- java.lang.Object
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- spice.basic.OsculatingElements
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- spice.basic.OsculatingElementsExtended
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public class OsculatingElementsExtended extends OsculatingElements
Class OsculatingElementsExtended provides methods for conversion between state vectors and osculating elements. The class also supports two-body propagation of osculating elements or state vectors.This class provides the true anomaly and, when these values are computable, the orbital semi-major axis and period.
The full set of elements is:
RP Perifocal distance. ECC Eccentricity. INC Inclination. LNODE Longitude of the ascending node. ARGP Argument of periapsis. M0 Mean anomaly at epoch. T0 Epoch. MU Gravitational parameter. NU True anomaly. A Semi-major axis. TAU Orbital period. Distance units are km. Angular units are radians. Time units are seconds.
Methods for retrieving the first eight elements shown above are inherited from the superclass
OsculatingElements
.Version 1.0.0 25-JAN-2017 (NJB)
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Constructor Summary
Constructors Constructor Description OsculatingElementsExtended(OsculatingElementsExtended elts)
Copy constructor.This constructor creates a deep copy.OsculatingElementsExtended(StateVector state, Time t, double mu)
Create osculating elements from a StateVector, a Time, and a gravitational parameter (GM).
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Method Summary
Modifier and Type Method Description double
getPeriod()
Return the orbital period.double
getSemiMajorAxis()
Return the orbital semi-major axis.double
getTrueAnomaly()
Return true anomaly.double[]
toArray()
Extract elements to an array of type double.-
Methods inherited from class spice.basic.OsculatingElements
getArgumentOfPeriapsis, getEccentricity, getEpoch, getGM, getInclination, getLongitudeOfNode, getMeanAnomaly, getPerifocalDistance, propagate, propagate
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Field Detail
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NXELTS
private static final int NXELTS
- See Also:
- Constant Field Values
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IDX_NU
private static final int IDX_NU
- See Also:
- Constant Field Values
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IDX_A
private static final int IDX_A
- See Also:
- Constant Field Values
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IDX_TAU
private static final int IDX_TAU
- See Also:
- Constant Field Values
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nu
private double nu
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a
private double a
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tau
private double tau
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Constructor Detail
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OsculatingElementsExtended
public OsculatingElementsExtended(OsculatingElementsExtended elts)
Copy constructor.This constructor creates a deep copy.- Parameters:
elts
- OsculatingElementsExtended
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OsculatingElementsExtended
public OsculatingElementsExtended(StateVector state, Time t, double mu) throws SpiceException
Create osculating elements from a StateVector, a Time, and a gravitational parameter (GM).The GM value `mu' is expressed in units of
3 2 km / sec
- Parameters:
state
- StateVectormu
- doublet
- Time- Throws:
SpiceException
- exception
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Method Detail
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toArray
public double[] toArray()
Extract elements to an array of type double.The full set of elements is:
RP Perifocal distance. ECC Eccentricity. INC Inclination. LNODE Longitude of the ascending node. ARGP Argument of periapsis. M0 Mean anomaly at epoch. T0 Epoch. MU Gravitational parameter. NU True anomaly. A Semi-major axis. TAU Orbital period. Distance units are km. Angular units are radians. Time units are seconds.
- Overrides:
toArray
in classOsculatingElements
- Returns:
- double[]
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getTrueAnomaly
public double getTrueAnomaly() throws SpiceException
Return true anomaly.Units are radians.
- Returns:
- double
- Throws:
SpiceException
- exception
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getSemiMajorAxis
public double getSemiMajorAxis() throws SpiceException
Return the orbital semi-major axis.Units are km.
This method throws an exception if the semi-major axis cannot be computed.
- Returns:
- double
- Throws:
SpiceException
- exception
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getPeriod
public double getPeriod() throws SpiceException
Return the orbital period.Units are seconds.
This method throws an exception if the period cannot be computed.
- Returns:
- double
- Throws:
SpiceException
- exception
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