#include <aeroelem.h>

Inheritance diagram for AerodynamicBody:

Collaboration diagram for AerodynamicBody:

Public Member Functions
	AerodynamicBody (unsigned int uLabel, const DofOwner pDO, const StructNode pN, InducedVelocity pR, bool bPassive, const Vec3 &fTmp, doublereal dS, const Mat3x3 &RaTmp, const Shape pC, const Shape pF, const Shape pV, const Shape pT, const Shape pTL, integer iN, AeroData a, const DriveCaller pDC, bool bUseJacobian, OrientationDescription ood, flag fOut)

virtual	~AerodynamicBody (void)

virtual std::ostream &	Restart (std::ostream &out) const

virtual VariableSubMatrixHandler &	AssJac (VariableSubMatrixHandler &WorkMat, doublereal dCoef, const VectorHandler &, const VectorHandler &)

virtual SubVectorHandler &	AssRes (SubVectorHandler &WorkVec, doublereal dCoef, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr)

virtual void	Output (OutputHandler &OH) const

virtual SubVectorHandler &	InitialAssRes (SubVectorHandler &WorkVec, const VectorHandler &XCurr)

virtual AerodynamicElem::Type	GetAerodynamicElemType (void) const

virtual void	GetConnectedNodes (std::vector< const Node * > &connectedNodes) const

Public Member Functions inherited from Elem
	Elem (unsigned int uL, flag fOut)

virtual	~Elem (void)

virtual void	AssMats (VariableSubMatrixHandler &WorkMatA, VariableSubMatrixHandler &WorkMatB, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr)

virtual bool	bInverseDynamics (void) const

void	SetInverseDynamicsFlags (unsigned uIDF)

unsigned	GetInverseDynamicsFlags (void) const

bool	bIsErgonomy (void) const

bool	bIsRightHandSide (void) const

virtual VariableSubMatrixHandler &	AssJac (VariableSubMatrixHandler &WorkMat, const VectorHandler &XCurr)

virtual SubVectorHandler &	AssRes (SubVectorHandler &WorkVec, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr, const VectorHandler &XPrimePrimeCurr, InverseDynamics::Order iOrder=InverseDynamics::INVERSE_DYNAMICS)

virtual int	GetNumConnectedNodes (void) const

Public Member Functions inherited from WithLabel
	WithLabel (unsigned int uL=0, const std::string &sN="")

virtual	~WithLabel (void)

void	PutLabel (unsigned int uL)

void	PutName (const std::string &sN)

unsigned int	GetLabel (void) const

const std::string &	GetName (void) const

Public Member Functions inherited from SimulationEntity
	SimulationEntity (void)

virtual	~SimulationEntity (void)

virtual bool	bIsValidIndex (unsigned int i) const

virtual DofOrder::Order	GetEqType (unsigned int i) const

virtual Hint *	ParseHint (DataManager pDM, const char s) const

virtual void	BeforePredict (VectorHandler &, VectorHandler &, VectorHandler &, VectorHandler &) const

virtual void	AfterPredict (VectorHandler &X, VectorHandler &XP)

virtual void	Update (const VectorHandler &XCurr, const VectorHandler &XPrimeCurr)

virtual void	DerivativesUpdate (const VectorHandler &XCurr, const VectorHandler &XPrimeCurr)

virtual void	Update (const VectorHandler &XCurr, InverseDynamics::Order iOrder)

virtual void	AfterConvergence (const VectorHandler &X, const VectorHandler &XP, const VectorHandler &XPP)

virtual unsigned int	iGetNumPrivData (void) const

virtual unsigned int	iGetPrivDataIdx (const char *s) const

virtual doublereal	dGetPrivData (unsigned int i) const

virtual std::ostream &	OutputAppend (std::ostream &out) const

virtual void	ReadInitialState (MBDynParser &HP)

Public Member Functions inherited from ToBeOutput
	ToBeOutput (flag fOut=fDefaultOut)

virtual	~ToBeOutput (void)

virtual void	Output (OutputHandler &OH, const VectorHandler &X, const VectorHandler &XP) const

virtual flag	fToBeOutput (void) const

virtual bool	bToBeOutput (void) const

Public Member Functions inherited from Aerodynamic2DElem< 1 >
	Aerodynamic2DElem (unsigned int uLabel, const DofOwner pDO, InducedVelocity pR, bool bPassive, const Shape pC, const Shape pF, const Shape pV, const Shape pT, const Shape pTL, integer iN, AeroData a, const DriveCaller *pDC, bool bUseJacobian, OrientationDescription ood, flag fOut)

virtual	~Aerodynamic2DElem (void)

virtual Elem::Type	GetElemType (void) const

virtual unsigned int	iGetNumDof (void) const

virtual std::ostream &	DescribeDof (std::ostream &out, const char *prefix="", bool bInitial=false) const

virtual void	DescribeDof (std::vector< std::string > &desc, bool bInitial=false, int i=-1) const

virtual std::ostream &	DescribeEq (std::ostream &out, const char *prefix="", bool bInitial=false) const

