AeroDynModule::GetCurrBladeR(), StructNode::GetRCurr(), AeroDynModule::iGetCurrBlade(), M_PI, module_aerodyn, AeroDynModule::pGetHubNode(), AeroDynModule::pGetNacelleNode(), R, and RotManip::VecRot().

 {
         /*
          * This comment is added by Fanzhong MENG 10th.Feb.2008
          * NOTE: Add code here too get blade Azimuth angle.
          * The 6 o'clock position is positive value
          * Variable name is *psi. [rad].
          */
         const Mat3x3& R_nacelle = ::module_aerodyn->pGetNacelleNode()->GetRCurr();
         const Mat3x3& R_hub = ::module_aerodyn->pGetHubNode()->GetRCurr();
         const Mat3x3& R_blade_root = ::module_aerodyn->GetCurrBladeR();
         Mat3x3 R = (R_hub*R_blade_root).MulTM(R_nacelle);
         Vec3 Phi(RotManip::VecRot(R));
         *psi = -Phi(3);
 
         // unwrap psi (0 <= psi <= 360)
         while (*psi < 0) {
             *psi += 2*M_PI;
         }
 
 #ifdef MODULE_AERODYN_DEBUG
         silent_cerr("getbladeparams: blade=" << ::module_aerodyn->iGetCurrBlade()
                 << " psi=" << (*psi)*180/M_PI << std::endl);
 #endif // MODULE_AERODYN_DEBUG
 
         return 0;
 }

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int __FC_DECL__() getelemparams	(	F_INTEGER *	MulTabLoc,
		F_REAL *	phi,
		F_REAL *	radius,
		F_REAL *	XGRND,
		F_REAL *	YGRND,
		F_REAL *	ZGRND
	)

Definition at line 1053 of file module-aerodyn.cc.

References AeroDynModule::dGetCurrBladeNodeBuiltinTwist(), AeroDynModule::GetCurrBladeR(), StructNode::GetRCurr(), StructDispNode::GetXCurr(), module_aerodyn, Mat3x3::MulTV(), Vec3::Norm(), AeroDynModule::pGetCurrBladeNode(), AeroDynModule::pGetHubNode(), AeroDynModule::pGetNacelleNode(), R, AeroDynModule::SetCurrBladeNodePITNOW(), Mat3x3::Transpose(), and RotManip::VecRot().

 {
         /*
          * This comment is added by Fanzhong MENG 10th.Feb.2008
          * Get coordinates of blade element relative to the undeflected
          * tower top reference frame. At the Hub height.
          * The variable name is *XGRND *YGRND *ZGRND
          */
         /*
          * Get blade elements coordinates X,Y,Z.
          */ 
         Vec3 x = ::module_aerodyn->pGetCurrBladeNode()->GetXCurr()
                 - ::module_aerodyn->pGetNacelleNode()->GetXCurr();
         // Maybe we have to modified here. Here we need
         // hub height coordinates.
         *XGRND = x(1);
         *YGRND = x(2);
         *ZGRND = x(3);
         /*
          * Get blade elements radius. It is the perpendicular distance 
          * from the rotor axis to the element aerodynamic reference point.
          */ 
         const Vec3& X_node = ::module_aerodyn->pGetCurrBladeNode()->GetXCurr();
         const Vec3& X_hub = ::module_aerodyn->pGetHubNode()->GetXCurr();
         const Mat3x3& R_nacelle = ::module_aerodyn->pGetNacelleNode()->GetRCurr();
         Vec3 d = R_nacelle.MulTV(X_node - X_hub);
         d(3) = 0.;
         *radius = d.Norm();
 
         /*
          * Get the blade elements local pitch angle. Here X-axis is in the blade
          * spanwise direction.
          */ 
         // unsigned blade = ::module_aerodyn->iGetCurrBlade();
         const Mat3x3& R_node = ::module_aerodyn->pGetCurrBladeNode()->GetRCurr(); 
         const Mat3x3& R_hub = ::module_aerodyn->pGetHubNode()->GetRCurr();
         const Mat3x3& R_blade_root = ::module_aerodyn->GetCurrBladeR();
         Mat3x3 R = (R_hub*R_blade_root).MulTM(R_node);
         Vec3 Phi(RotManip::VecRot(R.Transpose()));
 
         // Pitch Now = Pitch + Twist 
         *phi = Phi(1) + ::module_aerodyn->dGetCurrBladeNodeBuiltinTwist();
         ::module_aerodyn->SetCurrBladeNodePITNOW(*phi);
 
         /* 
          * This comment is added by Fanzhong MENG 10th.Feb.2008
          * When the Multi-airfoil table option is open, we should also 
          * switch on this option. By default, this value should be set to ZERO.
          * I don't know how this Multi-airfoil table work,yet.
          */ 
         *MulTabLoc = 0;
 
         return 0;
 }

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int __FC_DECL__() getrotorparams	(	F_REAL *	Omega,
		F_REAL *	gamma,
		F_REAL *	VHUB,
		F_REAL *	tau
	)

Definition at line 949 of file module-aerodyn.cc.

