MBDyn-1.7.3
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AerodynamicBeam Class Reference

#include <aeroelem.h>

Inheritance diagram for AerodynamicBeam:
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Collaboration diagram for AerodynamicBeam:
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Public Member Functions

 AerodynamicBeam (unsigned int uLabel, const DofOwner *pDO, const Beam *pB, InducedVelocity *pR, bool bPassive, const Vec3 &fTmp1, const Vec3 &fTmp2, const Vec3 &fTmp3, const Mat3x3 &Ra1Tmp, const Mat3x3 &Ra2Tmp, const Mat3x3 &Ra3Tmp, 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 ~AerodynamicBeam (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 SubVectorHandler & InitialAssRes (SubVectorHandler &WorkVec, const VectorHandler &XCurr)
 
virtual void Output (OutputHandler &OH) const
 
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< 3 >
 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 Types

enum  { NODE1 = 0, NODE2, NODE3, LASTNODE }
 
enum  {
  DELTAx1 = 0, DELTAg1, DELTAx2, DELTAg2,
  DELTAx3, DELTAg3
}
 

Protected Member Functions

void AssVec (SubVectorHandler &WorkVec, doublereal dCoef, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr)
 
- Protected Member Functions inherited from Aerodynamic2DElem< 3 >
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 Beam * pBeam
 
const StructNode * pNode [3]
 
const Vec3 f1
 
const Vec3 f2
 
const Vec3 f3
 
const Mat3x3 Ra1
 
const Mat3x3 Ra2
 
const Mat3x3 Ra3
 
const Vec3 Ra1_3
 
const Vec3 Ra2_3
 
const Vec3 Ra3_3
 
Vec3 F [LASTNODE]
 
Vec3 M [LASTNODE]
 
- Protected Attributes inherited from WithLabel
unsigned int uLabel
 
std::string sName
 
- Protected Attributes inherited from ToBeOutput
flag fOutput
 
- Protected Attributes inherited from Aerodynamic2DElem< 3 >
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 341 of file aeroelem.h.

Member Enumeration Documentation

anonymous enum
protected
Enumerator
NODE1 
NODE2 
NODE3 
LASTNODE 

Definition at line 346 of file aeroelem.h.

346 { NODE1 = 0, NODE2, NODE3, LASTNODE };
anonymous enum
protected
Enumerator
DELTAx1 
DELTAg1 
DELTAx2 
DELTAg2 
DELTAx3 
DELTAg3 

Definition at line 347 of file aeroelem.h.

347 { DELTAx1 = 0, DELTAg1, DELTAx2, DELTAg2, DELTAx3, DELTAg3 };

Constructor & Destructor Documentation

AerodynamicBeam::AerodynamicBeam ( unsigned int  uLabel,
const DofOwner *  pDO,
const Beam *  pB,
InducedVelocity *  pR,
bool  bPassive,
const Vec3 &  fTmp1,
const Vec3 &  fTmp2,
const Vec3 &  fTmp3,
const Mat3x3 &  Ra1Tmp,
const Mat3x3 &  Ra2Tmp,
const Mat3x3 &  Ra3Tmp,
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 1477 of file aeroelem.cc.

References ASSERT, Elem::BEAM, DEBUGCOUTFNAME, Beam::GetElemType(), pBeam, Beam::pGetNode(), pNode, and Node::STRUCTURAL.

1494 : Elem(uLabel, fOut),
1495 Aerodynamic2DElem<3>(uLabel, pDO, pR, bPassive,
1496  pC, pF, pV, pT, pTL, iN, a, pDC, bUseJacobian, ood, fOut),
1497 pBeam(pB),
1498 f1(fTmp1),
1499 f2(fTmp2),
1500 f3(fTmp3),
1501 Ra1(Ra1Tmp),
1502 Ra2(Ra2Tmp),
1503 Ra3(Ra3Tmp),
1504 Ra1_3(Ra1Tmp.GetVec(3)),
1505 Ra2_3(Ra2Tmp.GetVec(3)),
1506 Ra3_3(Ra3Tmp.GetVec(3))
1507 {
1508  DEBUGCOUTFNAME("AerodynamicBeam::AerodynamicBeam");
1509 
1510  ASSERT(pBeam != 0);
1511  ASSERT(pBeam->GetElemType() == Elem::BEAM);
1512 
1513  for (int iNode = 0; iNode < 3; iNode++) {
1514  pNode[iNode] = pBeam->pGetNode(iNode + 1);
1515 
1516  ASSERT(pNode[iNode] != 0);
1517  ASSERT(pNode[iNode]->GetNodeType() == Node::STRUCTURAL);
1518  }
1519 }
Beam::GetElemType
virtual Elem::Type GetElemType(void) const
Definition: beam.h:297
AerodynamicBeam::Ra1
const Mat3x3 Ra1
Definition: aeroelem.h:355
DEBUGCOUTFNAME
#define DEBUGCOUTFNAME(fname)
Definition: myassert.h:256
AerodynamicBeam::Ra3_3
const Vec3 Ra3_3
Definition: aeroelem.h:360
AerodynamicBeam::Ra2
const Mat3x3 Ra2
Definition: aeroelem.h:356
AerodynamicBeam::pBeam
const Beam * pBeam
Definition: aeroelem.h:349
Mat3x3::GetVec
Vec3 GetVec(unsigned short int i) const
Definition: matvec3.h:893
Beam::pGetNode
virtual const StructNode * pGetNode(unsigned int i) const
Definition: beam.cc:1290
AerodynamicBeam::pNode
const StructNode * pNode[3]
Definition: aeroelem.h:350
WithLabel::uLabel
unsigned int uLabel
Definition: withlab.h:44
ASSERT
#define ASSERT(expression)
Definition: colamd.c:977
AerodynamicBeam::f2
const Vec3 f2
Definition: aeroelem.h:353
AerodynamicBeam::f1
const Vec3 f1
Definition: aeroelem.h:352
AerodynamicBeam::Ra1_3
const Vec3 Ra1_3
Definition: aeroelem.h:358
AerodynamicBeam::f3
const Vec3 f3
Definition: aeroelem.h:354
a
static const doublereal a
Definition: hfluid_.h:289
Elem::Elem
Elem(unsigned int uL, flag fOut)
Definition: elem.cc:41
AerodynamicBeam::Ra2_3
const Vec3 Ra2_3
Definition: aeroelem.h:359
AerodynamicBeam::Ra3
const Mat3x3 Ra3
Definition: aeroelem.h:357

Here is the call graph for this function:

AerodynamicBeam::~AerodynamicBeam ( void  )
virtual

Definition at line 1521 of file aeroelem.cc.

References DEBUGCOUTFNAME.

1522 {
1523  DEBUGCOUTFNAME("AerodynamicBeam::~AerodynamicBeam");
1524 }
DEBUGCOUTFNAME
#define DEBUGCOUTFNAME(fname)
Definition: myassert.h:256

Member Function Documentation

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

Implements Elem.

Definition at line 1562 of file aeroelem.cc.

References Aerodynamic2DElem< 3 >::aerodata, AeroData::AssJac(), Aerodynamic2DElem< 3 >::bJacobian, c, Aerodynamic2DElem< 3 >::Chord, grad::cos(), Aerodynamic2DElem< 3 >::cq, Vec3::Cross(), DEBUGCOUT, DELTAg1, DELTAg2, DELTAg3, DELTAx1, DELTAx2, DELTAx3, ShapeOwner::dGet(), DriveOwner::dGet(), Rotor::dGetOmega(), PntWght::dGetPnt(), PntWght::dGetWght(), dN2, dN3, DxDcsi3N(), Eye3, f1, f2, f3, AirPropOwner::fGetAirVelocity(), GaussDataIterator::fGetNext(), Aerodynamic2DElem< 3 >::ForcePoint, Aerodynamic2DElem< 3 >::fq, Aerodynamic2DElem< 3 >::GDI, AirPropOwner::GetAirProps(), Elem::GetElemType(), GaussDataIterator::GetFirst(), AeroData::GetForcesJac(), InducedVelocity::GetInducedVelocity(), WithLabel::GetLabel(), Mat6x6::GetMat11(), Mat6x6::GetMat12(), Mat6x6::GetMat21(), Mat6x6::GetMat22(), Mat3xN::GetVec(), StructDispNode::GetXCurr(), DofOwnerOwner::iGetFirstIndex(), StructDispNode::iGetFirstMomentumIndex(), StructDispNode::iGetFirstPositionIndex(), AeroData::iGetNumDof(), LASTNODE, MatCross, MatCrossCross, ER_Rot::MatG, ER_Rot::MatGm1, ER_Rot::MatR, Mat3x3::MulMT(), Mat3x3::MulTM(), MultRMRt(), Mat3x3::MulTV(), NODE1, NODE2, NODE3, Aerodynamic2DElem< 3 >::OUTA, ER_Rot::Param, pdsf3, pdsi3, Aerodynamic2DElem< 3 >::pIndVel, pNode, FullSubMatrixHandler::PutColIndex(), Mat3xN::PutMat3x3(), FullSubMatrixHandler::PutRowIndex(), Vec3::PutTo(), Ra1, Ra2, Ra3, Mat3x3::Reset(), AerodynamicOutput::ResetIterator(), FullSubMatrixHandler::ResizeReset(), AeroData::SetAirData(), VariableSubMatrixHandler::SetFull(), VariableSubMatrixHandler::SetNullMatrix(), AeroData::SetSectionData(), ShapeFunc3N(), grad::sin(), FullSubMatrixHandler::Sub(), Mat3x3::Transpose(), Aerodynamic2DElem< 3 >::Twist, Aerodynamic2DElem< 3 >::VelocityPoint, Aerodynamic2DElem< 3 >::vx, Elem::WorkSpaceDim(), Aerodynamic2DElem< 3 >::wx, and Zero3.