virtual void	DescribeEq (std::vector< std::string > &desc, bool bInitial=false, int i=-1) const

virtual DofOrder::Order	GetDofType (unsigned int) const

virtual void	OutputPrepare (OutputHandler &OH)

virtual void	SetValue (DataManager pDM, VectorHandler &X, VectorHandler &XP, SimulationEntity::Hints h=0)

virtual void	AfterConvergence (const VectorHandler &X, const VectorHandler &XP)

virtual void	WorkSpaceDim (integer piNumRows, integer piNumCols) const

virtual unsigned int	iGetInitialNumDof (void) const

virtual void	InitialWorkSpaceDim (integer piNumRows, integer piNumCols) const

virtual VariableSubMatrixHandler &	InitialAssJac (VariableSubMatrixHandler &WorkMat, const VectorHandler &)

virtual const InducedVelocity *	pGetInducedVelocity (void) const

Public Member Functions inherited from AerodynamicElem
	AerodynamicElem (unsigned int uL, const DofOwner *pDO, flag fOut)

virtual	~AerodynamicElem (void)

virtual bool	NeedsAirProperties (void) const

Public Member Functions inherited from ElemWithDofs
	ElemWithDofs (unsigned int uL, const DofOwner *pDO, flag fOut)

virtual	~ElemWithDofs (void)

Public Member Functions inherited from DofOwnerOwner
	DofOwnerOwner (const DofOwner *pDO)

virtual	~DofOwnerOwner ()

virtual const DofOwner *	pGetDofOwner (void) const

virtual integer	iGetFirstIndex (void) const

virtual void	SetInitialValue (VectorHandler &X)

Public Member Functions inherited from AirPropOwner
	AirPropOwner (void)

virtual	~AirPropOwner (void)

virtual void	PutAirProperties (const AirProperties *pAP)

virtual flag	fGetAirVelocity (Vec3 &Velocity, const Vec3 &X) const

virtual doublereal	dGetAirDensity (const Vec3 &X) const

virtual doublereal	dGetAirPressure (const Vec3 &X) const

virtual doublereal	dGetAirTemperature (const Vec3 &X) const

virtual doublereal	dGetSoundSpeed (const Vec3 &X) const

virtual bool	GetAirProps (const Vec3 &X, doublereal &rho, doublereal &c, doublereal &p, doublereal &T) const

Public Member Functions inherited from InitialAssemblyElem
	InitialAssemblyElem (unsigned int uL, flag fOut)

virtual	~InitialAssemblyElem (void)

Public Member Functions inherited from SubjectToInitialAssembly
	SubjectToInitialAssembly (void)

virtual	~SubjectToInitialAssembly (void)

Public Member Functions inherited from DriveOwner
	DriveOwner (const DriveCaller *pDC=0)

	DriveOwner (const DriveOwner &drive)

virtual	~DriveOwner (void)

void	Set (const DriveCaller *pDC)

DriveCaller *	pGetDriveCaller (void) const

doublereal	dGet (const doublereal &dVar) const

doublereal	dGet (void) const

bool	bIsDifferentiable (void) const

doublereal	dGetP (const doublereal &dVar) const

doublereal	dGetP (void) const

Public Member Functions inherited from AerodynamicOutput
	AerodynamicOutput (flag f, int iNP, OrientationDescription ood)

	~AerodynamicOutput (void)

void	SetOutputFlag (flag f, int iNP)

void	ResetIterator (void)

void	SetData (const Vec3 &v, const doublereal *pd, const Vec3 &X, const Mat3x3 &R, const Vec3 &V, const Vec3 &W, const Vec3 &F, const Vec3 &M)

AerodynamicOutput::eOutput	GetOutput (void) const

bool	IsOutput (void) const

bool	IsSTD (void) const

bool	IsPGAUSS (void) const

bool	IsNODE (void) const

Protected Member Functions
void	AssVec (SubVectorHandler &WorkVec, doublereal dCoef, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr)

Protected Member Functions inherited from Aerodynamic2DElem< 1 >
virtual void	SetOutputFlag (flag f=flag(1))

void	Output_int (OutputHandler &OH) const

void	AddForce_int (const StructNode *pN, const Vec3 &F, const Vec3 &M, const Vec3 &X) const

void	AddSectionalForce_int (unsigned uPnt, const Vec3 &F, const Vec3 &M, doublereal dW, const Vec3 &X, const Mat3x3 &R, const Vec3 &V, const Vec3 &W) const

Protected Attributes
const StructNode *	pNode

const Vec3	f

doublereal	dHalfSpan

const Mat3x3	Ra

const Vec3	Ra3

Vec3	F

Vec3	M

Protected Attributes inherited from WithLabel
unsigned int	uLabel

std::string	sName

Protected Attributes inherited from ToBeOutput
flag	fOutput

Protected Attributes inherited from Aerodynamic2DElem< 1 >
AeroData *	aerodata

InducedVelocity *	pIndVel

bool	bPassiveInducedVelocity

const ShapeOwner	Chord

const ShapeOwner	ForcePoint

const ShapeOwner	VelocityPoint

const ShapeOwner	Twist

const ShapeOwner	TipLoss

GaussDataIterator	GDI

std::vector< outa_t >	OUTA

Mat3xN	vx

Mat3xN	wx

Mat3xN	fq

Mat3xN	cq

bool	bJacobian

Protected Attributes inherited from AirPropOwner
const AirProperties *	pAirProperties

