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java.lang.Object org.orekit.orbits.Orbit org.orekit.orbits.KeplerianOrbit
public final class KeplerianOrbit
This class handles traditional keplerian orbital parameters.
The parameters used internally are the keplerian elements (see KeplerianParameters
for more information.
The instance KeplerianOrbit
is guaranteed to be immutable.
Orbit
,
CircularOrbit
,
CartesianOrbit
,
EquinoctialOrbit
,
Serialized FormField Summary | |
---|---|
static int |
ECCENTRIC_ANOMALY
Deprecated. as of 6.0 replaced by PositionAngle |
static int |
MEAN_ANOMALY
Deprecated. as of 6.0 replaced by PositionAngle |
static int |
TRUE_ANOMALY
Deprecated. as of 6.0 replaced by PositionAngle |
Constructor Summary | |
---|---|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
int type,
Frame frame,
AbsoluteDate date,
double mu)
Deprecated. as of 6.0 replaced by KeplerianOrbit(double, double, double,
double, double, double, PositionAngle, Frame, AbsoluteDate, double) |
|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance. |
|
KeplerianOrbit(IOrbitalParameters parameters,
Frame frame,
AbsoluteDate date)
Creates a new instance. |
|
KeplerianOrbit(Orbit op)
Constructor from any kind of orbital parameters. |
|
KeplerianOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters. |
Method Summary | |
---|---|
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. |
double |
getA()
Get the semi-major axis. |
double |
getAnomaly(PositionAngle type)
Get the anomaly. |
double |
getE()
Get the eccentricity. |
double |
getEccentricAnomaly()
Get the eccentric anomaly. |
double |
getEquinoctialEx()
Get the first component of the eccentricity vector. |
double |
getEquinoctialEy()
Get the second component of the eccentricity vector. |
double |
getHx()
Get the first component of the inclination vector. |
double |
getHy()
Get the second component of the inclination vector. |
double |
getI()
Get the inclination. |
KeplerianParameters |
getKeplerianParameters()
Getter for underlying keplerian parameters. |
double |
getLE()
Get the eccentric latitude argument. |
double |
getLM()
Get the mean latitude argument. |
double |
getLv()
Get the true latitude argument. |
double |
getMeanAnomaly()
Get the mean anomaly. |
IOrbitalParameters |
getParameters()
Get underlying orbital parameters. |
double |
getPerigeeArgument()
Get the perigee argument. |
double |
getRightAscensionOfAscendingNode()
Get the right ascension of the ascending node. |
double |
getTrueAnomaly()
Get the true anomaly. |
OrbitType |
getType()
Get the orbit type. |
protected PVCoordinates |
initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters. |
KeplerianOrbit |
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 |
protected KeplerianOrbit |
orbitShiftedBy(double dt)
Get a time-shifted orbit. |
String |
toString()
Returns a string representation of this keplerian parameters object. |
Methods inherited from class java.lang.Object |
---|
clone, equals, finalize, getClass, hashCode, notify, notifyAll, wait, wait, wait |
Field Detail |
---|
@Deprecated public static final int MEAN_ANOMALY
PositionAngle
@Deprecated public static final int ECCENTRIC_ANOMALY
PositionAngle
@Deprecated public static final int TRUE_ANOMALY
PositionAngle
Constructor Detail |
---|
public KeplerianOrbit(IOrbitalParameters parameters, Frame frame, AbsoluteDate date)
parameters
- orbital parametersframe
- the frame in which the parameters are defineddate
- date of the orbital parameterspublic KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngle type, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
a
- semi-major axis (m), negative for hyperbolic orbitse
- eccentricity (e >= 0)i
- inclination (rad)pa
- perigee argument (ω, rad)raan
- right ascension of ascending node (Ω, rad)anomaly
- mean, eccentric or true anomaly (rad)type
- type of anomalyframe
- the frame in which the parameters are defineddate
- date of the orbital parametersmu
- central attraction coefficient (m3/s2)
IllegalArgumentException
- if a and e don't match for hyperbolic orbits,
or v is out of range for hyperbolic orbits@Deprecated public KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, int type, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
KeplerianOrbit(double, double, double,
double, double, double, PositionAngle, Frame, AbsoluteDate, double)
a
- semi-major axis (m), negative for hyperbolic orbitse
- eccentricityi
- inclination (rad)pa
- perigee argument (ω, rad)raan
- right ascension of ascending node (Ω, rad)anomaly
- mean, eccentric or true anomaly (rad)type
- type of anomaly, must be one of MEAN_ANOMALY
,
ECCENTRIC_ANOMALY
or TRUE_ANOMALY
frame
- the frame in which the parameters are defineddate
- date of the orbital parametersmu
- central attraction coefficient (m3/s2)
IllegalArgumentException
- if the longitude argument type is not
one of MEAN_ANOMALY
, ECCENTRIC_ANOMALY
IllegalArgumentException
- if a and e don't match for hyperbolic orbits,
or v is out of range for hyperbolic orbitsMEAN_ANOMALY
,
ECCENTRIC_ANOMALY
,
TRUE_ANOMALY
public KeplerianOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
pvCoordinates
- the PVCoordinates of the satelliteframe
- the frame in which are defined the PVCoordinates
date
- date of the orbital parametersmu
- central attraction coefficient (m3/s2)public KeplerianOrbit(Orbit op)
op
- orbital parameters to copyMethod Detail |
---|
public IOrbitalParameters getParameters()
getParameters
in class Orbit
public KeplerianParameters getKeplerianParameters()
public OrbitType getType()
getType
in class Orbit
public double getA()
getA
in class Orbit
public double getE()
getE
in class Orbit
public double getI()
getI
in class Orbit
public double getPerigeeArgument()
public double getRightAscensionOfAscendingNode()
public double getAnomaly(PositionAngle type)
type
- type of the angle
public double getTrueAnomaly()
public double getEccentricAnomaly()
public double getMeanAnomaly()
public double getEquinoctialEx()
getEquinoctialEx
in class Orbit
public double getEquinoctialEy()
getEquinoctialEy
in class Orbit
public double getHx()
getHx
in class Orbit
public double getHy()
getHy
in class Orbit
public double getLv()
getLv
in class Orbit
public double getLE()
getLE
in class Orbit
public double getLM()
getLM
in class Orbit
protected PVCoordinates initPVCoordinates()
initPVCoordinates
in class Orbit
protected KeplerianOrbit 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 seconds
public KeplerianOrbit 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 on Keplerian elements, without derivatives (which means the interpolation falls back to Lagrange interpolation only).
date
- interpolation datesample
- sample points on which interpolation should be done
protected 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 String toString()
toString
in class Object
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