public bool QueryDerivatives(IAgFlightBasicManeuverState pCurrentState, IAgFlightBasicManeuverDerivs presultCurrentDerivs, bool vbAllowThresholdDetection)
{
// the strategy extrapolates the starting flight condition ...
// model the effects of coriolis without compensating for it ...
presultCurrentDerivs.SetVertPlaneCompensateForCoriolisAccel(false);
presultCurrentDerivs.SetHorizPlaneCompensateForCoriolisAccel(false);
// totalECFAccel = pitchRateNormalAccel + speedDotLongAccel + coriolisAccel - centripetalAccel
pCurrentState.QueryECFCoriolisAccel(m_coriolisAccel);
pCurrentState.QueryECFCentripetalAccel(m_centripetalAccel);
m_accelCommand.SetToZero(); // pitchRateNormalAccel = speedDotLongAccel = 0
m_accelCommand.Add(m_coriolisAccel);
m_accelCommand.Subtract(m_centripetalAccel);
presultCurrentDerivs.SetEcfAccelCommand(m_accelCommand);
// compute ref axes PQRs
pCurrentState.QueryECFToRefAxesAttRefFrame(m_ecfToRefAxesQuat, null);
pCurrentState.QueryOmegaEarthInFrame(m_ecfToRefAxesQuat, m_earthOmegaInRefAxes);
double dCommandFPADot = 0.0;
m_PQR.ConstructFromComponents(0.0, dCommandFPADot, 0.0);
m_PQR.Add(m_earthOmegaInRefAxes);
presultCurrentDerivs.SetRefAxesOmegaCommand(m_PQR);
// Tgo is used for calc progress and to refine stopping condition
presultCurrentDerivs.NavTimeToGo = 1.0;
presultCurrentDerivs.ProfileTimeToGo = 1.0;
return(true);
}
public bool QueryDerivatives(IAgFlightBasicManeuverState pCurrentState, IAgFlightBasicManeuverDerivs presultCurrentDerivs, bool vbAllowThresholdDetection)
{
// nothing to do for this example, all the action gets done in the Nav strategy
return(true);
}