Protected Attributes inherited from DriveOwner
DriveCaller *	pDriveCaller

Protected Attributes inherited from AerodynamicOutput
flag	m_eOutput

OrientationDescription	od

std::vector< Aero_output >	OutputData

std::vector< Aero_output > ::iterator	OutputIter

Additional Inherited Members
Public Types inherited from Elem
enum	Type { UNKNOWN = -1, AIRPROPERTIES = 0, INDUCEDVELOCITY, AUTOMATICSTRUCTURAL, GRAVITY, BODY, JOINT, JOINT_REGULARIZATION, BEAM, PLATE, FORCE, INERTIA, ELECTRICBULK, ELECTRIC, THERMAL, HYDRAULIC, BULK, LOADABLE, DRIVEN, EXTERNAL, AEROMODAL, AERODYNAMIC, GENEL, SOCKETSTREAM_OUTPUT, RTAI_OUTPUT = SOCKETSTREAM_OUTPUT, LASTELEMTYPE }

Public Types inherited from SimulationEntity
typedef std::vector< Hint * >	Hints

Public Types inherited from ToBeOutput
enum	{ OUTPUT = 0x1U, OUTPUT_MASK = 0xFU, OUTPUT_PRIVATE = 0x10U, OUTPUT_PRIVATE_MASK = ~OUTPUT_MASK }

Public Types inherited from AerodynamicElem
enum	Type { UNKNOWN = -1, INDUCEDVELOCITY = 0, AEROMODAL, AERODYNAMICBODY, AERODYNAMICBEAM, AERODYNAMICEXTERNAL, AERODYNAMICEXTERNALMODAL, AERODYNAMICLOADABLE, AIRCRAFTINSTRUMENTS, GENERICFORCE, LASTAEROTYPE }

Public Types inherited from AerodynamicOutput
enum	eOutput { AEROD_OUT_NONE = 0x0U, AEROD_OUT_STD = (ToBeOutput::OUTPUT_PRIVATE << 0), AEROD_OUT_PGAUSS = (ToBeOutput::OUTPUT_PRIVATE << 1), AEROD_OUT_NODE = (ToBeOutput::OUTPUT_PRIVATE << 2), AEROD_OUT_MASK = (AEROD_OUT_STD \| AEROD_OUT_PGAUSS \| AEROD_OUT_NODE) }

enum	{ OUTPUT_NONE = 0x0U, OUTPUT_GP_X = (ToBeOutput::OUTPUT_PRIVATE << 4), OUTPUT_GP_R = (ToBeOutput::OUTPUT_PRIVATE << 5), OUTPUT_GP_V = (ToBeOutput::OUTPUT_PRIVATE << 6), OUTPUT_GP_W = (ToBeOutput::OUTPUT_PRIVATE << 7), OUTPUT_GP_CONFIGURATION = (OUTPUT_GP_X \| OUTPUT_GP_R \| OUTPUT_GP_V \| OUTPUT_GP_W), OUTPUT_GP_F = (ToBeOutput::OUTPUT_PRIVATE << 8), OUTPUT_GP_M = (ToBeOutput::OUTPUT_PRIVATE << 9), OUTPUT_GP_FORCES = (OUTPUT_GP_F \| OUTPUT_GP_M), OUTPUT_DEFAULT = (OUTPUT_GP_F \| OUTPUT_GP_M), OUTPUT_GP_ALL = (ToBeOutput::OUTPUT_PRIVATE_MASK & (~AEROD_OUT_MASK)) }

Detailed Description

Definition at line 253 of file aeroelem.h.

Constructor & Destructor Documentation

AerodynamicBody::AerodynamicBody	(	unsigned int	uLabel,
		const DofOwner *	pDO,
		const StructNode *	pN,
		InducedVelocity *	pR,
		bool	bPassive,
		const Vec3 &	fTmp,
		doublereal	dS,
		const Mat3x3 &	RaTmp,
		const Shape *	pC,
		const Shape *	pF,
		const Shape *	pV,
		const Shape *	pT,
		const Shape *	pTL,
		integer	iN,
		AeroData *	a,
		const DriveCaller *	pDC,
		bool	bUseJacobian,
		OrientationDescription	ood,
		flag	fOut
	)

Definition at line 660 of file aeroelem.cc.

References ASSERT, DEBUGCOUTFNAME, StructDispNode::GetNodeType(), pNode, and Node::STRUCTURAL.

