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java.lang.Object org.orekit.orbits.Orbit org.orekit.orbits.EquinoctialOrbit
public final class EquinoctialOrbit
This class handles equinoctial orbital parameters, which can support both circular and equatorial orbits.
The parameters used internally are the equinoctial elements (see EquinoctialParameters
for more information.
The instance EquinoctialOrbit
is guaranteed to be immutable.
Orbit
,
KeplerianOrbit
,
CircularOrbit
,
CartesianOrbit
,
Serialized FormField Summary | |
---|---|
static int |
ECCENTRIC_LATITUDE_ARGUMENT
Deprecated. as of 6.0 replaced by PositionAngle |
static int |
MEAN_LATITUDE_ARGUMENT
Deprecated. as of 6.0 replaced by PositionAngle |
static int |
TRUE_LATITUDE_ARGUMENT
Deprecated. as of 6.0 replaced by PositionAngle |
Constructor Summary | |
---|---|
EquinoctialOrbit(double a,
double ex,
double ey,
double hx,
double hy,
double l,
int type,
Frame frame,
AbsoluteDate date,
double mu)
Deprecated. as of 6.0 replaced by EquinoctialOrbit(double, double, double,
double, double, double, PositionAngle, Frame, AbsoluteDate, double) |
|
EquinoctialOrbit(double a,
double ex,
double ey,
double hx,
double hy,
double l,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance. |
|
EquinoctialOrbit(IOrbitalParameters parameters,
Frame frame,
AbsoluteDate date)
Creates a new instance. |
|
EquinoctialOrbit(Orbit op)
Constructor from any kind of orbital parameters. |
|
EquinoctialOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters. |
Method Summary | |
---|---|
protected double[][] |
computeJacobianCartesianWrtTrue()
Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters with true angle. |
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 |
getE()
Get the eccentricity. |
double |
getEquinoctialEx()
Get the first component of the eccentricity vector. |
double |
getEquinoctialEy()
Get the second component of the eccentricity vector. |
EquinoctialParameters |
getEquinoctialParameters()
Getter for underlying equinoctial parameters. |
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. |
void |
getJacobianWrtParameters(PositionAngle type,
double[][] jacobian)
Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters. |
double |
getL(PositionAngle type)
Get the longitude argument. |
double |
getLE()
Get the eccentric longitude argument. |
double |
getLM()
Get the mean longitude argument. |
double |
getLv()
Get the true longitude argument. |
IOrbitalParameters |
getParameters()
Get underlying orbital parameters. |
OrbitType |
getType()
Get the orbit type. |
protected PVCoordinates |
initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters. |
EquinoctialOrbit |
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 EquinoctialOrbit |
orbitShiftedBy(double dt)
Get a time-shifted orbit. |
String |
toString()
Returns a string representation of this equinoctial 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_LATITUDE_ARGUMENT
PositionAngle
@Deprecated public static final int ECCENTRIC_LATITUDE_ARGUMENT
PositionAngle
@Deprecated public static final int TRUE_LATITUDE_ARGUMENT
PositionAngle
Constructor Detail |
---|
public EquinoctialOrbit(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 EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngle type, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
a
- semi-major axis (m)ex
- e cos(ω + Ω), first component of eccentricity vectorey
- e sin(ω + Ω), second component of eccentricity vectorhx
- tan(i/2) cos(Ω), first component of inclination vectorhy
- tan(i/2) sin(Ω), second component of inclination vectorl
- (M or E or v) + ω + Ω, mean, eccentric or true longitude argument (rad)type
- type of longitude argument, must be one of MEAN_LATITUDE_ARGUMENT
,
ECCENTRIC_LATITUDE_ARGUMENT
or TRUE_LATITUDE_ARGUMENT
frame
- the frame in which the parameters are defineddate
- date of the orbital parametersmu
- central attraction coefficient (m3/s2)
IllegalArgumentException
- if eccentricity is equal to 1 or larger@Deprecated public EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, int type, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
EquinoctialOrbit(double, double, double,
double, double, double, PositionAngle, Frame, AbsoluteDate, double)
a
- semi-major axis (m)ex
- e cos(ω + Ω), first component of eccentricity vectorey
- e sin(ω + Ω), second component of eccentricity vectorhx
- tan(i/2) cos(Ω), first component of inclination vectorhy
- tan(i/2) sin(Ω), second component of inclination vectorl
- (M or E or v) + ω + Ω, mean, eccentric or true longitude argument (rad)type
- type of longitude argument, must be one of MEAN_LATITUDE_ARGUMENT
,
ECCENTRIC_LATITUDE_ARGUMENT
or TRUE_LATITUDE_ARGUMENT
frame
- the frame in which the parameters are defineddate
- date of the orbital parametersmu
- central attraction coefficient (m3/s2)
IllegalArgumentException
- if eccentricity is equal to 1 or larger or
if the longitude argument type is not one of MEAN_LATITUDE_ARGUMENT
,
ECCENTRIC_LATITUDE_ARGUMENT
or TRUE_LATITUDE_ARGUMENT
MEAN_LATITUDE_ARGUMENT
,
ECCENTRIC_LATITUDE_ARGUMENT
,
TRUE_LATITUDE_ARGUMENT
public EquinoctialOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
pvCoordinates
- the position end velocityframe
- the frame in which are defined the PVCoordinates
date
- date of the orbital parametersmu
- central attraction coefficient (m3/s2)
IllegalArgumentException
- if eccentricity is equal to 1 or largerpublic EquinoctialOrbit(Orbit op)
op
- orbital parameters to copyMethod Detail |
---|
public IOrbitalParameters getParameters()
getParameters
in class Orbit
public EquinoctialParameters getEquinoctialParameters()
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 getHx()
getHx
in class Orbit
public double getHy()
getHy
in class Orbit
public double getL(PositionAngle type)
type
- type of the angle
public double getLv()
getLv
in class Orbit
public double getLE()
getLE
in class Orbit
public double getLM()
getLM
in class Orbit
public double getE()
getE
in class Orbit
public double getI()
getI
in class Orbit
protected PVCoordinates initPVCoordinates()
initPVCoordinates
in class Orbit
protected EquinoctialOrbit 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 EquinoctialOrbit 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 equinoctial 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()
public void getJacobianWrtParameters(PositionAngle type, double[][] jacobian)
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.
getJacobianWrtParameters
in class Orbit
type
- type of the position angle to usejacobian
- placeholder 6x6 (or larger) matrix to be filled with the Jacobian, if matrix
is larger than 6x6, only the 6x6 upper left corner will be modifiedprotected double[][] computeJacobianCartesianWrtTrue()
Element jacobian[i][j]
is the derivative of Cartesian coordinate i with
respect to the parameter j of the orbit. This means each column correspond to one orbital parameter
whereas rows 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.
computeJacobianMeanWrtCartesian()
,
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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