public final class CartesianOrbit extends Orbit
The parameters used internally are the cartesian elements (see CartesianParameters
for more information.
The instance CartesianOrbit
is guaranteed to be immutable.
Orbit
,
KeplerianOrbit
,
CircularOrbit
,
EquinoctialOrbit
,
Serialized FormConstructor and Description |
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CartesianOrbit(IOrbitalParameters parametersIn,
Frame frame,
AbsoluteDate date)
Creates a new instance.
|
CartesianOrbit(Orbit op)
Constructor from any kind of orbital parameters.
|
CartesianOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
Modifier and Type | Method and Description |
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protected double[][] |
computeJacobianEccentricWrtCartesian()
Compute the Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian parameters.
|
protected double[][] |
computeJacobianMeanWrtCartesian()
Compute the Jacobian of the orbital parameters with mean angle with respect to the Cartesian parameters.
|
protected double[][] |
computeJacobianTrueWrtCartesian()
Compute the Jacobian of the orbital parameters with true angle with respect to the Cartesian parameters.
|
boolean |
equals(Object object)
Test for the equality of two orbits.
|
double |
getA()
Get the semi-major axis.
|
CartesianParameters |
getCartesianParameters()
Getter for underlying circular parameters.
|
double |
getE()
Get the eccentricity.
|
double |
getEquinoctialEx()
Get the first component of the equinoctial eccentricity vector.
|
double |
getEquinoctialEy()
Get the second component of the equinoctial eccentricity vector.
|
double |
getHx()
Get hx = ix / (2 * cos(i/2)), where ix is the first component of the inclination vector.
|
double |
getHy()
Get hy = iy / (2 * cos(i/2)), where iy is the second component of the inclination vector.
|
double |
getI()
Get the inclination.
|
double |
getLE()
Get the eccentric longitude argument.
|
double |
getLM()
Get the mean longitude argument.
|
double |
getLv()
Get the true longitude argument.
|
double |
getN()
Get the mean motion.
|
IOrbitalParameters |
getParameters()
Get underlying orbital parameters.
|
OrbitType |
getType()
Get the orbit type.
|
int |
hashCode()
Get a hashCode for the orbit.
|
protected PVCoordinates |
initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters.
|
CartesianOrbit |
interpolate(AbsoluteDate date,
Collection<Orbit> sample)
Get an interpolated instance.
|
protected void |
orbitAddKeplerContribution(PositionAngle type,
double gm,
double[] pDot)
Add the contribution of the Keplerian motion to parameters derivatives
This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the
orbital state.
|
protected CartesianOrbit |
orbitShiftedBy(double dt)
Get a time-shifted orbit.
|
String |
toString() |
addKeplerContribution, createInverseJacobian, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, getDate, getFrame, getJacobian, getJacobian, getJacobianWrtCartesian, getJacobianWrtParameters, getJacobianWrtParametersEccentric, getJacobianWrtParametersMean, getJacobianWrtParametersTrue, getKeplerianMeanMotion, getKeplerianPeriod, getKeplerianTransitionMatrix, getMu, getPVCoordinates, getPVCoordinates, getPVCoordinates, isPositiveDefinite, setJacobianWrtParametersEccentric, setJacobianWrtParametersMean, setJacobianWrtParametersTrue, shiftedBy
public CartesianOrbit(IOrbitalParameters parametersIn, Frame frame, AbsoluteDate date)
parametersIn
- orbital parametersframe
- the frame in which the parameters are defineddate
- date of the orbital parameterspublic CartesianOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
pvCoordinates
- the position and velocity of the satellite.frame
- the frame in which the PVCoordinates
are defineddate
- date of the orbital parametersmu
- central attraction coefficient (m3/s2)public CartesianOrbit(Orbit op)
op
- orbital parameters to copypublic IOrbitalParameters getParameters()
getParameters
in class Orbit
public CartesianParameters getCartesianParameters()
public OrbitType getType()
public double getA()
Note that the semi-major axis is considered negative for hyperbolic orbits.
public double getE()
public double getI()
public double getEquinoctialEx()
getEquinoctialEx
in class Orbit
public double getEquinoctialEy()
getEquinoctialEy
in class Orbit
public double getHx()
public double getHy()
public double getLv()
public double getLE()
public double getLM()
public double getN()
protected PVCoordinates initPVCoordinates()
initPVCoordinates
in class Orbit
protected CartesianOrbit orbitShiftedBy(double dt)
The orbit can be slightly shifted to close dates. This shift is based on a simple keplerian model. It is not intended as a replacement for proper orbit and attitude propagation but should be sufficient for small time shifts or coarse accuracy.
orbitShiftedBy
in class Orbit
dt
- time shift in secondspublic CartesianOrbit interpolate(AbsoluteDate date, Collection<Orbit> sample)
Note that the state of the current instance may not be used in the interpolation process, only its type and non interpolable fields are used (for example central attraction coefficient or frame when interpolating orbits). The interpolable fields taken into account are taken only from the states of the sample points. So if the state of the instance must be used, the instance should be included in the sample points.
The interpolated instance is created by polynomial Hermite interpolation ensuring velocity remains the exact derivative of position.
date
- interpolation datesample
- sample points on which interpolation should be doneprotected double[][] computeJacobianMeanWrtCartesian()
Element jacobian[i][j]
is the derivative of parameter i of the orbit with respect to Cartesian coordinate
j. This means each row correspond to one orbital parameter whereas columns 0 to 5 correspond to the Cartesian
coordinates x, y, z, xDot, yDot and zDot.
computeJacobianMeanWrtCartesian
in class Orbit
Orbit.computeJacobianEccentricWrtCartesian()
,
Orbit.computeJacobianTrueWrtCartesian()
protected double[][] computeJacobianEccentricWrtCartesian()
Element jacobian[i][j]
is the derivative of parameter i of the orbit with respect to Cartesian coordinate
j. This means each row correspond to one orbital parameter whereas columns 0 to 5 correspond to the Cartesian
coordinates x, y, z, xDot, yDot and zDot.
computeJacobianEccentricWrtCartesian
in class Orbit
Orbit.computeJacobianMeanWrtCartesian()
,
Orbit.computeJacobianTrueWrtCartesian()
protected double[][] computeJacobianTrueWrtCartesian()
Element jacobian[i][j]
is the derivative of parameter i of the orbit with respect to Cartesian coordinate
j. This means each row correspond to one orbital parameter whereas columns 0 to 5 correspond to the Cartesian
coordinates x, y, z, xDot, yDot and zDot.
computeJacobianTrueWrtCartesian
in class Orbit
Orbit.computeJacobianMeanWrtCartesian()
,
Orbit.computeJacobianEccentricWrtCartesian()
protected void orbitAddKeplerContribution(PositionAngle type, double gm, double[] pDot)
This method is used by numerical propagators to evaluate the part of Keplerrian motion to evolution of the orbital state.
orbitAddKeplerContribution
in class Orbit
type
- type of the position angle in the stategm
- attraction coefficient to usepDot
- array containing orbital state derivatives to update (the Keplerian
part must be added to the array components, as the array may already
contain some non-zero elements corresponding to non-Keplerian parts)public boolean equals(Object object)
Orbits are considered equals if they have the same type and all their attributes are equals. In particular, the orbits frame are considered equals if they represent the same instance. If they have the same attributes but are not the same instance, the method will return false.
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