 : Elem(uLabel, fOut),
 Aerodynamic2DElem<1>(uLabel, pDO, pR, bPassive, pC, pF, pV, pT, pTL, iN,
         a, pDC, bUseJacobian, ood, fOut),
 pNode(pN),
 f(fTmp),
 dHalfSpan(dS/2.),
 Ra(RaTmp),
 Ra3(RaTmp.GetVec(3)),
 F(Zero3),
 M(Zero3)
 {
         DEBUGCOUTFNAME("AerodynamicBody::AerodynamicBody");
 
         ASSERT(pNode != 0);
         ASSERT(pNode->GetNodeType() == Node::STRUCTURAL);
 
 }

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AerodynamicBody::~AerodynamicBody ( void )

virtual

Definition at line 691 of file aeroelem.cc.

References DEBUGCOUTFNAME.

 {
         DEBUGCOUTFNAME("AerodynamicBody::~AerodynamicBody");
 }

Member Function Documentation

VariableSubMatrixHandler & AerodynamicBody::AssJac	(	VariableSubMatrixHandler &	WorkMat,
		doublereal	dCoef,
		const VectorHandler &	XCurr,
		const VectorHandler &	XPrimeCurr
	)

virtual

Implements Elem.

Definition at line 723 of file aeroelem.cc.

 {
         DEBUGCOUT("Entering AerodynamicBody::AssJac()" << std::endl);
 
         if (!bJacobian) {
                 WorkMat.SetNullMatrix();
                 return WorkMat;
         }
 
         FullSubMatrixHandler& WM = WorkMat.SetFull();
 
         /* Ridimensiona la sottomatrice in base alle esigenze */
         integer iNumRows = 0;
         integer iNumCols = 0;
         WorkSpaceDim(&iNumRows, &iNumCols);
         WM.ResizeReset(iNumRows, iNumCols);
 
         /* Recupera gli indici delle varie incognite */
         integer iNodeFirstMomIndex = pNode->iGetFirstMomentumIndex();
         integer iNodeFirstPosIndex = pNode->iGetFirstPositionIndex();
 
         /* Setta gli indici delle equazioni */
         for (int iCnt = 1; iCnt <= 6; iCnt++) {
                 WM.PutRowIndex(iCnt, iNodeFirstMomIndex + iCnt);
                 WM.PutColIndex(iCnt, iNodeFirstPosIndex + iCnt);
         }
 
         /* Equations start here... */
         doublereal dW[6];
 
         /* Dati del nodo */
         const Vec3& Xn(pNode->GetXCurr());
         const Mat3x3& Rn(pNode->GetRCurr());
         const Vec3& Vn(pNode->GetVCurr());
         const Vec3& Wn(pNode->GetWCurr());
 
         /*
          * Matrice di trasformazione dal sistema globale a quello aerodinamico
          */
         Mat3x3 RR(Rn*Ra);
 
         /*
          * Se l'elemento e' collegato ad un rotore,
          * si fa dare la velocita' di rotazione
          */
         doublereal dOmega = 0.;
         if (pIndVel != 0) {
                 Rotor *pRotor = dynamic_cast<Rotor *>(pIndVel);
                 if (pRotor) {
                         dOmega = pRotor->dGetOmega();
                 }
         }
 
         /*
          * Dati "permanenti" (uso la posizione del nodo perche'
          * non dovrebbero cambiare "molto")
          */
         doublereal rho, c, p, T;
         GetAirProps(Xn, rho, c, p, T);  /* p, T no used yet */
         aerodata->SetAirData(rho, c);
 
         ResetIterator();
 
         integer iNumDof = aerodata->iGetNumDof();
         integer iFirstEq = -1;
         integer iFirstSubEq = -1;
         if (iNumDof > 0) {
                 iFirstEq = iGetFirstIndex();
                 iFirstSubEq = 6;
 
                 integer iOffset = iFirstEq - 6;
 
                 for (int iCnt = 6 + 1; iCnt <= iNumRows; iCnt++) {
                         WM.PutRowIndex(iCnt, iOffset + iCnt);
                         WM.PutColIndex(iCnt, iOffset + iCnt);
                 }
         }
 
         /* Ciclo sui punti di Gauss */
         PntWght PW = GDI.GetFirst();
         int iPnt = 0;
         do {
                 doublereal dCsi = PW.dGetPnt();
                 Vec3 Xr(Rn*(f + Ra3*(dHalfSpan*dCsi)));
                 Vec3 Xnr = Xn + Xr;
                 Vec3 Vr(Vn + Wn.Cross(Xr));
 
                 /* Contributo di velocita' del vento */
                 Vec3 VTmp(Zero3);
                 if (fGetAirVelocity(VTmp, Xnr)) {
                         Vr -= VTmp;
                 }
 
                 /*
                  * Se l'elemento e' collegato ad un rotore,
                  * aggiunge alla velocita' la velocita' indotta
                  */
                 if (pIndVel != 0) {
                         Vr += pIndVel->GetInducedVelocity(GetElemType(),
                                 GetLabel(), iPnt, Xnr);
                 }
 