1566 {
1567  DEBUGCOUT("Entering AerodynamicBeam::AssJac()" << std::endl);
1568 
1569  if (!bJacobian) {
1570  WorkMat.SetNullMatrix();
1571  return WorkMat;
1572  }
1573 
1574  FullSubMatrixHandler& WM = WorkMat.SetFull();
1575 
1576  /* Ridimensiona la sottomatrice in base alle esigenze */
1577  integer iNumRows = 0;
1578  integer iNumCols = 0;
1579  WorkSpaceDim(&iNumRows, &iNumCols);
1580  WM.ResizeReset(iNumRows, iNumCols);
1581 
1582  integer iNode1FirstIndex = pNode[NODE1]->iGetFirstMomentumIndex();
1583  integer iNode1FirstPosIndex = pNode[NODE1]->iGetFirstPositionIndex();
1584  integer iNode2FirstIndex = pNode[NODE2]->iGetFirstMomentumIndex();
1585  integer iNode2FirstPosIndex = pNode[NODE2]->iGetFirstPositionIndex();
1586  integer iNode3FirstIndex = pNode[NODE3]->iGetFirstMomentumIndex();
1587  integer iNode3FirstPosIndex = pNode[NODE3]->iGetFirstPositionIndex();
1588 
1589  for (int iCnt = 1; iCnt <= 6; iCnt++) {
1590  WM.PutRowIndex(iCnt, iNode1FirstIndex + iCnt);
1591  WM.PutColIndex(iCnt, iNode1FirstPosIndex + iCnt);
1592  WM.PutRowIndex(6 + iCnt, iNode2FirstIndex + iCnt);
1593  WM.PutColIndex(6 + iCnt, iNode2FirstPosIndex + iCnt);
1594  WM.PutRowIndex(12 + iCnt, iNode3FirstIndex + iCnt);
1595  WM.PutColIndex(12 + iCnt, iNode3FirstPosIndex + iCnt);
1596  }
1597 
1598  doublereal dW[6];
1599 
1600  /* array di vettori per via del ciclo sui nodi ... */
1601  Vec3 Xn[3];
1602 
1603  /* Dati dei nodi */
1604  Xn[NODE1] = pNode[NODE1]->GetXCurr();
1605  const Mat3x3& Rn1(pNode[NODE1]->GetRCurr());
1606  const Vec3& Vn1(pNode[NODE1]->GetVCurr());
1607  const Vec3& Wn1(pNode[NODE1]->GetWCurr());
1608 
1609  Xn[NODE2] = pNode[NODE2]->GetXCurr();
1610  const Mat3x3& Rn2(pNode[NODE2]->GetRCurr());
1611  const Vec3& Vn2(pNode[NODE2]->GetVCurr());
1612  const Vec3& Wn2(pNode[NODE2]->GetWCurr());
1613 
1614  Xn[NODE3] = pNode[NODE3]->GetXCurr();
1615  const Mat3x3& Rn3(pNode[NODE3]->GetRCurr());
1616  const Vec3& Vn3(pNode[NODE3]->GetVCurr());
1617  const Vec3& Wn3(pNode[NODE3]->GetWCurr());
1618 
1619  Vec3 f1Tmp(Rn1*f1);
1620  Vec3 f2Tmp(Rn2*f2);
1621  Vec3 f3Tmp(Rn3*f3);
1622 
1623  Vec3 X1Tmp(Xn[NODE1] + f1Tmp);
1624  Vec3 X2Tmp(Xn[NODE2] + f2Tmp);
1625  Vec3 X3Tmp(Xn[NODE3] + f3Tmp);
1626 
1627  Vec3 V1Tmp(Vn1 + Wn1.Cross(f1Tmp));
1628  Vec3 V2Tmp(Vn2 + Wn2.Cross(f2Tmp));
1629  Vec3 V3Tmp(Vn3 + Wn3.Cross(f3Tmp));
1630 
1631  Vec3 Omega1Crossf1(Wn1.Cross(f1Tmp));
1632  Vec3 Omega2Crossf2(Wn2.Cross(f2Tmp));
1633  Vec3 Omega3Crossf3(Wn3.Cross(f3Tmp));
1634 
1635  /*
1636  * Matrice di trasformazione dal sistema globale a quello aerodinamico
1637  */
1638  Mat3x3 RR1(Rn1*Ra1);
1639  Mat3x3 RR2(Rn2*Ra2);
1640  Mat3x3 RR3(Rn3*Ra3);
1641 
1642  /*
1643  * Parametri di rotazione dai nodi 1 e 3 al nodo 2 (nell'ipotesi
1644  * che tale trasformazione non dia luogo ad una singolarita')
1645  */
1646 
1647  Vec3 g1(ER_Rot::Param, RR2.MulTM(RR1));
1648  Vec3 g3(ER_Rot::Param, RR2.MulTM(RR3));
1649 
1650  Mat3x3 GammaInv1(ER_Rot::MatGm1, g1);
1651  Mat3x3 GammaInv3(ER_Rot::MatGm1, g3);
1652 
1653  /*
1654  * Se l'elemento e' collegato ad un rotore,
1655  * si fa dare la velocita' di rotazione
1656  */
1657  doublereal dOmega = 0.;
1658  if (pIndVel != 0) {
1659  Rotor *pRotor = dynamic_cast<Rotor *>(pIndVel);
1660  if (pRotor != 0) {
1661  dOmega = pRotor->dGetOmega();
1662  }
1663  }
1664 
1665  /*
1666  * Dati "permanenti" (uso solo la posizione del nodo 2 perche'
1667  * non dovrebbero cambiare "molto")
1668  */
1669  doublereal rho, c, p, T;
1670  GetAirProps(Xn[NODE2], rho, c, p, T); /* p, T no used yet */
1671  aerodata->SetAirData(rho, c);
1672 
1673  int iPnt = 0;
1674 
1675  ResetIterator();
1676 
1677  integer iNumDof = aerodata->iGetNumDof();
1678  integer iFirstEq = -1;
1679  integer iFirstSubEq = -1;
1680  if (iNumDof > 0) {
1681  iFirstEq = iGetFirstIndex();
1682  iFirstSubEq = 18;
1683 
1684  integer iOffset = iFirstEq - 18;
1685 
1686  for (int iCnt = 18 + 1; iCnt <= iNumRows; iCnt++) {
1687  WM.PutRowIndex(iCnt, iOffset + iCnt);
1688  WM.PutColIndex(iCnt, iOffset + iCnt);
1689  }
1690  }
1691 
1692  for (int iNode = 0; iNode < LASTNODE; iNode++) {
1693  doublereal dsi = pdsi3[iNode];
1694  doublereal dsf = pdsf3[iNode];
1695 
1696  doublereal dsm = (dsf + dsi)/2.;
1697  doublereal dsdCsi = (dsf - dsi)/2.;
1698 
1699  Mat3x3 WM_F[6], WM_M[6];
1700  WM_F[DELTAx1].Reset();
1701  WM_F[DELTAg1].Reset();
1702  WM_F[DELTAx2].Reset();
1703  WM_F[DELTAg2].Reset();
1704  WM_F[DELTAx3].Reset();
1705  WM_F[DELTAg3].Reset();
1706  WM_M[DELTAx1].Reset();
1707  WM_M[DELTAg1].Reset();
1708  WM_M[DELTAx2].Reset();
1709  WM_M[DELTAg2].Reset();
1710  WM_M[DELTAx3].Reset();
1711  WM_M[DELTAg3].Reset();
1712 
1713  //unsigned int iDelta_x1, iDelta_g1, iDelta_x2, iDelta_g2, iDelta_x3, iDelta_g3;
1714  //iDelta_x1 = 0;, iDelta_g1, iDelta_x2, iDelta_g2, iDelta_x3, iDelta_g3;
1715 
1716  /* Ciclo sui punti di Gauss */
1717  PntWght PW = GDI.GetFirst();
1718  do {
1719  doublereal dCsi = PW.dGetPnt();
1720  doublereal ds = dsm + dsdCsi*dCsi;
1721  doublereal dXds = DxDcsi3N(ds,
1722  Xn[NODE1], Xn[NODE2], Xn[NODE3]);
1723 
1724  doublereal dN1 = ShapeFunc3N(ds, 1);
1725  doublereal dN2 = ShapeFunc3N(ds, 2);
1726  doublereal dN3 = ShapeFunc3N(ds, 3);
1727 
1728  Vec3 Xr(X1Tmp*dN1 + X2Tmp*dN2 + X3Tmp*dN3);
1729  Vec3 Vr(V1Tmp*dN1 + V2Tmp*dN2 + V3Tmp*dN3);
1730  Vec3 Wr(Wn1*dN1 + Wn2*dN2 + Wn3*dN3);
1731  Vec3 gr(g1*dN1 + g3*dN3);
1732  Mat3x3 Gamma(ER_Rot::MatG, gr);
1733 
1734  /* Contributo di velocita' del vento */
1735  Vec3 VTmp(Zero3);
1736  if (fGetAirVelocity(VTmp, Xr)) {
1737  Vr -= VTmp;
1738  }
1739 
1740  /*
1741  * Se l'elemento e' collegato ad un rotore,
1742  * aggiunge alla velocita' la velocita' indotta
1743  */
1744  if (pIndVel != 0) {
1745  Vr += pIndVel->GetInducedVelocity(GetElemType(),
1746  GetLabel(), iPnt, Xr);
1747  }
1748 
1749  /* Copia i dati nel vettore di lavoro dVAM */
1750  doublereal dTw = Twist.dGet(ds);
1751  /* Contributo dell'eventuale sup. mobile */
1752  dTw += dGet();
1753 
1754  aerodata->SetSectionData(dCsi,
1755  Chord.dGet(ds),
1756  ForcePoint.dGet(ds),
1757  VelocityPoint.dGet(ds),
1758  dTw,
1759  dOmega);
1760 
1761  /*
1762  * Lo svergolamento non viene piu' trattato in aerod2_;
