本文整理汇总了C++中Vector6d::segment方法的典型用法代码示例。如果您正苦于以下问题：C++ Vector6d::segment方法的具体用法？C++ Vector6d::segment怎么用？C++ Vector6d::segment使用的例子？那么恭喜您, 这里精选的方法代码示例或许可以为您提供帮助。您也可以进一步了解该方法所在类Vector6d的用法示例。
在下文中一共展示了Vector6d::segment方法的2个代码示例，这些例子默认根据受欢迎程度排序。您可以为喜欢或者感觉有用的代码点赞，您的评价将有助于系统推荐出更棒的C++代码示例。
示例1: mapCartesian
/*!
* This function is implemented in order to not use any external
* mapping functions. The function was build completely from pieces of
* code of the old cartesianStateDerivativeModel in order to use
* completely different, but also verified methods of constructing a
* stateDerivative from the total accelerations.
* \param currentState The current state.
* \param accelerations Total sum of accelerations.
* \return stateDerivative
*/
Vector6d mapCartesian( const Vector6d& cartesianState, const Eigen::Vector3d& acceleration )
{
// {{{ Snippets from cartesianStateDerivativeModel.h
typedef Vector6d CartesianStateDerivativeType;
// Declare Cartesian state derivative size.
unsigned int stateDerivativeSize = cartesianState.rows( );
// Declare Cartesian state derivative of the same size as Cartesian state.
CartesianStateDerivativeType cartesianStateDerivative
= CartesianStateDerivativeType::Zero( stateDerivativeSize );
// Set derivative of position components to current Cartesian velocity.
cartesianStateDerivative.segment( 0, stateDerivativeSize / 2 )
= cartesianState.segment( stateDerivativeSize / 2, stateDerivativeSize / 2 );
// Add transformed acceleration to state derivative.
cartesianStateDerivative.segment( stateDerivativeSize / 2, stateDerivativeSize / 2 )
+= acceleration;
// Return assembled state derivative.
return cartesianStateDerivative;
// }}} End Snippets from cartesianStateDerivativeModel.h
}示例2: determinePartCoefficients
//! Determine aerodynamic coefficients of a single vehicle part.
Vector6d HypersonicLocalInclinationAnalysis::determinePartCoefficients(
const int partNumber, const boost::array< int, 3 > independentVariableIndices )
{
// Declare and determine angles of attack and sideslip for analysis.
double angleOfAttack = dataPointsOfIndependentVariables_[ 1 ]
[ independentVariableIndices[ 1 ] ];
double angleOfSideslip = dataPointsOfIndependentVariables_[ 2 ]
[ independentVariableIndices[ 2 ] ];
// Declare partCoefficient vector.
Vector6d partCoefficients = Vector6d::Zero( );
// Check whether the inclinations of the vehicle part have already been computed.
if ( previouslyComputedInclinations_.count( std::pair< double, double >(
angleOfAttack, angleOfSideslip ) ) == 0 )
{
// Determine panel inclinations for part.
determineInclinations( angleOfAttack, angleOfSideslip );
// Add panel inclinations to container
previouslyComputedInclinations_[ std::pair< double, double >(
angleOfAttack, angleOfSideslip ) ] = inclination_;
}
else
{
// Fetch inclinations from container
inclination_ = previouslyComputedInclinations_[ std::pair< double, double >(
angleOfAttack, angleOfSideslip ) ];
}
// Set pressureCoefficient_ array for given independent variables.
determinePressureCoefficients( partNumber, independentVariableIndices );
// Calculate force coefficients from pressure coefficients.
partCoefficients.segment( 0, 3 ) = calculateForceCoefficients( partNumber );
// Calculate moment coefficients from pressure coefficients.
partCoefficients.segment( 3, 3 ) = calculateMomentCoefficients( partNumber );
return partCoefficients;
}