                 /* Copia i dati nel vettore di lavoro dVAM */
                 doublereal dTw = Twist.dGet(dCsi) + dGet();
                 aerodata->SetSectionData(dCsi,
                         Chord.dGet(dCsi),
                         ForcePoint.dGet(dCsi),
                         VelocityPoint.dGet(dCsi),
                         dTw,
                         dOmega);
 
                 /*
                  * Lo svergolamento non viene piu' trattato in aerod2_; quindi
                  * lo uso per correggere la matrice di rotazione
                  * dal sistema aerodinamico a quello globale
                  */
                 Mat3x3 RRloc;
                 if (dTw != 0.) {
                         doublereal dCosT = cos(dTw);
                         doublereal dSinT = sin(dTw);
                         /* Assumo lo svergolamento positivo a cabrare */
                         Mat3x3 RTw( dCosT, dSinT, 0.,
                                 -dSinT, dCosT, 0.,
                                 0.,    0.,    1.);
                         RRloc = RR*RTw;
 
                 } else {
                         RRloc = RR;
                 }
 
                 /*
                  * Ruota velocita' e velocita' angolare nel sistema
                  * aerodinamico e li copia nel vettore di lavoro dW
                  */
                 VTmp = RRloc.MulTV(Vr);
                 VTmp.PutTo(dW);
 
                 Vec3 WTmp = RRloc.MulTV(Wn);
                 WTmp.PutTo(&dW[3]);
 
                 /* Funzione di calcolo delle forze aerodinamiche */
                 doublereal Fa0[6];
                 Mat6x6 JFa;
 
                 /* Jacobian Assembly... */
                 doublereal cc = dHalfSpan*PW.dGetWght();
 
                 if (iNumDof) {
                         // prepare (v/dot{x} + dCoef*v/x) and so
                         Mat3x3 RRlocT(RRloc.Transpose());
 
                         vx.PutMat3x3(1, RRlocT);
                         vx.PutMat3x3(4, RRloc.MulTM(Mat3x3(MatCross, (Vr + Xr.Cross(Wn))*dCoef - Xr)));
                         wx.PutMat3x3(4, RRlocT);
 
                         // equations from iFirstEq on are dealt with by aerodata
                         aerodata->AssJac(WM, dCoef, XCurr, XPrimeCurr,
                                 iFirstEq, iFirstSubEq,
                                 vx, wx, fq, cq, iPnt, dW, Fa0, JFa, OUTA[iPnt]);
 
                         // deal with (f/dot{q} + dCoef*f/q) and so
                         integer iOffset = 6 + iPnt*iNumDof;
                         for (integer iCol = 1; iCol <= iNumDof; iCol++) {
                                 Vec3 fqTmp((RRloc*fq.GetVec(iCol))*cc);
                                 Vec3 cqTmp(Xr.Cross(fqTmp) + (RRloc*cq.GetVec(iCol))*cc);
 
                                 WM.Sub(1, iOffset + iCol, fqTmp);
                                 WM.Sub(4, iOffset + iCol, cqTmp);
                         }
 
                         // first equation
                         iFirstEq += iNumDof;
                         iFirstSubEq += iNumDof;
 
                 } else {
                         aerodata->GetForcesJac(iPnt, dW, Fa0, JFa, OUTA[iPnt]);
                 }
 
                 // rotate force, couple and Jacobian matrix in absolute frame
                 Mat6x6 JFaR = MultRMRt(JFa, RRloc, cc);
 
                 Vec3 fTmp(RRloc*(Vec3(&Fa0[0])*dCoef));
                 Vec3 cTmp(RRloc*(Vec3(&Fa0[3])*dCoef) + Xr.Cross(fTmp));
 
                 // compute submatrices (see tecman.pdf)
                 Mat3x3 Mat21(Xr.Cross(JFaR.GetMat11()) + JFaR.GetMat21());
 
                 Mat3x3 Mat12(JFaR.GetMat12() - JFaR.GetMat11()*Mat3x3(MatCross, Xr));
 
                 Mat3x3 Mat22(Xr.Cross(JFaR.GetMat12()) + JFaR.GetMat22() - Mat21*Mat3x3(MatCross, Xr));
 
                 Mat3x3 MatV(MatCross, (Vr + Xr.Cross(Wn))*dCoef);
 
                 Mat12 += JFaR.GetMat11()*MatV - Mat3x3(MatCross, fTmp);
 
                 Mat22 += Mat21*MatV - Mat3x3(MatCross, cTmp);
 
                 // add (actually, sub) contributions, scaled by weight
                 WM.Sub(1, 1, JFaR.GetMat11());
                 WM.Sub(1, 4, Mat12);
                 WM.Sub(4, 1, Mat21);
                 WM.Sub(4, 4, Mat22);
 
                 iPnt++;
 
         } while (GDI.fGetNext(PW));
 
         return WorkMat;
 }

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SubVectorHandler & AerodynamicBody::AssRes	(	SubVectorHandler &	WorkVec,
		doublereal	dCoef,
		const VectorHandler &	XCurr,
		const VectorHandler &	XPrimeCurr
	)

virtual

Implements Elem.

Definition at line 938 of file aeroelem.cc.