1763  * quindi lo uso per correggere la matrice di rotazione
1764  * dal sistema aerodinamico a quello globale
1765  */
1766  Mat3x3 RRloc(RR2*Mat3x3(ER_Rot::MatR, gr));
1767  if (dTw != 0.) {
1768  doublereal dCosT = cos(dTw);
1769  doublereal dSinT = sin(dTw);
1770  /* Assumo lo svergolamento positivo a cabrare */
1771  Mat3x3 RTw(dCosT, dSinT, 0.,
1772  -dSinT, dCosT, 0.,
1773  0., 0., 1.);
1774  /*
1775  * Allo stesso tempo interpola le g
1776  * e aggiunge lo svergolamento
1777  */
1778  RRloc = RRloc*RTw;
1779  }
1780 
1781  /*
1782  * Ruota velocita' e velocita' angolare nel sistema
1783  * aerodinamico e li copia nel vettore di lavoro dW
1784  */
1785  VTmp = RRloc.MulTV(Vr);
1786  VTmp.PutTo(&dW[0]);
1787 
1788  Vec3 WTmp = RRloc.MulTV(Wr);
1789  WTmp.PutTo(&dW[3]);
1790  /* Funzione di calcolo delle forze aerodinamiche */
1791  doublereal Fa0[6];
1792  Mat6x6 JFa;
1793 
1794  doublereal cc = dXds*dsdCsi*PW.dGetWght();
1795 
1796  Vec3 d(Xr - Xn[iNode]);
1797 
1798  Mat3x3 Theta1(RR2*Gamma*GammaInv1.MulMT(RR2*dN1));
1799  Mat3x3 Theta3(RR2*Gamma*GammaInv3.MulMT(RR2*dN3));
1800  Mat3x3 Theta2(Eye3 - Theta1 - Theta3);
1801 
1802  Vec3 Vrc(Vr*dCoef);
1803  Mat3x3 Bv1(Vrc.Cross(Theta1) - Mat3x3(MatCross, Omega1Crossf1*(dN1*dCoef)));
1804  Mat3x3 Bv2(Vrc.Cross(Theta2) - Mat3x3(MatCross, Omega2Crossf2*(dN2*dCoef)));
1805  Mat3x3 Bv3(Vrc.Cross(Theta3) - Mat3x3(MatCross, Omega3Crossf3*(dN3*dCoef)));
1806 
1807  Vec3 Wrc(Wr*dCoef);
1808  Mat3x3 Bw1(Wrc.Cross(Theta1) - Mat3x3(MatCross, Wn1*(dN1*dCoef)));
1809  Mat3x3 Bw2(Wrc.Cross(Theta2) - Mat3x3(MatCross, Wn2*(dN2*dCoef)));
1810  Mat3x3 Bw3(Wrc.Cross(Theta3) - Mat3x3(MatCross, Wn3*(dN3*dCoef)));
1811 
1812  if (iNumDof) {
1813  // prepare (v/dot{x} + dCoef*v/x) and so
1814  Mat3x3 RRlocT(RRloc.Transpose());
1815 
1816  vx.PutMat3x3(1, RRlocT*dN1);
1817  vx.PutMat3x3(4, RRloc.MulTM(Bv1 - Mat3x3(MatCross, f1Tmp*dN1)));
1818 
1819  vx.PutMat3x3(6 + 1, RRlocT*dN2);
1820  vx.PutMat3x3(6 + 4, RRloc.MulTM(Bv2 - Mat3x3(MatCross, f2Tmp*dN2)));
1821 
1822  vx.PutMat3x3(12 + 1, RRlocT*dN3);
1823  vx.PutMat3x3(12 + 4, RRloc.MulTM(Bv3 - Mat3x3(MatCross, f3Tmp*dN3)));
1824 
1825  wx.PutMat3x3(4, RRlocT + Bw1);
1826  wx.PutMat3x3(6 + 4, RRlocT + Bw2);
1827  wx.PutMat3x3(12 + 4, RRlocT + Bw3);
1828 
1829  // equations from iFirstEq on are dealt with by aerodata
1830  aerodata->AssJac(WM, dCoef, XCurr, XPrimeCurr,
1831  iFirstEq, iFirstSubEq,
1832  vx, wx, fq, cq, iPnt, dW, Fa0, JFa, OUTA[iPnt]);
1833 
1834  // deal with (f/dot{q} + dCoef*f/q) and so
1835  integer iOffset = 18 + iPnt*iNumDof;
1836  for (integer iCol = 1; iCol <= iNumDof; iCol++) {
1837  Vec3 fqTmp((RRloc*fq.GetVec(iCol))*cc);
1838  Vec3 cqTmp(d.Cross(fqTmp) + (RRloc*cq.GetVec(iCol))*cc);
1839 
1840  WM.Sub(6*iNode + 1, iOffset + iCol, fqTmp);
1841  WM.Sub(6*iNode + 4, iOffset + iCol, cqTmp);
1842  }
1843 
1844  // first equation
1845  iFirstEq += iNumDof;
1846  iFirstSubEq += iNumDof;
1847 
1848  } else {
1849  aerodata->GetForcesJac(iPnt, dW, Fa0, JFa, OUTA[iPnt]);
1850  }
1851 
1852  // rotate force, couple and Jacobian matrix in absolute frame
1853  Mat6x6 JFaR = MultRMRt(JFa, RRloc, cc);
1854 
1855  // force and moment about the node
1856  Vec3 fTmp(RRloc*(Vec3(&Fa0[0])*dCoef));
1857  Vec3 cTmp(RRloc*(Vec3(&Fa0[3])*dCoef) + d.Cross(fTmp));
1858 
1859  Mat3x3 WM_F2[6];
1860 
1861  // f <-> x
1862  WM_F2[DELTAx1] = JFaR.GetMat11()*dN1;
1863 
1864  WM_F2[DELTAx2] = JFaR.GetMat11()*dN2;
1865 
1866  WM_F2[DELTAx3] = JFaR.GetMat11()*dN3;
1867 
1868  doublereal delta;
1869 
1870  // c <-> x
1871  delta = (iNode == NODE1) ? 1. : 0.;
1872  WM_M[DELTAx1] += JFaR.GetMat21()*dN1 - Mat3x3(MatCross, fTmp*(dN1 - delta));
1873 
1874  delta = (iNode == NODE2) ? 1. : 0.;
1875  WM_M[DELTAx2] += JFaR.GetMat21()*dN2 - Mat3x3(MatCross, fTmp*(dN2 - delta));
1876 
1877  delta = (iNode == NODE3) ? 1. : 0.;
1878  WM_M[DELTAx3] += JFaR.GetMat21()*dN3 - Mat3x3(MatCross, fTmp*(dN3 - delta));
1879 
1880  // f <-> g
1881  WM_F2[DELTAg1] = (JFaR.GetMat12() - JFaR.GetMat11()*Mat3x3(MatCross, f1Tmp))*dN1;
1882  WM_F2[DELTAg1] += JFaR.GetMat11()*Bv1 + JFaR.GetMat12()*Bw1;
1883  WM_F2[DELTAg1] -= fTmp.Cross(Theta1);
1884 
1885  WM_F2[DELTAg2] = (JFaR.GetMat12() - JFaR.GetMat11()*Mat3x3(MatCross, f2Tmp))*dN2;
1886  WM_F2[DELTAg2] += JFaR.GetMat11()*Bv2 + JFaR.GetMat12()*Bw2;
1887  WM_F2[DELTAg2] -= fTmp.Cross(Theta2);
1888 
1889  WM_F2[DELTAg3] = (JFaR.GetMat12() - JFaR.GetMat11()*Mat3x3(MatCross, f3Tmp))*dN3;
1890  WM_F2[DELTAg3] += JFaR.GetMat11()*Bv3 + JFaR.GetMat12()*Bw3;
1891  WM_F2[DELTAg3] -= fTmp.Cross(Theta3);
1892 
1893  // c <-> g
1894  WM_M[DELTAg1] += (JFaR.GetMat22() - JFaR.GetMat21()*Mat3x3(MatCross, f1Tmp))*dN1;
1895  WM_M[DELTAg1] += JFaR.GetMat21()*Bv1 + JFaR.GetMat22()*Bw1;
1896  WM_M[DELTAg1] -= cTmp.Cross(Theta1);
1897  WM_M[DELTAg1] += Mat3x3(MatCrossCross, fTmp, f1Tmp*dN1);
1898 
1899  WM_M[DELTAg2] += (JFaR.GetMat22() - JFaR.GetMat21()*Mat3x3(MatCross, f2Tmp))*dN2;
1900  WM_M[DELTAg2] += JFaR.GetMat21()*Bv2 + JFaR.GetMat22()*Bw2;
1901  WM_M[DELTAg2] -= cTmp.Cross(Theta2);
1902  WM_M[DELTAg2] += Mat3x3(MatCrossCross, fTmp, f2Tmp*dN2);
1903 
1904  WM_M[DELTAg3] += (JFaR.GetMat22() - JFaR.GetMat21()*Mat3x3(MatCross, f3Tmp))*dN3;
1905  WM_M[DELTAg3] += JFaR.GetMat21()*Bv3 + JFaR.GetMat22()*Bw3;
1906  WM_M[DELTAg3] -= cTmp.Cross(Theta3);
1907  WM_M[DELTAg3] += Mat3x3(MatCrossCross, fTmp, f3Tmp*dN3);
1908 
1909  for (int iCnt = 0; iCnt < 2*LASTNODE; iCnt++) {
1910  WM_F[iCnt] += WM_F2[iCnt];
1911  WM_M[iCnt] += d.Cross(WM_F2[iCnt]);
1912  }
1913 
1914  iPnt++;
1915 
1916  } while (GDI.fGetNext(PW));
1917 
1918  for (int iCnt = 0; iCnt < 2*LASTNODE; iCnt++) {
1919  WM.Sub(6*iNode + 1, 3*iCnt + 1, WM_F[iCnt]);
1920  WM.Sub(6*iNode + 4, 3*iCnt + 1, WM_M[iCnt]);
1921  }
1922  }
1923 
1924  return WorkMat;
1925 }
AerodynamicOutput::ResetIterator
void ResetIterator(void)
Definition: aeroelem.cc:77
MultRMRt
Mat3x3 MultRMRt(const Mat3x3 &m, const Mat3x3 &R)
Definition: matvec3.cc:1162
FullSubMatrixHandler::PutColIndex
void PutColIndex(integer iSubCol, integer iCol)
Definition: submat.h:325
AeroData::SetSectionData
virtual void SetSectionData(const doublereal &abscissa, const doublereal &chord, const doublereal &forcepoint, const doublereal &velocitypoint, const doublereal &twist, const doublereal &omega=0.)