References grad::atan2(), AeroDynModule::dGetHubTowerXYDistance(), elemout(), StructNode::GetRCurr(), Mat3x3::GetVec(), StructNode::GetWCurr(), M_PI, module_aerodyn, AeroDynModule::pGetHubNode(), AeroDynModule::pGetNacelleNode(), AeroDynModule::SetRotorSpeed(), and grad::sqrt().

 {
         /*
          * This comment is added by Fanzhong MENG 10th.Feb.2008
          * NOTE: Add code here to get rotorspeed from MBDyn.  
          * Rotor can be running clockwise or ccw.  But the
          * value of *Omega must be positive [rad/s]
          */
         /*
          * PM 2008-09-06:
          * nacelle & rotor axis is node axis 3, positive opposite
          * to wind direction
          */
 
         const Mat3x3& nacelle_R = ::module_aerodyn->pGetNacelleNode()->GetRCurr();
         const Vec3& hub_Omega = ::module_aerodyn->pGetHubNode()->GetWCurr();
         Vec3 rotation_axis = nacelle_R.GetVec(3);
 
         *Omega = std::abs(hub_Omega*rotation_axis);
         module_aerodyn->SetRotorSpeed(*Omega);
 
         /* 
          * This comment is added by Fanzhong MENG 10th.Feb.2008
          * NOTE: Add code here to get Yawangle from MBDyn.  
          * Yaw angle of the shaft relative to the ground reference.
          * Positive value is clockwise when viewed from above of nacelle.
          * Variable name is *gamma. [rad].
          */
         *gamma = std::atan2(-rotation_axis(2), -rotation_axis(1));
 
         /*
          * This comment is added by Fanzhong MENG 10th.Feb.2008
          * NOTE: Add code here to get tilt angle from MBDyn.
          * Tilt angle of the shaft relative to the ground reference.
          * Positive value is Tilt UP
          * Variable name is *tau. [rad].
          */
         *tau = std::atan2(rotation_axis(3),
                 std::sqrt(rotation_axis(1)*rotation_axis(1) + rotation_axis(2)*rotation_axis(2)));
 
         /*
          * This comment is added by Fanzhong MENG 10th.Feb.2008
          * NOTE: Add code here to get Hub Tangential velocity from MBDyn.
          * Positive value is in the same direction with Yaw Angle.
          * Variable name is *VHUB.[m/s or feet/s]
          */ 
         // *VHUB = hub_Omega(3)*::module_aerodyn->dGetHubTowerXYDistance();
         /* See Emails by Fanzhong Meng August 27, 2010 */
         const Vec3& nacelle_Omega = ::module_aerodyn->pGetNacelleNode()->GetWCurr();
         *VHUB = nacelle_Omega(3)*::module_aerodyn->dGetHubTowerXYDistance();
         
         __FC_DECL__(elemout)();
 
 #ifdef MODULE_AERODYN_DEBUG
         silent_cerr("getrotorparams: "
                 "Omega=" << *Omega << " "
                 "gamma=" << (*gamma)*180/M_PI << " "
                 "tau=" << (*tau)*180/M_PI << " "
                 "VHUB=" << *VHUB << std::endl);
 #endif // MODULE_AERODYN_DEBUG
 
         return 0;
 }

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int __FC_DECL__() getvnvt	(	F_REAL *	VX,
		F_REAL *	VY,
		F_REAL *	VZ,
		F_REAL *	VT,
		F_REAL *	VNW,
		F_REAL *	VNE
	)

Definition at line 1118 of file module-aerodyn.cc.

References grad::cos(), AeroDynModule::dGetCurrBladeNodePITNOW(), AeroDynModule::GetCurrBladeNodeRa(), StructNode::GetRCurr(), StructDispNode::GetVCurr(), module_aerodyn, Mat3x3::MulTV(), AeroDynModule::pGetCurrBladeNode(), and grad::sin().