References AssVec(), DEBUGCOUTFNAME, StructDispNode::iGetFirstMomentumIndex(), pNode, SubVectorHandler::PutRowIndex(), VectorHandler::ResizeReset(), and Elem::WorkSpaceDim().

 {
         DEBUGCOUTFNAME("AerodynamicBody::AssRes");
 
         integer iNumRows;
         integer iNumCols;
         WorkSpaceDim(&iNumRows, &iNumCols);
         WorkVec.ResizeReset(iNumRows);
 
         integer iFirstIndex = pNode->iGetFirstMomentumIndex();
         for (int iCnt = 1; iCnt <= 6; iCnt++) {
                 WorkVec.PutRowIndex(iCnt, iFirstIndex + iCnt);
         }
 
         AssVec(WorkVec, dCoef, XCurr, XPrimeCurr);
 
         return WorkVec;
 }

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void AerodynamicBody::AssVec	(	SubVectorHandler &	WorkVec,
		doublereal	dCoef,
		const VectorHandler &	XCurr,
		const VectorHandler &	XPrimeCurr
	)

protected

Definition at line 990 of file aeroelem.cc.

Referenced by AssRes(), and InitialAssRes().

 {
         DEBUGCOUTFNAME("AerodynamicBody::AssVec");
 
         doublereal dTng[6];
         doublereal dW[6];
 
         /* Dati del nodo */
         const Vec3& Xn(pNode->GetXCurr());
         const Mat3x3& Rn(pNode->GetRCurr());
         const Vec3& Vn(pNode->GetVCurr());
         const Vec3& Wn(pNode->GetWCurr());
 
         /*
          * Matrice di trasformazione dal sistema globale a quello aerodinamico
          */
         Mat3x3 RR(Rn*Ra);
 
         /*
          * Se l'elemento e' collegato ad un rotore,
          * si fa dare la velocita' di rotazione
          */
         doublereal dOmega = 0.;
         if (pIndVel != 0) {
                 Rotor *pRotor = dynamic_cast<Rotor *>(pIndVel);
                 if (pRotor) {
                         dOmega = pRotor->dGetOmega();
                 }
         }
 
         /* Resetta i dati */
         F.Reset();
         M.Reset();
 
         /*
          * Dati "permanenti" (uso la posizione del nodo perche'
          * non dovrebbero cambiare "molto")
          */
         doublereal rho, c, p, T;
         GetAirProps(Xn, rho, c, p, T);  /* p, T no used yet */
         aerodata->SetAirData(rho, c);
 
         ResetIterator();
 
         integer iNumDof = aerodata->iGetNumDof();
         integer iFirstEq = -1;
         integer iFirstSubEq = -1;
         if (iNumDof > 0) {
                 iFirstEq = iGetFirstIndex();
                 iFirstSubEq = 6;
 
                 integer iOffset = iFirstEq - 6;
                 integer iNumRows = WorkVec.iGetSize();
                 for (int iCnt = 6 + 1; iCnt <= iNumRows; iCnt++) {
                         WorkVec.PutRowIndex(iCnt, iOffset + iCnt);
                 }
         }
 
         /* Ciclo sui punti di Gauss */
         PntWght PW = GDI.GetFirst();
         int iPnt = 0;
         do {
                 doublereal dCsi = PW.dGetPnt();
                 Vec3 Xr(Rn*(f + Ra3*(dHalfSpan*dCsi)));
                 Vec3 Xnr = Xn + Xr;
                 Vec3 Vr(Vn + Wn.Cross(Xr));
 
                 /* Contributo di velocita' del vento */
                 Vec3 VTmp(Zero3);
                 if (fGetAirVelocity(VTmp, Xnr)) {
                         Vr -= VTmp;
                 }
 
                 /*
                  * Se l'elemento e' collegato ad un rotore,
                  * aggiunge alla velocita' la velocita' indotta
                  */
                 if (pIndVel != 0) {
                         Vr += pIndVel->GetInducedVelocity(GetElemType(),
                                 GetLabel(), iPnt, Xnr);
                 }
 
                 /* Copia i dati nel vettore di lavoro dVAM */
                 doublereal dTw = Twist.dGet(dCsi) + dGet();
                 aerodata->SetSectionData(dCsi,
                         Chord.dGet(dCsi),
                         ForcePoint.dGet(dCsi),
                         VelocityPoint.dGet(dCsi),
                         dTw,
                         dOmega);
 
                 /*
                  * Lo svergolamento non viene piu' trattato in aerod2_; quindi
                  * lo uso per correggere la matrice di rotazione
                  * dal sistema aerodinamico a quello globale
                  */
                 Mat3x3 RRloc;
                 if (dTw != 0.) {
                         doublereal dCosT = cos(dTw);
                         doublereal dSinT = sin(dTw);
                         /* Assumo lo svergolamento positivo a cabrare */
                         Mat3x3 RTw( dCosT, dSinT, 0.,
                                    -dSinT, dCosT, 0.,
                                     0.,    0.,    1.);
                         RRloc = RR*RTw;
 
