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java.lang.Object org.orekit.orbits.Orbit org.orekit.orbits.CircularOrbit
public final class CircularOrbit
This class handles circular orbital parameters.
The parameters used internally are the circular elements (see CircularParameters
for more information.
The instance CircularOrbit
is guaranteed to be immutable.
Orbit
,
KeplerianOrbit
,
CartesianOrbit
,
EquinoctialOrbit
,
Serialized FormField Summary | |
---|---|
static int |
ECCENTRIC_LONGITUDE_ARGUMENT
Deprecated. as of 6.0 replaced by PositionAngle |
static int |
MEAN_LONGITUDE_ARGUMENT
Deprecated. as of 6.0 replaced by PositionAngle |
static int |
TRUE_LONGITUDE_ARGUMENT
Deprecated. as of 6.0 replaced by PositionAngle |
Constructor Summary | |
---|---|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
int type,
Frame frame,
AbsoluteDate date,
double mu)
Deprecated. as of 6.0 replaced by CircularOrbit(double, double, double,
double, double, double, PositionAngle, Frame, AbsoluteDate, double) |
|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance. |
|
CircularOrbit(IOrbitalParameters parameters,
Frame frame,
AbsoluteDate date)
Creates a new instance. |
|
CircularOrbit(Orbit op)
Constructor from any kind of orbital parameters. |
|
CircularOrbit(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 |
getAlpha(PositionAngle type)
Get the latitude argument. |
double |
getAlphaE()
Get the eccentric latitude argument. |
double |
getAlphaM()
Get the mean latitude argument. |
double |
getAlphaV()
Get the true latitude argument. |
double |
getCircularEx()
Get the first component of the circular eccentricity vector. |
double |
getCircularEy()
Get the second component of the circular eccentricity vector. |
CircularParameters |
getCircularParameters()
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 the first component of the inclination vector. |
double |
getHy()
Get the second component of the inclination vector. |
double |
getI()
Get the inclination. |
double |
getLE()
Get the eccentric latitude argument. |
double |
getLM()
Get the mean latitude argument. |
double |
getLv()
Get the true latitude argument. |
IOrbitalParameters |
getParameters()
Get underlying orbital parameters. |
double |
getRightAscensionOfAscendingNode()
Get the right ascension of the ascending node. |
OrbitType |
getType()
Get the orbit type. |
protected PVCoordinates |
initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters. |
CircularOrbit |
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 CircularOrbit |
orbitShiftedBy(double dt)
Get a time-shifted orbit. |
String |
toString()
Returns a string representation of this Orbit 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_LONGITUDE_ARGUMENT
PositionAngle
@Deprecated public static final int ECCENTRIC_LONGITUDE_ARGUMENT
PositionAngle
@Deprecated public static final int TRUE_LONGITUDE_ARGUMENT
PositionAngle
Constructor Detail |
---|
public CircularOrbit(IOrbitalParameters parameters, Frame frame, AbsoluteDate date)
parameters
- orbital parametersframe
- the frame in which the parameters are defined
(must be a pseudo-inertial frame
)date
- date of the orbital parameterspublic CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngle type, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
a
- semi-major axis (m)ex
- e cos(ω), first component of circular eccentricity vectorey
- e sin(ω), second component of circular eccentricity vectori
- inclination (rad)raan
- right ascension of ascending node (Ω, rad)alpha
- an + ω, mean, eccentric or true latitude argument (rad)type
- type of latitude argumentframe
- the frame in which are defined the parametersdate
- date of the orbital parametersmu
- central attraction coefficient (m3/s2)
IllegalArgumentException
- if eccentricity is equal to 1 or larger@Deprecated public CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, int type, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
CircularOrbit(double, double, double,
double, double, double, PositionAngle, Frame, AbsoluteDate, double)
a
- semi-major axis (m)ex
- e cos(ω), first component of circular eccentricity vectorey
- e sin(ω), second component of circular eccentricity vectori
- inclination (rad)raan
- right ascension of ascending node (Ω, rad)alpha
- an + ω, mean, eccentric or true latitude argument (rad)type
- type of latitude argument, must be one of MEAN_LONGITUDE_ARGUMENT
,
ECCENTRIC_LONGITUDE_ARGUMENT
or TRUE_LONGITUDE_ARGUMENT
frame
- the frame in which are defined the parametersdate
- date of the orbital parametersmu
- central attraction coefficient (m3/s2)
IllegalArgumentException
- if the latitude argument type is not
one of MEAN_LONGITUDE_ARGUMENT
, ECCENTRIC_LONGITUDE_ARGUMENT
or TRUE_LONGITUDE_ARGUMENT
IllegalArgumentException
- if eccentricity is equal to 1 or largerMEAN_LONGITUDE_ARGUMENT
,
ECCENTRIC_LONGITUDE_ARGUMENT
,
TRUE_LONGITUDE_ARGUMENT
public CircularOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
pvCoordinates
- the PVCoordinates
in inertial frameframe
- the frame in which are defined the PVCoordinates
date
- date of the orbital parametersmu
- central attraction coefficient (m3/s2)public CircularOrbit(Orbit op)
op
- orbital parameters to copyMethod Detail |
---|
public IOrbitalParameters getParameters()
getParameters
in class Orbit
public CircularParameters getCircularParameters()
public OrbitType getType()
getType
in class Orbit
public double getA()
getA
in class Orbit
public double getEquinoctialEx()
getEquinoctialEx
in class Orbit
public double getEquinoctialEy()
getEquinoctialEy
in class Orbit
public double getCircularEx()
public double getCircularEy()
public double getHx()
getHx
in class Orbit
public double getHy()
getHy
in class Orbit
public double getAlphaV()
public double getAlpha(PositionAngle type)
type
- type of the angle
public double getAlphaE()
public double getAlphaM()
public double getE()
getE
in class Orbit
public double getI()
getI
in class Orbit
public double getRightAscensionOfAscendingNode()
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 CircularOrbit 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 CircularOrbit 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 circular 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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