Definition: aerodata.cc:237
Zero3
const Vec3 Zero3(0., 0., 0.)
AirPropOwner::GetAirProps
virtual bool GetAirProps(const Vec3 &X, doublereal &rho, doublereal &c, doublereal &p, doublereal &T) const
Definition: aerodyn.cc:760
AerodynamicBeam::Ra1
const Mat3x3 Ra1
Definition: aeroelem.h:355
Mat6x6::GetMat12
Mat3x3 GetMat12(void)
Definition: matvec6.h:328
AeroData::GetForcesJac
virtual int GetForcesJac(int i, const doublereal *W, doublereal *TNG, Mat6x6 &J, outa_t &OUTA)
Definition: aerodata.cc:384
Vec3
Definition: matvec3.h:98
grad::sin
GradientExpression< UnaryExpr< FuncSin, Expr > > sin(const GradientExpression< Expr > &u)
Definition: gradient.h:2977
ER_Rot::MatR
MatR_Manip MatR
Definition: Rot.cc:292
MatCross
const MatCross_Manip MatCross
Definition: matvec3.cc:639
VariableSubMatrixHandler::SetFull
FullSubMatrixHandler & SetFull(void)
Definition: submat.h:1168
GaussDataIterator::fGetNext
flag fGetNext(doublereal &d, integer i=0) const
Definition: gauss.cc:205
Mat6x6::GetMat21
Mat3x3 GetMat21(void)
Definition: matvec6.h:324
AeroData::iGetNumDof
virtual unsigned int iGetNumDof(void) const
Definition: aerodata.cc:362
GaussDataIterator::GetFirst
PntWght GetFirst(void) const
Definition: gauss.cc:198
DriveOwner::dGet
doublereal dGet(void) const
Definition: drive.cc:671
Eye3
const Mat3x3 Eye3(1., 0., 0., 0., 1., 0., 0., 0., 1.)
Aerodynamic2DElem< 3 >::OUTA
std::vector< outa_t > OUTA
Definition: aeroelem.h:164
Aerodynamic2DElem< 3 >::Chord
const ShapeOwner Chord
Definition: aeroelem.h:157
Aerodynamic2DElem< 3 >::pIndVel
InducedVelocity * pIndVel
Definition: aeroelem.h:154
Mat3xN::PutMat3x3
void PutMat3x3(integer iCol, const Mat3x3 &m)
Definition: matvec3n.cc:628
ER_Rot::Param
Param_Manip Param
Definition: Rot.cc:291
ShapeFunc3N
doublereal ShapeFunc3N(doublereal d, integer iNode, enum Order Ord)
Definition: shapefnc.cc:173
Mat6x6::GetMat22
Mat3x3 GetMat22(void)
Definition: matvec6.h:332
Elem::GetElemType
virtual Elem::Type GetElemType(void) const =0
AerodynamicBeam::Ra2
const Mat3x3 Ra2
Definition: aeroelem.h:356
Aerodynamic2DElem< 3 >::Twist
const ShapeOwner Twist
Definition: aeroelem.h:160
Aerodynamic2DElem< 3 >::aerodata
AeroData * aerodata
Definition: aeroelem.h:153
AeroData::SetAirData
virtual void SetAirData(const doublereal &rho, const doublereal &c)
Definition: aerodata.cc:214
Mat6x6::GetMat11
Mat3x3 GetMat11(void)
Definition: matvec6.h:320
Mat3xN::GetVec
Vec3 GetVec(integer iCol) const
Definition: matvec3n.cc:553
Mat3x3::Reset
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Definition: matvec3.cc:613
PntWght::dGetWght
doublereal dGetWght(void) const
Definition: gauss.h:56
dN2
const doublereal dN2[2]
Definition: shapefnc.cc:52
AerodynamicBeam::pNode
const StructNode * pNode[3]
Definition: aeroelem.h:350
Aerodynamic2DElem< 3 >::ForcePoint
const ShapeOwner ForcePoint
Definition: aeroelem.h:158
VariableSubMatrixHandler::SetNullMatrix
void SetNullMatrix(void)
Definition: submat.h:1159
dN3
const doublereal dN3[2][3]
Definition: shapefnc.cc:157
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static const doublereal pdsf3[]
Definition: aeroelem.cc:1558
Vec3::PutTo
void PutTo(doublereal *pd) const
Definition: matvec3.h:339
InducedVelocity::GetInducedVelocity
virtual Vec3 GetInducedVelocity(Elem::Type type, unsigned uLabel, unsigned uPnt, const Vec3 &X) const =0
DEBUGCOUT
#define DEBUGCOUT(msg)
Definition: myassert.h:232
Aerodynamic2DElem< 3 >::GDI
GaussDataIterator GDI
Definition: aeroelem.h:163
StructDispNode::iGetFirstMomentumIndex
virtual integer iGetFirstMomentumIndex(void) const =0
ShapeOwner::dGet
virtual doublereal dGet(doublereal d) const
Definition: shape.cc:60
StructDispNode::iGetFirstPositionIndex
virtual integer iGetFirstPositionIndex(void) const
Definition: strnode.h:452
ER_Rot::MatG
MatG_Manip MatG
Definition: Rot.cc:293
AerodynamicBeam::f2
const Vec3 f2
Definition: aeroelem.h:353
AerodynamicBeam::f1
const Vec3 f1
Definition: aeroelem.h:352
Rotor::dGetOmega
virtual doublereal dGetOmega(void) const
Definition: rotor.h:151
StructDispNode::GetXCurr
virtual const Vec3 & GetXCurr(void) const
Definition: strnode.h:310
FullSubMatrixHandler::ResizeReset
virtual void ResizeReset(integer, integer)
Definition: submat.cc:182
Aerodynamic2DElem< 3 >::VelocityPoint
const ShapeOwner VelocityPoint
Definition: aeroelem.h:159
c
static std::stack< cleanup * > c
Definition: cleanup.cc:59
MatCrossCross
const MatCrossCross_Manip MatCrossCross
Definition: matvec3.cc:640
DxDcsi3N
doublereal DxDcsi3N(doublereal d, const Vec3 &X1, const Vec3 &X2, const Vec3 &X3)
Definition: shapefnc.cc:228
PntWght::dGetPnt
doublereal dGetPnt(void) const
Definition: gauss.h:55
FullSubMatrixHandler::PutRowIndex
void PutRowIndex(integer iSubRow, integer iRow)
Definition: submat.h:311
AerodynamicBeam::f3
const Vec3 f3
Definition: aeroelem.h:354
Elem::WorkSpaceDim
virtual void WorkSpaceDim(integer *piNumRows, integer *piNumCols) const =0
FullSubMatrixHandler::Sub
void Sub(integer iRow, integer iCol, const Vec3 &v)
Definition: submat.cc:215
AirPropOwner::fGetAirVelocity
virtual flag fGetAirVelocity(Vec3 &Velocity, const Vec3 &X) const
Definition: aerodyn.cc:725
grad::cos
GradientExpression< UnaryExpr< FuncCos, Expr > > cos(const GradientExpression< Expr > &u)
Definition: gradient.h:2978
pdsi3
static const doublereal pdsi3[]
Definition: aeroelem.cc:1557
DofOwnerOwner::iGetFirstIndex
virtual integer iGetFirstIndex(void) const
Definition: dofown.h:127
AeroData::AssJac
virtual void AssJac(FullSubMatrixHandler &WorkMat, doublereal dCoef, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr, integer iFirstIndex, integer iFirstSubIndex, const Mat3xN &vx, const Mat3xN &wx, Mat3xN &fq, Mat3xN &cq, int i, const doublereal *W, doublereal *TNG, Mat6x6 &J, outa_t &OUTA)
Definition: aerodata.cc:403
doublereal
double doublereal
Definition: colamd.c:52
integer
long int integer
Definition: colamd.c:51
WithLabel::GetLabel
unsigned int GetLabel(void) const
Definition: withlab.cc:62
ER_Rot::MatGm1
MatGm1_Manip MatGm1
Definition: Rot.cc:294
AerodynamicBeam::Ra3
const Mat3x3 Ra3
Definition: aeroelem.h:357
Rotor
Definition: rotor.h:43
PntWght
Definition: gauss.h:50

