/** {@inheritDoc} */
public double getParameter(final String name) throws IllegalArgumentException {
complainIfNotSupported(name);
if (name.equals(RadiationSensitive.ABSORPTION_COEFFICIENT)) {
return spacecraft.getAbsorptionCoefficient();
}
return spacecraft.getReflectionCoefficient();
}
/** {@inheritDoc} */
public void setParameter(final String name, final double value) throws IllegalArgumentException {
complainIfNotSupported(name);
if (name.equals(RadiationSensitive.ABSORPTION_COEFFICIENT)) {
spacecraft.setAbsorptionCoefficient(value);
} else {
spacecraft.setReflectionCoefficient(value);
}
}
/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> accelerationDerivatives(
final SpacecraftState s, final String paramName) throws OrekitException {
complainIfNotSupported(paramName);
final AbsoluteDate date = s.getDate();
final Frame frame = s.getFrame();
final Vector3D position = s.getPVCoordinates().getPosition();
final Vector3D sunSatVector =
position.subtract(sun.getPVCoordinates(date, frame).getPosition());
final double r2 = sunSatVector.getNormSq();
// compute flux
final double rawP = kRef * getLightningRatio(position, frame, date) / r2;
final Vector3D flux = new Vector3D(rawP / FastMath.sqrt(r2), sunSatVector);
return spacecraft.radiationPressureAcceleration(
date, frame, position, s.getAttitude().getRotation(), s.getMass(), flux, paramName);
}
/** {@inheritDoc} */
public void addContribution(final SpacecraftState s, final TimeDerivativesEquations adder)
throws OrekitException {
final AbsoluteDate date = s.getDate();
final Frame frame = s.getFrame();
final Vector3D position = s.getPVCoordinates().getPosition();
final Vector3D sunSatVector =
position.subtract(sun.getPVCoordinates(date, frame).getPosition());
final double r2 = sunSatVector.getNormSq();
// compute flux
final double rawP = kRef * getLightningRatio(position, frame, date) / r2;
final Vector3D flux = new Vector3D(rawP / FastMath.sqrt(r2), sunSatVector);
final Vector3D acceleration =
spacecraft.radiationPressureAcceleration(
date, frame, position, s.getAttitude().getRotation(), s.getMass(), flux);
// provide the perturbing acceleration to the derivatives adder
adder.addAcceleration(acceleration, s.getFrame());
}
/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> accelerationDerivatives(
final AbsoluteDate date,
final Frame frame,
final FieldVector3D<DerivativeStructure> position,
final FieldVector3D<DerivativeStructure> velocity,
final FieldRotation<DerivativeStructure> rotation,
final DerivativeStructure mass)
throws OrekitException {
final FieldVector3D<DerivativeStructure> sunSatVector =
position.subtract(sun.getPVCoordinates(date, frame).getPosition());
final DerivativeStructure r2 = sunSatVector.getNormSq();
// compute flux
final double ratio = getLightningRatio(position.toVector3D(), frame, date);
final DerivativeStructure rawP = r2.reciprocal().multiply(kRef * ratio);
final FieldVector3D<DerivativeStructure> flux =
new FieldVector3D<DerivativeStructure>(rawP.divide(r2.sqrt()), sunSatVector);
// compute acceleration with all its partial derivatives
return spacecraft.radiationPressureAcceleration(date, frame, position, rotation, mass, flux);
}