                 } else {
                         RRloc = RR;
                 }
 
                 /*
                  * Ruota velocita' e velocita' angolare nel sistema
                  * aerodinamico e li copia nel vettore di lavoro dW
                  */
                 VTmp = RRloc.MulTV(Vr);
                 VTmp.PutTo(dW);
 
                 Vec3 WTmp = RRloc.MulTV(Wn);
                 WTmp.PutTo(&dW[3]);
 
                 /* Funzione di calcolo delle forze aerodinamiche */
                 if (iNumDof) {
                         aerodata->AssRes(WorkVec, dCoef, XCurr, XPrimeCurr,
                                 iFirstEq, iFirstSubEq, iPnt, dW, dTng, OUTA[iPnt]);
 
                         // first equation
                         iFirstEq += iNumDof;
                         iFirstSubEq += iNumDof;
 
                 } else {
                         aerodata->GetForces(iPnt, dW, dTng, OUTA[iPnt]);
                 }
 
                 /* Dimensionalizza le forze */
                 doublereal dWght = dHalfSpan*PW.dGetWght();
                 dTng[1] *= TipLoss.dGet(dCsi);
                 Vec3 FTmp(RRloc*(Vec3(&dTng[0])));
                 Vec3 MTmp(RRloc*(Vec3(&dTng[3])));
 
                 // Se e' definito il rotore, aggiungere il contributo alla trazione
                 AddSectionalForce_int(iPnt, FTmp, MTmp, dWght, Xnr, RRloc, Vr, Wn);
 
                 FTmp *= dWght;
                 MTmp *= dWght;
 
                 F += FTmp;
                 M += MTmp;
                 M += Xr.Cross(FTmp);
 
                 // specific for Gauss points force output
                 if (bToBeOutput()) {
                         SetData(VTmp, dTng, Xr, RRloc, Vr, Wn, FTmp, MTmp);
                 }
 
                 iPnt++;
 
         } while (GDI.fGetNext(PW));
 
         // Se e' definito il rotore, aggiungere il contributo alla trazione
         AddForce_int(pNode, F, M, Xn);
 
         /* Sommare il termine al residuo */
         WorkVec.Add(1, F);
         WorkVec.Add(4, M);
 }

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virtual AerodynamicElem::Type AerodynamicBody::GetAerodynamicElemType ( void ) const

inlinevirtual

Implements AerodynamicElem.

Definition at line 319 of file aeroelem.h.

References AerodynamicElem::AERODYNAMICBODY.

                                                                        {
                 return AerodynamicElem::AERODYNAMICBODY;
         };

virtual void AerodynamicBody::GetConnectedNodes ( std::vector< const Node * > & connectedNodes ) const

inlinevirtual

Reimplemented from Elem.

Definition at line 329 of file aeroelem.h.

                                                                          {
                 connectedNodes.resize(1);
                 connectedNodes[0] = pNode;
         };

SubVectorHandler & AerodynamicBody::InitialAssRes	(	SubVectorHandler &	WorkVec,
		const VectorHandler &	XCurr
	)

virtual

Implements SubjectToInitialAssembly.

Definition at line 962 of file aeroelem.cc.

References Aerodynamic2DElem< 1 >::aerodata, AssVec(), DEBUGCOUTFNAME, StructDispNode::iGetFirstPositionIndex(), AeroData::iGetNumDof(), pNode, SubVectorHandler::PutRowIndex(), VectorHandler::ResizeReset(), and Elem::WorkSpaceDim().

 {
         DEBUGCOUTFNAME("AerodynamicBody::InitialAssRes");
 
         if (aerodata->iGetNumDof() > 0) {
                 WorkVec.ResizeReset(0);
                 return WorkVec;
         }
 
         integer iNumRows;
         integer iNumCols;
         WorkSpaceDim(&iNumRows, &iNumCols);
         WorkVec.ResizeReset(iNumRows);
 
         integer iFirstIndex = pNode->iGetFirstPositionIndex();
         for (int iCnt = 1; iCnt <= 6; iCnt++) {
                 WorkVec.PutRowIndex(iCnt, iFirstIndex + iCnt);
         }
 
         AssVec(WorkVec, 1., XCurr, XCurr);
 
         return WorkVec;
 }

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void AerodynamicBody::Output ( OutputHandler & OH ) const

virtual

Reimplemented from ToBeOutput.

Definition at line 1164 of file aeroelem.cc.

References AerodynamicOutput::AEROD_OUT_NODE, AerodynamicOutput::AEROD_OUT_PGAUSS, AerodynamicOutput::AEROD_OUT_STD, OutputHandler::AERODYNAMIC, OutputHandler::Aerodynamic(), ASSERT, ToBeOutput::bToBeOutput(), F, Aerodynamic2DElem< 1 >::GDI, WithLabel::GetLabel(), AerodynamicOutput::GetOutput(), NumIntData::iGetNum(), M, Aerodynamic2DElem< 1 >::OUTA, Aerodynamic2DElem< iNN >::Output_int(), AerodynamicOutput::OutputData, pNode, OutputHandler::UseText(), and Vec3::Write().