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

Implements Elem.

Definition at line 1929 of file aeroelem.cc.

References AssVec(), DEBUGCOUTFNAME, StructDispNode::iGetFirstMomentumIndex(), NODE1, NODE2, NODE3, pNode, SubVectorHandler::PutRowIndex(), VectorHandler::ResizeReset(), and Elem::WorkSpaceDim().

1933 {
1934  DEBUGCOUTFNAME("AerodynamicBeam::AssRes");
1935 
1936  integer iNumRows;
1937  integer iNumCols;
1938  WorkSpaceDim(&iNumRows, &iNumCols);
1939  WorkVec.ResizeReset(iNumRows);
1940 
1941  integer iNode1FirstIndex = pNode[NODE1]->iGetFirstMomentumIndex();
1942  integer iNode2FirstIndex = pNode[NODE2]->iGetFirstMomentumIndex();
1943  integer iNode3FirstIndex = pNode[NODE3]->iGetFirstMomentumIndex();
1944  for (int iCnt = 1; iCnt <= 6; iCnt++) {
1945  WorkVec.PutRowIndex(iCnt, iNode1FirstIndex + iCnt);
1946  WorkVec.PutRowIndex(6 + iCnt, iNode2FirstIndex + iCnt);
1947  WorkVec.PutRowIndex(12 + iCnt, iNode3FirstIndex + iCnt);
1948  }
1949 
1950  AssVec(WorkVec, dCoef, XCurr, XPrimeCurr);
1951 
1952  return WorkVec;
1953 }
DEBUGCOUTFNAME
#define DEBUGCOUTFNAME(fname)
Definition: myassert.h:256
VectorHandler::ResizeReset
virtual void ResizeReset(integer)
Definition: vh.cc:55
SubVectorHandler::PutRowIndex
virtual void PutRowIndex(integer iSubRow, integer iRow)=0
AerodynamicBeam::AssVec
void AssVec(SubVectorHandler &WorkVec, doublereal dCoef, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr)
Definition: aeroelem.cc:1980
AerodynamicBeam::pNode
const StructNode * pNode[3]
Definition: aeroelem.h:350
StructDispNode::iGetFirstMomentumIndex
virtual integer iGetFirstMomentumIndex(void) const =0
Elem::WorkSpaceDim
virtual void WorkSpaceDim(integer *piNumRows, integer *piNumCols) const =0
integer
long int integer
Definition: colamd.c:51

Here is the call graph for this function:

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

Definition at line 1980 of file aeroelem.cc.

References VectorHandler::Add(), Aerodynamic2DElem< 3 >::AddForce_int(), Aerodynamic2DElem< 3 >::AddSectionalForce_int(), Aerodynamic2DElem< 3 >::aerodata, AeroData::AssRes(), ToBeOutput::bToBeOutput(), c, Aerodynamic2DElem< 3 >::Chord, grad::cos(), Vec3::Cross(), grad::Cross(), DEBUGCOUTFNAME, ShapeOwner::dGet(), DriveOwner::dGet(), Rotor::dGetOmega(), PntWght::dGetPnt(), PntWght::dGetWght(), dN2, dN3, DxDcsi3N(), F, f1, f2, f3, AirPropOwner::fGetAirVelocity(), GaussDataIterator::fGetNext(), Aerodynamic2DElem< 3 >::ForcePoint, Aerodynamic2DElem< 3 >::GDI, AirPropOwner::GetAirProps(), Elem::GetElemType(), GaussDataIterator::GetFirst(), AeroData::GetForces(), InducedVelocity::GetInducedVelocity(), WithLabel::GetLabel(), StructDispNode::GetXCurr(), DofOwnerOwner::iGetFirstIndex(), AeroData::iGetNumDof(), VectorHandler::iGetSize(), LASTNODE, M, ER_Rot::MatR, Mat3x3::MulTM(), Mat3x3::MulTV(), NODE1, NODE2, NODE3, Aerodynamic2DElem< 3 >::OUTA, ER_Rot::Param, pdsf3, pdsi3, Aerodynamic2DElem< 3 >::pIndVel, pNode, SubVectorHandler::PutRowIndex(), Vec3::PutTo(), Ra1, Ra2, Ra3, Vec3::Reset(), AerodynamicOutput::ResetIterator(), AeroData::SetAirData(), AerodynamicOutput::SetData(), AeroData::SetSectionData(), ShapeFunc3N(), grad::sin(), Aerodynamic2DElem< 3 >::TipLoss, Aerodynamic2DElem< 3 >::Twist, Aerodynamic2DElem< 3 >::VelocityPoint, and Zero3.

Referenced by AssRes(), and InitialAssRes().

