fr.cnes.sirius.patrius.attitudes

Class AeroAttitudeLaw

java.lang.Object

fr.cnes.sirius.patrius.attitudes.AbstractAttitudeLaw

fr.cnes.sirius.patrius.attitudes.AeroAttitudeLaw

All Implemented Interfaces:

AttitudeLaw, AttitudeProvider, Serializable

public class AeroAttitudeLaw
extends AbstractAttitudeLaw

Class defining an aerodynamic attitude law by angle of attack, sideslip and velocity roll.

Since:

3.4

Version:

$Id: AeroAttitudeLaw.java 17582 2017-05-10 12:58:16Z bignon $

Author:

Emmanuel Bignon

See Also:

Serialized Form

Constructor Summary

Constructors

Constructor and Description
AeroAttitudeLaw(double angleofattack, double sideslip, double rollVel, EllipsoidBodyShape earthShape) Constructor.
AeroAttitudeLaw(double angleofattack, double sideslip, double rollVel, EllipsoidBodyShape earthShape, double dtSpin, double dtAcc) Constructor with parameterizable delta-time for spin and acceleration computation.
AeroAttitudeLaw(IParameterizableFunction angleofattack, IParameterizableFunction sideslip, IParameterizableFunction rollVel, EllipsoidBodyShape earthShape) Constructor.
AeroAttitudeLaw(IParameterizableFunction angleofattack, IParameterizableFunction sideslip, IParameterizableFunction rollVel, EllipsoidBodyShape earthShape, double dtSpin, double dtAcc) Constructor with parameterizable delta-time for spin and acceleration computation.

Method Summary

Modifier and Type	Method and Description
static double[]	aircraftToAero(double slopeVel, double azimuthVel, double yaw, double pitch, double roll) Method to compute aerodynamic frame orientation angles with respect aircraft frame.
double	getAngleOfAttack(SpacecraftState state) Getter for the angle of attack.
Attitude	getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
double	getRollVelocity(SpacecraftState state) Getter for the roll velocity.
double	getSideSlipAngle(SpacecraftState state) Getter for the side slip angle.
String	toString()

Methods inherited from class fr.cnes.sirius.patrius.attitudes.AbstractAttitudeLaw

getSpinDerivativesComputation, setSpinDerivativesComputation

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, wait, wait, wait

Methods inherited from interface fr.cnes.sirius.patrius.attitudes.AttitudeProvider

computeSpinByFD, computeSpinDerivativeByFD, getAttitude

Constructor Detail

AeroAttitudeLaw

public AeroAttitudeLaw(double angleofattack,
                       double sideslip,
                       double rollVel,
                       EllipsoidBodyShape earthShape)
                throws PatriusException

Constructor.

Parameters:

angleofattack - angle of attack in [-Pi;Pi]

sideslip - sideslip angle in ]-Pi/2; Pi/2[

rollVel - roll velocity in [-Pi;Pi]

earthShape - Earth shape

Throws:

PatriusException - if some specific error occurs

AeroAttitudeLaw

public AeroAttitudeLaw(IParameterizableFunction angleofattack,
                       IParameterizableFunction sideslip,
                       IParameterizableFunction rollVel,
                       EllipsoidBodyShape earthShape)
                throws PatriusException

Constructor.

Parameters:

angleofattack - angle of attack

sideslip - sideslip angle

rollVel - roll velocity

earthShape - Earth shape

Throws:

PatriusException - if some specific error occurs

AeroAttitudeLaw

public AeroAttitudeLaw(double angleofattack,
                       double sideslip,
                       double rollVel,
                       EllipsoidBodyShape earthShape,
                       double dtSpin,
                       double dtAcc)
                throws PatriusException

Constructor with parameterizable delta-time for spin and acceleration computation.

Parameters:

angleofattack - angle of attack

sideslip - sideslip angle

rollVel - roll velocity

earthShape - Earth shape

dtSpin - step for finite differences spin computation

dtAcc - step for finite differences spin derivative computation

Throws:

PatriusException - if some specific error occurs

AeroAttitudeLaw

public AeroAttitudeLaw(IParameterizableFunction angleofattack,
                       IParameterizableFunction sideslip,
                       IParameterizableFunction rollVel,
                       EllipsoidBodyShape earthShape,
                       double dtSpin,
                       double dtAcc)
                throws PatriusException

Constructor with parameterizable delta-time for spin and acceleration computation.

Parameters:

angleofattack - angle of attack

sideslip - sideslip angle

rollVel - roll velocity

earthShape - Earth shape

dtSpin - step for finite differences spin computation

dtAcc - step for finite differences spin derivative computation

Throws:

PatriusException - if some specific error occurs

Method Detail

getAttitude

public Attitude getAttitude(PVCoordinatesProvider pvProv,
                            AbsoluteDate date,
                            Frame frame)
                     throws PatriusException

Compute the attitude corresponding to an orbital state.

Parameters:

pvProv - local position-velocity provider around current date

date - current date

frame - reference frame from which attitude is computed

Returns:

attitude attitude on the specified date and position-velocity state

Throws:

PatriusException - if attitude cannot be computed for provided date

aircraftToAero

public static double[] aircraftToAero(double slopeVel,
                                      double azimuthVel,
                                      double yaw,
                                      double pitch,
                                      double roll)
                               throws PatriusException

Method to compute aerodynamic frame orientation angles with respect aircraft frame.

Parameters:

slopeVel - Slope velocity

azimuthVel - Azimuth velocity

yaw - Aircraft yaw

pitch - Aircraft pitch

roll - Aircraft roll

Returns:

Angle of Attack, Side slip angle, Bank angle

Throws:

PatriusException - side slip angle doesn't permit to compute bank angle

getAngleOfAttack

public double getAngleOfAttack(SpacecraftState state)

Getter for the angle of attack.

Parameters:

state - state

Returns:

the angle of attack.

getSideSlipAngle

public double getSideSlipAngle(SpacecraftState state)

Getter for the side slip angle.

Parameters:

state - state

Returns:

the side slip angle.

getRollVelocity

public double getRollVelocity(SpacecraftState state)

Getter for the roll velocity.

Parameters:

state - state

Returns:

the roll velocity.

toString

public String toString()

Overrides:

toString in class Object