 {
         /* Output delle forze aerodinamiche F, M su apposito file */
         if (bToBeOutput()) {
                 Aerodynamic2DElem<1>::Output_int(OH);
 
                 if (OH.UseText(OutputHandler::AERODYNAMIC)) {
                         std::ostream& out = OH.Aerodynamic()
                                 << std::setw(8) << GetLabel();
 
                         switch (GetOutput()) {
                         case AEROD_OUT_NODE:
                                 out << " " << std::setw(8) << pNode->GetLabel()
                                         << " ", F.Write(out, " ") << " ", M.Write(out, " ");
                                 break;
 
                         case AEROD_OUT_PGAUSS:
                                 ASSERT(!OutputData.empty());
                                 for (std::vector<Aero_output>::const_iterator i = OutputData.begin();
                                         i != OutputData.end(); ++i)
                                 {
                                         out << " " << i->alpha
                                                 << " " << i->f;
                                 }
                                 break;
 
                         case AEROD_OUT_STD:
                                 for (int i = 0; i < GDI.iGetNum(); i++) {
                                         out
                                                 << " " << OUTA[i].alpha
                                                 << " " << OUTA[i].gamma
                                                 << " " << OUTA[i].mach
                                                 << " " << OUTA[i].cl
                                                 << " " << OUTA[i].cd
                                                 << " " << OUTA[i].cm
                                                 << " " << OUTA[i].alf1
                                                 << " " << OUTA[i].alf2;
                                 }
                                 break;
 
                         default:
                                 ASSERT(0);
                                 break;
                         }
 
                         out << std::endl;
         }       }
 }

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std::ostream & AerodynamicBody::Restart ( std::ostream & out ) const

virtual

Implements Elem.

Definition at line 698 of file aeroelem.cc.

References Aerodynamic2DElem< 1 >::aerodata, Aerodynamic2DElem< 1 >::Chord, DEBUGCOUTFNAME, dHalfSpan, f, Aerodynamic2DElem< 1 >::ForcePoint, Aerodynamic2DElem< 1 >::GDI, WithLabel::GetLabel(), Mat3x3::GetVec(), NumIntData::iGetNum(), DriveOwner::pGetDriveCaller(), ShapeOwner::pGetShape(), Aerodynamic2DElem< 1 >::pIndVel, pNode, Ra, Shape::Restart(), AeroData::Restart(), DriveCaller::Restart(), Aerodynamic2DElem< 1 >::Twist, Aerodynamic2DElem< 1 >::VelocityPoint, Write(), and Vec3::Write().

 {
         DEBUGCOUTFNAME("AerodynamicBody::Restart");
 
         out << "  aerodynamic body: " << GetLabel() << ", "
                 << pNode->GetLabel();
         if (pIndVel != 0) {
                 out << ", rotor, " << pIndVel->GetLabel();
         }
         out << ", reference, node, ", f.Write(out, ", ")
                 << ", " << dHalfSpan*2.
                 << ", reference, node, 1, ", (Ra.GetVec(1)).Write(out, ", ")
                 << ", 2, ", (Ra.GetVec(2)).Write(out, ", ")
                 << ", ";
         Chord.pGetShape()->Restart(out) << ", ";
         ForcePoint.pGetShape()->Restart(out) << ", ";
         VelocityPoint.pGetShape()->Restart(out) << ", ";
         Twist.pGetShape()->Restart(out) << ", "
                 << ", " << GDI.iGetNum() << ", control, ";
         pGetDriveCaller()->Restart(out) << ", ";
         aerodata->Restart(out);
         return out << ";" << std::endl;
 }

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Member Data Documentation

doublereal AerodynamicBody::dHalfSpan

protected

Definition at line 261 of file aeroelem.h.

Referenced by AssJac(), AssVec(), and Restart().

const Vec3 AerodynamicBody::f

protected

Definition at line 260 of file aeroelem.h.

Referenced by AssJac(), AssVec(), and Restart().

Vec3 AerodynamicBody::F

protected

Definition at line 265 of file aeroelem.h.

Referenced by AssVec(), and Output().

Vec3 AerodynamicBody::M

protected

Definition at line 266 of file aeroelem.h.

Referenced by AssVec(), and Output().

const StructNode* AerodynamicBody::pNode

protected

Definition at line 258 of file aeroelem.h.

Referenced by AerodynamicBody(), AssJac(), AssRes(), AssVec(), InitialAssRes(), Output(), and Restart().

const Mat3x3 AerodynamicBody::Ra

protected

Definition at line 262 of file aeroelem.h.

Referenced by AssJac(), AssVec(), and Restart().

const Vec3 AerodynamicBody::Ra3

protected

Definition at line 263 of file aeroelem.h.

Referenced by AssJac(), and AssVec().

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

Public Member Functions

Protected Member Functions

Protected Attributes

Additional Inherited Members

Detailed Description

Constructor & Destructor Documentation

Member Function Documentation

Member Data Documentation