1984 {
1985  DEBUGCOUTFNAME("AerodynamicBeam::AssVec");
1986 
1987  /* array di vettori per via del ciclo sui nodi ... */
1988  Vec3 Xn[3];
1989 
1990  /* Dati dei nodi */
1991  Xn[NODE1] = pNode[NODE1]->GetXCurr();
1992  const Mat3x3& Rn1(pNode[NODE1]->GetRCurr());
1993  const Vec3& Vn1(pNode[NODE1]->GetVCurr());
1994  const Vec3& Wn1(pNode[NODE1]->GetWCurr());
1995 
1996  Xn[NODE2] = pNode[NODE2]->GetXCurr();
1997  const Mat3x3& Rn2(pNode[NODE2]->GetRCurr());
1998  const Vec3& Vn2(pNode[NODE2]->GetVCurr());
1999  const Vec3& Wn2(pNode[NODE2]->GetWCurr());
2000 
2001  Xn[NODE3] = pNode[NODE3]->GetXCurr();
2002  const Mat3x3& Rn3(pNode[NODE3]->GetRCurr());
2003  const Vec3& Vn3(pNode[NODE3]->GetVCurr());
2004  const Vec3& Wn3(pNode[NODE3]->GetWCurr());
2005 
2006  Vec3 f1Tmp(Rn1*f1);
2007  Vec3 f2Tmp(Rn2*f2);
2008  Vec3 f3Tmp(Rn3*f3);
2009 
2010  Vec3 X1Tmp(Xn[NODE1] + f1Tmp);
2011  Vec3 X2Tmp(Xn[NODE2] + f2Tmp);
2012  Vec3 X3Tmp(Xn[NODE3] + f3Tmp);
2013 
2014  Vec3 V1Tmp(Vn1 + Wn1.Cross(f1Tmp));
2015  Vec3 V2Tmp(Vn2 + Wn2.Cross(f2Tmp));
2016  Vec3 V3Tmp(Vn3 + Wn3.Cross(f3Tmp));
2017 
2018  /*
2019  * Matrice di trasformazione dal sistema globale a quello aerodinamico
2020  */
2021  Mat3x3 RR1(Rn1*Ra1);
2022  Mat3x3 RR2(Rn2*Ra2);
2023  Mat3x3 RR3(Rn3*Ra3);
2024 
2025  /*
2026  * Parametri di rotazione dai nodi 1 e 3 al nodo 2 (nell'ipotesi
2027  * che tale trasformazione non dia luogo ad una singolarita')
2028  */
2029  Vec3 g1(ER_Rot::Param, RR2.MulTM(RR1));
2030  Vec3 g3(ER_Rot::Param, RR2.MulTM(RR3));
2031 
2032  /*
2033  * Se l'elemento e' collegato ad un rotore,
2034  * si fa dare la velocita' di rotazione
2035  */
2036  doublereal dOmega = 0.;
2037  if (pIndVel != 0) {
2038  Rotor *pRotor = dynamic_cast<Rotor *>(pIndVel);
2039  if (pRotor != 0) {
2040  dOmega = pRotor->dGetOmega();
2041  }
2042  }
2043 
2044  /*
2045  * Dati "permanenti" (uso solo la posizione del nodo 2 perche'
2046  * non dovrebbero cambiare "molto")
2047  */
2048  doublereal rho, c, p, T;
2049  GetAirProps(Xn[NODE2], rho, c, p, T); /* p, T no used yet */
2050  aerodata->SetAirData(rho, c);
2051 
2052  int iPnt = 0;
2053 
2054  ResetIterator();
2055 
2056  integer iNumDof = aerodata->iGetNumDof();
2057  integer iFirstEq = -1;
2058  integer iFirstSubEq = -1;
2059  if (iNumDof > 0) {
2060  iFirstEq = iGetFirstIndex();
2061  iFirstSubEq = 18;
2062 
2063  integer iOffset = iFirstEq - 18;
2064  integer iNumRows = WorkVec.iGetSize();
2065  for (int iCnt = 18 + 1; iCnt <= iNumRows; iCnt++) {
2066  WorkVec.PutRowIndex(iCnt, iOffset + iCnt);
2067  }
2068  }
2069 
2070  for (int iNode = 0; iNode < LASTNODE; iNode++) {
2071 
2072  /* Resetta le forze */
2073  F[iNode].Reset();
2074  M[iNode].Reset();
2075 
2076  doublereal dsi = pdsi3[iNode];
2077  doublereal dsf = pdsf3[iNode];
2078 
2079  doublereal dsm = (dsf + dsi)/2.;
2080  doublereal dsdCsi = (dsf - dsi)/2.;
2081 
2082  /* Ciclo sui punti di Gauss */
2083  PntWght PW = GDI.GetFirst();
2084  do {
2085  doublereal dCsi = PW.dGetPnt();
2086  doublereal ds = dsm + dsdCsi*dCsi;
2087  doublereal dXds = DxDcsi3N(ds,
2088  Xn[NODE1], Xn[NODE2], Xn[NODE3]);
2089 
2090  doublereal dN1 = ShapeFunc3N(ds, 1);
2091  doublereal dN2 = ShapeFunc3N(ds, 2);
2092  doublereal dN3 = ShapeFunc3N(ds, 3);
2093 
2094  Vec3 Xr(X1Tmp*dN1 + X2Tmp*dN2 + X3Tmp*dN3);
2095  Vec3 Vr(V1Tmp*dN1 + V2Tmp*dN2 + V3Tmp*dN3);
2096  Vec3 Wr(Wn1*dN1 + Wn2*dN2 + Wn3*dN3);
2097 
2098  /* Contributo di velocita' del vento */
2099  Vec3 VTmp(Zero3);
2100  if (fGetAirVelocity(VTmp, Xr)) {
2101  Vr -= VTmp;
2102  }
2103 
2104  /*
2105  * Se l'elemento e' collegato ad un rotore,
2106  * aggiunge alla velocita' la velocita' indotta
2107  */
2108  if (pIndVel != 0) {
2109  Vr += pIndVel->GetInducedVelocity(GetElemType(),
2110  GetLabel(), iPnt, Xr);
2111  }
2112 
2113  /* Copia i dati nel vettore di lavoro dVAM */
2114  doublereal dTw = Twist.dGet(ds);
2115  /* Contributo dell'eventuale sup. mobile */
2116  dTw += dGet();
2117 
2118  aerodata->SetSectionData(dCsi,
2119  Chord.dGet(ds),
2120  ForcePoint.dGet(ds),
2121  VelocityPoint.dGet(ds),
2122  dTw,
2123  dOmega);
2124 
2125  /*
2126  * Lo svergolamento non viene piu' trattato in aerod2_;
2127  * quindi lo uso per correggere la matrice di rotazione
2128  * dal sistema aerodinamico a quello globale
2129  */
2130  Mat3x3 RRloc(RR2*Mat3x3(ER_Rot::MatR, g1*dN1 + g3*dN3));
2131  if (dTw != 0.) {
2132  doublereal dCosT = cos(dTw);
2133  doublereal dSinT = sin(dTw);
2134  /* Assumo lo svergolamento positivo a cabrare */
2135  Mat3x3 RTw(dCosT, dSinT, 0.,
2136  -dSinT, dCosT, 0.,
2137  0., 0., 1.);
2138  /*
2139  * Allo stesso tempo interpola le g
2140  * e aggiunge lo svergolamento
2141  */
2142  RRloc = RRloc*RTw;
2143  }
2144 
2145  /*
2146  * Ruota velocita' e velocita' angolare nel sistema
2147  * aerodinamico e li copia nel vettore di lavoro dW
2148  */
2149  doublereal dW[6];
2150  doublereal dTng[6];
2151 
2152  VTmp = RRloc.MulTV(Vr);
2153  VTmp.PutTo(&dW[0]);
2154 
2155  Vec3 WTmp = RRloc.MulTV(Wr);
2156  WTmp.PutTo(&dW[3]);
2157 
2158  /* Funzione di calcolo delle forze aerodinamiche */
2159  if (iNumDof) {
2160  aerodata->AssRes(WorkVec, dCoef, XCurr, XPrimeCurr,
2161  iFirstEq, iFirstSubEq, iPnt, dW, dTng, OUTA[iPnt]);
2162 
2163  // first equation
2164  iFirstEq += iNumDof;
2165  iFirstSubEq += iNumDof;
2166 
2167  } else {
2168  aerodata->GetForces(iPnt, dW, dTng, OUTA[iPnt]);
2169  }
2170 
2171  /* Dimensionalizza le forze */
2172  doublereal dWght = dXds*dsdCsi*PW.dGetWght();
2173  dTng[1] *= TipLoss.dGet(dCsi);
2174  Vec3 FTmp(RRloc*(Vec3(&dTng[0])));
2175  Vec3 MTmp(RRloc*(Vec3(&dTng[3])));
2176 
2177  // Se e' definito il rotore, aggiungere il contributo alla trazione
2178  AddSectionalForce_int(iPnt, FTmp, MTmp, dWght, Xr, RRloc, Vr, Wr);
2179 
2180  FTmp *= dWght;
2181  MTmp *= dWght;
2182  F[iNode] += FTmp;
2183  M[iNode] += MTmp;
2184  M[iNode] += (Xr - Xn[iNode]).Cross(FTmp);
2185 
2186  // specific for Gauss points force output
2187  if (bToBeOutput()) {
2188  SetData(VTmp, dTng, Xr, RRloc, Vr, Wr, FTmp, MTmp);
2189  }
2190 
2191  iPnt++;
2192 
2193  } while (GDI.fGetNext(PW));
2194 
2195  // Se e' definito il rotore, aggiungere il contributo alla trazione
2196  AddForce_int(pNode[iNode], F[iNode], M[iNode], Xn[iNode]);
2197 
2198  /* Somma il termine al residuo */
2199  WorkVec.Add(6*iNode + 1, F[iNode]);
2200  WorkVec.Add(6*iNode + 4, M[iNode]);
2201  }
2202 }
AerodynamicOutput::ResetIterator
void ResetIterator(void)
Definition: aeroelem.cc:77
AeroData::SetSectionData
virtual void SetSectionData(const doublereal &abscissa, const doublereal &chord, const doublereal &forcepoint, const doublereal &velocitypoint, const doublereal &twist, const doublereal &omega=0.)
Definition: aerodata.cc:237
Zero3
const Vec3 Zero3(0., 0., 0.)
AirPropOwner::GetAirProps
virtual bool GetAirProps(const Vec3 &X, doublereal &rho, doublereal &c, doublereal &p, doublereal &T) const
Definition: aerodyn.cc:760
AerodynamicBeam::Ra1
const Mat3x3 Ra1
Definition: aeroelem.h:355
ToBeOutput::bToBeOutput
virtual bool bToBeOutput(void) const
Definition: output.cc:890
Vec3
Definition: matvec3.h:98
grad::sin
GradientExpression< UnaryExpr< FuncSin, Expr > > sin(const GradientExpression< Expr > &u)
Definition: gradient.h:2977
DEBUGCOUTFNAME
#define DEBUGCOUTFNAME(fname)
Definition: myassert.h:256
ER_Rot::MatR
MatR_Manip MatR
Definition: Rot.cc:292
AerodynamicBeam::M
Vec3 M[LASTNODE]
Definition: aeroelem.h:367
GaussDataIterator::fGetNext
flag fGetNext(doublereal &d, integer i=0) const
Definition: gauss.cc:205
AeroData::iGetNumDof
virtual unsigned int iGetNumDof(void) const
Definition: aerodata.cc:362
GaussDataIterator::GetFirst
PntWght GetFirst(void) const
Definition: gauss.cc:198
DriveOwner::dGet
doublereal dGet(void) const
Definition: drive.cc:671
Aerodynamic2DElem< 3 >::OUTA
std::vector< outa_t > OUTA
Definition: aeroelem.h:164
AeroData::GetForces
virtual int GetForces(int i, const doublereal *W, doublereal *TNG, outa_t &OUTA)
Definition: aerodata.cc:377
Aerodynamic2DElem< 3 >::Chord
const ShapeOwner Chord
Definition: aeroelem.h:157
Aerodynamic2DElem< 3 >::pIndVel
InducedVelocity * pIndVel
Definition: aeroelem.h:154
ER_Rot::Param
Param_Manip Param
Definition: Rot.cc:291
ShapeFunc3N
doublereal ShapeFunc3N(doublereal d, integer iNode, enum Order Ord)
Definition: shapefnc.cc:173
Elem::GetElemType
virtual Elem::Type GetElemType(void) const =0
AerodynamicBeam::Ra2
const Mat3x3 Ra2
Definition: aeroelem.h:356
VectorHandler::iGetSize
virtual integer iGetSize(void) const =0
Aerodynamic2DElem< 3 >::Twist
const ShapeOwner Twist
Definition: aeroelem.h:160
Aerodynamic2DElem< 3 >::aerodata
AeroData * aerodata
Definition: aeroelem.h:153
Aerodynamic2DElem< 3 >::TipLoss
const ShapeOwner TipLoss
Definition: aeroelem.h:161
AeroData::SetAirData
virtual void SetAirData(const doublereal &rho, const doublereal &c)
Definition: aerodata.cc:214
SubVectorHandler::PutRowIndex
virtual void PutRowIndex(integer iSubRow, integer iRow)=0
PntWght::dGetWght
doublereal dGetWght(void) const
Definition: gauss.h:56
dN2
const doublereal dN2[2]
Definition: shapefnc.cc:52
AerodynamicBeam::pNode
const StructNode * pNode[3]
Definition: aeroelem.h:350
Aerodynamic2DElem< 3 >::ForcePoint
const ShapeOwner ForcePoint
Definition: aeroelem.h:158
dN3
const doublereal dN3[2][3]
Definition: shapefnc.cc:157
Vec3::Reset
void Reset(void)
Definition: matvec3.cc:109
pdsf3
static const doublereal pdsf3[]
Definition: aeroelem.cc:1558
Vec3::PutTo
void PutTo(doublereal *pd) const
Definition: matvec3.h:339
InducedVelocity::GetInducedVelocity
virtual Vec3 GetInducedVelocity(Elem::Type type, unsigned uLabel, unsigned uPnt, const Vec3 &X) const =0
Aerodynamic2DElem< 3 >::GDI
GaussDataIterator GDI
Definition: aeroelem.h:163
ShapeOwner::dGet
virtual doublereal dGet(doublereal d) const
Definition: shape.cc:60
AerodynamicBeam::f2
const Vec3 f2
Definition: aeroelem.h:353
AerodynamicBeam::f1
const Vec3 f1
Definition: aeroelem.h:352
Rotor::dGetOmega
virtual doublereal dGetOmega(void) const
Definition: rotor.h:151
grad::Cross
VectorExpression< VectorCrossExpr< VectorLhsExpr, VectorRhsExpr >, 3 > Cross(const VectorExpression< VectorLhsExpr, 3 > &u, const VectorExpression< VectorRhsExpr, 3 > &v)
Definition: matvec.h:3248
Aerodynamic2DElem< 3 >::AddSectionalForce_int
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
StructDispNode::GetXCurr
virtual const Vec3 & GetXCurr(void) const
Definition: strnode.h:310
VectorHandler::Add
virtual void Add(integer iRow, const Vec3 &v)
Definition: vh.cc:63
Aerodynamic2DElem< 3 >::VelocityPoint
const ShapeOwner VelocityPoint
Definition: aeroelem.h:159
c
static std::stack< cleanup * > c
Definition: cleanup.cc:59
AerodynamicOutput::SetData
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)
Definition: aeroelem.cc:92
DxDcsi3N
doublereal DxDcsi3N(doublereal d, const Vec3 &X1, const Vec3 &X2, const Vec3 &X3)
Definition: shapefnc.cc:228
PntWght::dGetPnt
doublereal dGetPnt(void) const
Definition: gauss.h:55
AerodynamicBeam::f3
const Vec3 f3
Definition: aeroelem.h:354
AerodynamicBeam::F
Vec3 F[LASTNODE]
Definition: aeroelem.h:366
AirPropOwner::fGetAirVelocity
virtual flag fGetAirVelocity(Vec3 &Velocity, const Vec3 &X) const
Definition: aerodyn.cc:725
grad::cos
GradientExpression< UnaryExpr< FuncCos, Expr > > cos(const GradientExpression< Expr > &u)
Definition: gradient.h:2978
pdsi3
static const doublereal pdsi3[]
Definition: aeroelem.cc:1557
DofOwnerOwner::iGetFirstIndex
virtual integer iGetFirstIndex(void) const
Definition: dofown.h:127
doublereal
double doublereal
Definition: colamd.c:52
Aerodynamic2DElem< 3 >::AddForce_int
void AddForce_int(const StructNode *pN, const Vec3 &F, const Vec3 &M, const Vec3 &X) const
integer
long int integer
Definition: colamd.c:51
WithLabel::GetLabel
unsigned int GetLabel(void) const
Definition: withlab.cc:62
AerodynamicBeam::Ra3
const Mat3x3 Ra3
Definition: aeroelem.h:357
AeroData::AssRes
virtual void AssRes(SubVectorHandler &WorkVec, doublereal dCoef, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr, integer iFirstIndex, integer iFirstSubIndex, int i, const doublereal *W, doublereal *TNG, outa_t &OUTA)
Definition: aerodata.cc:391
Rotor
Definition: rotor.h:43
PntWght
Definition: gauss.h:50