 {
         /*
          * Fanzhong MENG 18th.Feb.2008.
          * This function returns velocities of the wind
          * and the element in the ground reference frame.
          * VX,VY,VZ are provided by AeroDyn for MBDyn.
          */
         /*
          * This "getvnvt" function is correct now!
          */
         /*
          * velocity of the element related to Ground reference frame.
          */
         const Vec3& ve_G = ::module_aerodyn->pGetCurrBladeNode()->GetVCurr();
 
         /*
          * velocity of the wind related to Ground reference frame.
          * The "-" sign change the wind velocity from Aerodyn reference frame to MBDyn 
          *  Global reference frame. AeroDyn global reference frame can be found on page 35 of Aerodyn user's guide--Figure C1
          */
         Vec3 vw_G = Vec3(-(*VX), -(*VY), *VZ);
 
         /*
          * Transform wind vector from ground coordinate system (vw_G) to
          * blade Node reference frame (vw_El)
          */
         const Mat3x3& R_node = ::module_aerodyn->pGetCurrBladeNode()->GetRCurr();
         /*
          * 10th of June. Modified by fanzhong meng.
          * get orientation matrix of node twist with respect to node without pitch.
          */
         const Mat3x3& R_node_twist = ::module_aerodyn->GetCurrBladeNodeRa(); 
 
         
         Vec3 vw_El = R_node_twist.MulTV( R_node.MulTV(vw_G) );
         Vec3 ve_El = R_node_twist.MulTV( R_node.MulTV(ve_G) );
 
         /*
          * Calculate SIN and COS value of current pitch angle.
          */
 
         doublereal PitchNow = ::module_aerodyn->dGetCurrBladeNodePITNOW(); 
         doublereal CPitchNow = std::cos(PitchNow);
         doublereal SPitchNow = std::sin(PitchNow);
         
         /*
          * Play around with these SIN and COS value to get
          * *VT,*VNW and *VNE.
          */
 
         doublereal vt_wind = -vw_El(2)*CPitchNow - vw_El(3)*SPitchNow;
         doublereal vt_element = ve_El(2)*CPitchNow + ve_El(3)*SPitchNow;
 
         *VT = vt_wind + vt_element;
         *VNW = -vw_El(2)*SPitchNow + vw_El(3)*CPitchNow;
         /* 
          * Element Normal velocity opposites to the Wind Normal velocity. 
          * You can find is on page 35 of Aerodyn user's guide--Figure C2.
          */
         *VNE = -(-ve_El(2)*SPitchNow + ve_El(3)*CPitchNow);
 
         return 0;
 }

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int __FC_DECL__() mbdyn_ad_inputgate	(	F_CHAR *	ifname,
		F_INTEGER *	ifnamelen,
		F_CHAR *	efname,
		F_INTEGER *	efnamelen
	)

Referenced by AeroDynModule::AeroDynModule().

int __FC_DECL__() mbdyn_com_data	(	F_INTEGER *	c_blade,
		F_INTEGER *	c_elem
	)

Referenced by AeroDynModule::AssRes().

int __FC_DECL__() mbdyn_false ( F_LOGICAL * val )

Referenced by AeroDynModule::AssRes().

int __FC_DECL__() mbdyn_get_hl_const	(	F_REAL *	RLOCAL,
		F_INTEGER *	Cur_elem,
		F_REAL *	RHub
	)

Referenced by AeroDynModule::AeroDynModule().

int __FC_DECL__() mbdyn_get_tl_const	(	F_REAL *	RLOCAL,
		F_INTEGER *	Cur_elem
	)

Referenced by AeroDynModule::AeroDynModule().

int __FC_DECL__() mbdyn_init	(	F_CHAR *	Version,
		F_INTEGER *	nblades,
		F_REAL *	rotradius
	)

Referenced by AeroDynModule::AeroDynModule().

int __FC_DECL__() mbdyn_sim_time ( doublereal * c_time )

Referenced by AeroDynModule::AeroDynModule(), and AeroDynModule::AfterPredict().

int __FC_DECL__() mbdyn_time_step ( F_REAL * dt )

Referenced by AeroDynModule::AfterPredict().

int __FC_DECL__() mbdyn_true ( F_LOGICAL * val )

Referenced by AeroDynModule::AeroDynModule().

int __FC_DECL__() usrmes	(	F_LOGICAL *	Logical,
		F_CHAR	msg[],
		F_INTEGER *	code,
		F_CHAR	level[]
	)

Definition at line 1199 of file module-aerodyn.cc.

References msg.

 {
 #if 0
         // can't work, unless we know the size of the arrays!
         silent_cerr("module-aerodyn: msg=\"" << msg << "\" "
                 "code=" << *code
                 << " level=" << level
                 << std::endl);
 #endif
         silent_cerr("module-aerodyn: diagnostics from AeroDyn, "
                 "code=" << *code << std::endl);
 
         return 0;
 }

Typedefs

Functions

Typedef Documentation

Function Documentation