Here is the call graph for this function:

virtual AerodynamicElem::Type AerodynamicBeam::GetAerodynamicElemType ( void  ) const
inlinevirtual

Implements AerodynamicElem.

Definition at line 424 of file aeroelem.h.

References AerodynamicElem::AERODYNAMICBEAM.

424  {
425  return AerodynamicElem::AERODYNAMICBEAM;
426  };
virtual void AerodynamicBeam::GetConnectedNodes ( std::vector< const Node * > &  connectedNodes) const
inlinevirtual

Reimplemented from Elem.

Definition at line 434 of file aeroelem.h.

References NODE1, and NODE2.

434  {
435  connectedNodes.resize(3);
436  connectedNodes[0] = pNode[NODE1];
437  connectedNodes[1] = pNode[NODE2];
438  connectedNodes[2] = pNode[NODE3];
439  };
AerodynamicBeam::pNode
const StructNode * pNode[3]
Definition: aeroelem.h:350
SubVectorHandler & AerodynamicBeam::InitialAssRes ( SubVectorHandler &  WorkVec,
const VectorHandler &  XCurr 
)
virtual

Implements SubjectToInitialAssembly.

Definition at line 1957 of file aeroelem.cc.

References AssVec(), DEBUGCOUTFNAME, StructDispNode::iGetFirstPositionIndex(), NODE1, NODE2, NODE3, pNode, SubVectorHandler::PutRowIndex(), and VectorHandler::ResizeReset().

1959 {
1960  DEBUGCOUTFNAME("AerodynamicBeam::InitialAssRes");
1961  WorkVec.ResizeReset(18);
1962 
1963  integer iNode1FirstIndex = pNode[NODE1]->iGetFirstPositionIndex();
1964  integer iNode2FirstIndex = pNode[NODE2]->iGetFirstPositionIndex();
1965  integer iNode3FirstIndex = pNode[NODE3]->iGetFirstPositionIndex();
1966  for (int iCnt = 1; iCnt <= 6; iCnt++) {
1967  WorkVec.PutRowIndex(iCnt, iNode1FirstIndex + iCnt);
1968  WorkVec.PutRowIndex(6 + iCnt, iNode2FirstIndex + iCnt);
1969  WorkVec.PutRowIndex(12 + iCnt, iNode3FirstIndex + iCnt);
1970  }
1971 
1972  AssVec(WorkVec, 1., XCurr, XCurr);
1973 
1974  return WorkVec;
1975 }
DEBUGCOUTFNAME
#define DEBUGCOUTFNAME(fname)
Definition: myassert.h:256
VectorHandler::ResizeReset
virtual void ResizeReset(integer)
Definition: vh.cc:55
SubVectorHandler::PutRowIndex
virtual void PutRowIndex(integer iSubRow, integer iRow)=0
AerodynamicBeam::AssVec
void AssVec(SubVectorHandler &WorkVec, doublereal dCoef, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr)
Definition: aeroelem.cc:1980
AerodynamicBeam::pNode
const StructNode * pNode[3]
Definition: aeroelem.h:350
StructDispNode::iGetFirstPositionIndex
virtual integer iGetFirstPositionIndex(void) const
Definition: strnode.h:452
integer
long int integer
Definition: colamd.c:51

Here is the call graph for this function:

void AerodynamicBeam::Output ( OutputHandler &  OH) const
virtual

Reimplemented from ToBeOutput.

Definition at line 2209 of file aeroelem.cc.

References AerodynamicOutput::AEROD_OUT_NODE, AerodynamicOutput::AEROD_OUT_PGAUSS, AerodynamicOutput::AEROD_OUT_STD, OutputHandler::AERODYNAMIC, OutputHandler::Aerodynamic(), ASSERT, ToBeOutput::bToBeOutput(), DEBUGCOUTFNAME, F, Aerodynamic2DElem< 3 >::GDI, WithLabel::GetLabel(), AerodynamicOutput::GetOutput(), NumIntData::iGetNum(), M, NODE1, NODE2, NODE3, Aerodynamic2DElem< 3 >::OUTA, Aerodynamic2DElem< iNN >::Output_int(), AerodynamicOutput::OutputData, pBeam, OutputHandler::UseText(), and Vec3::Write().

2210 {
2211  DEBUGCOUTFNAME("AerodynamicBeam::Output");
2212 
2213  if (bToBeOutput()) {
2214  Aerodynamic2DElem<3>::Output_int(OH);
2215 
2216  if (OH.UseText(OutputHandler::AERODYNAMIC)) {
2217  std::ostream& out = OH.Aerodynamic() << std::setw(8) << GetLabel();
2218 
2219  switch (GetOutput()) {
2220  case AEROD_OUT_NODE:
2221  out << " " << std::setw(8) << pBeam->GetLabel()
2222  << " ", F[NODE1].Write(out, " ") << " ", M[NODE1].Write(out, " ")
2223  << " ", F[NODE2].Write(out, " ") << " ", M[NODE2].Write(out, " ")
2224  << " ", F[NODE3].Write(out, " ") << " ", M[NODE3].Write(out, " ");
2225  break;
2226 
2227  case AEROD_OUT_PGAUSS:
2228  ASSERT(!OutputData.empty());
2229 
2230  for (std::vector<Aero_output>::const_iterator i = OutputData.begin();
2231  i != OutputData.end(); ++i)
2232  {
2233  out << " " << i->alpha
2234  << " " << i->f;
2235  }
2236  break;
2237 
2238  case AEROD_OUT_STD:
2239  for (int i = 0; i < 3*GDI.iGetNum(); i++) {
2240  out
2241  << " " << OUTA[i].alpha
2242  << " " << OUTA[i].gamma
2243  << " " << OUTA[i].mach
2244  << " " << OUTA[i].cl
2245  << " " << OUTA[i].cd
2246  << " " << OUTA[i].cm
2247  << " " << OUTA[i].alf1
2248  << " " << OUTA[i].alf2;
2249  }
2250  break;
2251 
2252  default:
2253  ASSERT(0);
2254  break;
2255  }
2256 
2257  out << std::endl;
2258  }
2259  }
2260 }
Vec3::Write
std::ostream & Write(std::ostream &out, const char *sFill=" ") const
Definition: matvec3.cc:738
ToBeOutput::bToBeOutput
virtual bool bToBeOutput(void) const
Definition: output.cc:890
DEBUGCOUTFNAME
#define DEBUGCOUTFNAME(fname)
Definition: myassert.h:256
AerodynamicOutput::GetOutput
AerodynamicOutput::eOutput GetOutput(void) const
Definition: aeroelem.cc:125
AerodynamicBeam::M
Vec3 M[LASTNODE]
Definition: aeroelem.h:367
Aerodynamic2DElem< 3 >::OUTA
std::vector< outa_t > OUTA
Definition: aeroelem.h:164
AerodynamicBeam::pBeam
const Beam * pBeam
Definition: aeroelem.h:349
Aerodynamic2DElem< 3 >::GDI
GaussDataIterator GDI
Definition: aeroelem.h:163
ASSERT
#define ASSERT(expression)
Definition: colamd.c:977
Aerodynamic2DElem::Output_int
void Output_int(OutputHandler &OH) const
Definition: aeroelem.cc:544
AerodynamicOutput::OutputData
std::vector< Aero_output > OutputData
Definition: aeroelem.h:107
AerodynamicBeam::F
Vec3 F[LASTNODE]
Definition: aeroelem.h:366
NumIntData::iGetNum
virtual integer iGetNum(void) const
Definition: gauss.h:96
WithLabel::GetLabel
unsigned int GetLabel(void) const
Definition: withlab.cc:62
OutputHandler::UseText
bool UseText(int out) const
Definition: output.cc:446
OutputHandler::Aerodynamic
std::ostream & Aerodynamic(void) const
Definition: output.h:485

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

Implements Elem.

Definition at line 1528 of file aeroelem.cc.

References Aerodynamic2DElem< 3 >::aerodata, Aerodynamic2DElem< 3 >::Chord, DEBUGCOUTFNAME, f1, f2, f3, Aerodynamic2DElem< 3 >::ForcePoint, Aerodynamic2DElem< 3 >::GDI, WithLabel::GetLabel(), Mat3x3::GetVec(), NumIntData::iGetNum(), pBeam, DriveOwner::pGetDriveCaller(), ShapeOwner::pGetShape(), Aerodynamic2DElem< 3 >::pIndVel, Ra1, Ra2, Ra3, Shape::Restart(), AeroData::Restart(), DriveCaller::Restart(), Aerodynamic2DElem< 3 >::Twist, Aerodynamic2DElem< 3 >::VelocityPoint, Write(), and Vec3::Write().

1529 {
1530  DEBUGCOUTFNAME("AerodynamicBeam::Restart");
1531  out << " aerodynamic beam: " << GetLabel()
1532  << ", " << pBeam->GetLabel();
1533  if (pIndVel != 0) {
1534  out << ", rotor, " << pIndVel->GetLabel();
1535  }
1536  out << ", reference, node, ", f1.Write(out, ", ")
1537  << ", reference, node, 1, ", (Ra1.GetVec(1)).Write(out, ", ")
1538  << ", 2, ", (Ra1.GetVec(2)).Write(out, ", ")
1539  << ", reference, node, ", f2.Write(out, ", ")
1540  << ", reference, node, 1, ", (Ra2.GetVec(1)).Write(out, ", ")
1541  << ", 2, ", (Ra2.GetVec(2)).Write(out, ", ")
1542  << ", reference, node, ", f3.Write(out, ", ")
1543  << ", reference, node, 1, ", (Ra3.GetVec(1)).Write(out, ", ")
1544  << ", 2, ", (Ra3.GetVec(2)).Write(out, ", ")
1545  << ", ";
1546  Chord.pGetShape()->Restart(out) << ", ";
1547  ForcePoint.pGetShape()->Restart(out) << ", ";
1548  VelocityPoint.pGetShape()->Restart(out) << ", ";
1549  Twist.pGetShape()->Restart(out) << ", "
1550  << GDI.iGetNum() << ", control, ";
1551  pGetDriveCaller()->Restart(out) << ", ";
1552  aerodata->Restart(out);
1553  return out << ";" << std::endl;
1554 }
Vec3::Write
std::ostream & Write(std::ostream &out, const char *sFill=" ") const
Definition: matvec3.cc:738
AerodynamicBeam::Ra1
const Mat3x3 Ra1
Definition: aeroelem.h:355
DEBUGCOUTFNAME
#define DEBUGCOUTFNAME(fname)
Definition: myassert.h:256
Shape::Restart
virtual std::ostream & Restart(std::ostream &out) const =0
Write
std::ostream & Write(std::ostream &out, const FullMatrixHandler &m, const char *s, const char *s2)
Definition: fullmh.cc:376
Aerodynamic2DElem< 3 >::Chord
const ShapeOwner Chord
Definition: aeroelem.h:157
Aerodynamic2DElem< 3 >::pIndVel
InducedVelocity * pIndVel
Definition: aeroelem.h:154
ShapeOwner::pGetShape
virtual const Shape * pGetShape(void) const
Definition: shape.cc:72
AerodynamicBeam::Ra2
const Mat3x3 Ra2
Definition: aeroelem.h:356
AerodynamicBeam::pBeam
const Beam * pBeam
Definition: aeroelem.h:349
Mat3x3::GetVec
Vec3 GetVec(unsigned short int i) const
Definition: matvec3.h:893
Aerodynamic2DElem< 3 >::Twist
const ShapeOwner Twist
Definition: aeroelem.h:160
Aerodynamic2DElem< 3 >::aerodata
AeroData * aerodata
Definition: aeroelem.h:153
DriveCaller::Restart
virtual std::ostream & Restart(std::ostream &out) const =0
AeroData::Restart
virtual std::ostream & Restart(std::ostream &out) const =0
Aerodynamic2DElem< 3 >::ForcePoint
const ShapeOwner ForcePoint
Definition: aeroelem.h:158
Aerodynamic2DElem< 3 >::GDI
GaussDataIterator GDI
Definition: aeroelem.h:163
AerodynamicBeam::f2
const Vec3 f2
Definition: aeroelem.h:353
AerodynamicBeam::f1
const Vec3 f1
Definition: aeroelem.h:352
DriveOwner::pGetDriveCaller
DriveCaller * pGetDriveCaller(void) const
Definition: drive.cc:658
Aerodynamic2DElem< 3 >::VelocityPoint
const ShapeOwner VelocityPoint
Definition: aeroelem.h:159
AerodynamicBeam::f3
const Vec3 f3
Definition: aeroelem.h:354
NumIntData::iGetNum
virtual integer iGetNum(void) const
Definition: gauss.h:96
WithLabel::GetLabel
unsigned int GetLabel(void) const
Definition: withlab.cc:62
AerodynamicBeam::Ra3
const Mat3x3 Ra3
Definition: aeroelem.h:357

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Member Data Documentation

Vec3 AerodynamicBeam::F[LASTNODE]
protected

Definition at line 366 of file aeroelem.h.

Referenced by AssVec(), and Output().

const Vec3 AerodynamicBeam::f1
protected

Definition at line 352 of file aeroelem.h.

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

const Vec3 AerodynamicBeam::f2
protected

Definition at line 353 of file aeroelem.h.

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

const Vec3 AerodynamicBeam::f3
protected

Definition at line 354 of file aeroelem.h.

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

Vec3 AerodynamicBeam::M[LASTNODE]
protected

Definition at line 367 of file aeroelem.h.

Referenced by AssVec(), and Output().

const Beam* AerodynamicBeam::pBeam
protected

Definition at line 349 of file aeroelem.h.

Referenced by AerodynamicBeam(), Output(), and Restart().

const StructNode* AerodynamicBeam::pNode[3]
protected

Definition at line 350 of file aeroelem.h.

Referenced by AerodynamicBeam(), AssJac(), AssRes(), AssVec(), and InitialAssRes().

const Mat3x3 AerodynamicBeam::Ra1
protected

Definition at line 355 of file aeroelem.h.

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

const Vec3 AerodynamicBeam::Ra1_3
protected

Definition at line 358 of file aeroelem.h.

const Mat3x3 AerodynamicBeam::Ra2
protected

Definition at line 356 of file aeroelem.h.

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

const Vec3 AerodynamicBeam::Ra2_3
protected

Definition at line 359 of file aeroelem.h.

const Mat3x3 AerodynamicBeam::Ra3
protected

Definition at line 357 of file aeroelem.h.

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

const Vec3 AerodynamicBeam::Ra3_3
protected

Definition at line 360 of file aeroelem.h.

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