org.jeospace.physics.orbit
Class OrbitalElements

java.lang.Object
  org.jeospace.physics.orbit.OrbitalElements

public class OrbitalElements

extends java.lang.Object

An immutable object containing a set of measure objects that together represent orbital elements. Descriptions of the elements can be found at:
http://ssd.jpl.nasa.gov/glossary.html
or
http://www.amsat.org/amsat/keps/kepmodel.html

Version:

$Revision: 1.1.1.1 $

Author:

Rex Melton

See Also:

DecimalAngle, Epoch, Length, Longitude

Constructor Summary

OrbitalElements(double eccentricity, Longitude inclination, Longitude ascendingNode, Longitude argumentOfPeriapsis, Length distanceOfPeriapsis, Epoch timeOfPeriapsis, Epoch epoch, double GM)
Create an OrbitalElements object with the given parameters.

OrbitalElements(double eccentricity, Longitude inclination, Longitude ascendingNode, Longitude argumentOfPeriapsis, Length semiMajorAxis, Longitude meanAnomalyAtTheEpoch, Epoch epoch, double GM)
Create an OrbitalElements object with the given parameters.

OrbitalElements(double eccentricity, Longitude inclination, Longitude ascendingNode, Longitude argumentOfPeriapsis, Longitude meanAnomalyAtTheEpoch, DecimalAngle meanMotion, double dragCoefficient, Epoch epoch, double GM)
Create an OrbitalElements object with the given parameters.

Method Summary

boolean	equals(java.lang.Object obj) Compare two OrbitalElements objects for equality.
Longitude	getArgumentOfPeriapsis() Return the argument of periapsis
Length	getDistanceOfPeriapsis() Return the distance of periapsis
double	getDragCoefficient() Return the drag coefficient
double	getEccentricity() Return the orbital eccentricity
Epoch	getEpoch() Return the epoch
Longitude	getInclination() Return the orbital inclination
Longitude	getLongitudeOfTheAscendingNode() Return the longitude of the ascending node
Longitude	getMeanAnomalyAtTheEpoch() Return the mean anomaly at the epoch
DecimalAngle	getMeanMotion() Return the mean motion (per day)
Length	getSemiMajorAxis() Return the semi-major axis
Length	getSemiMinorAxis() Return the semi-minor axis
Epoch	getTimeOfPeriapsis() Return the Julian Day of the time of periapsis
OrbitalElementsType	getType() Return the instantiation type of these orbital elements
int	hashCode() Calculate the hashcode

Methods inherited from class java.lang.Object

clone, finalize, getClass, notify, notifyAll, toString, wait, wait, wait

Constructor Detail

OrbitalElements

public OrbitalElements(double eccentricity,
                       Longitude inclination,
                       Longitude ascendingNode,
                       Longitude argumentOfPeriapsis,
                       Length distanceOfPeriapsis,
                       Epoch timeOfPeriapsis,
                       Epoch epoch,
                       double GM)

Create an OrbitalElements object with the given parameters. The arguments of this constructor are typical of the published elements for high eccentricity planetary objects such as comets.

Parameters:

eccentricity - the eccentricity

inclination - the inclination to the reference plane

ascendingNode - the longitude of the ascending node

argumentOfPeriapsis - the argument of periapsis

distanceOfPeriapsis - the distance of periapsis

timeOfPeriapsis - the time of periapsis

epoch - the epoch

GM - the gravitational constant, in km^3/sec^2

OrbitalElements

public OrbitalElements(double eccentricity,
                       Longitude inclination,
                       Longitude ascendingNode,
                       Longitude argumentOfPeriapsis,
                       Length semiMajorAxis,
                       Longitude meanAnomalyAtTheEpoch,
                       Epoch epoch,
                       double GM)

Create an OrbitalElements object with the given parameters. The elements of this constructor are typical of the published elements for low eccentricity planetary objects such as planets and asteroids.

Parameters:

eccentricity - the eccentricity

inclination - the inclination to the reference plane

ascendingNode - the longitude of the ascending node

argumentOfPeriapsis - the argument of periapsis

semiMajorAxis - the semi-major axis

meanAnomalyAtTheEpoch - the mean anomaly at the time of the epoch

epoch - the epoch

GM - the gravitational constant, in km^3/sec^2

OrbitalElements

public OrbitalElements(double eccentricity,
                       Longitude inclination,
                       Longitude ascendingNode,
                       Longitude argumentOfPeriapsis,
                       Longitude meanAnomalyAtTheEpoch,
                       DecimalAngle meanMotion,
                       double dragCoefficient,
                       Epoch epoch,
                       double GM)

Create an OrbitalElements object with the given parameters. The elements of this constructor are typical of the published elements for earth's satellites found in "NORAD Two-Line Element Sets".

Parameters:

eccentricity - the eccentricity

inclination - the inclination to the reference plane

ascendingNode - the longitude of the ascending node

argumentOfPeriapsis - the argument of periapsis

meanAnomalyAtTheEpoch - the mean anomaly at the time of the epoch

meanMotion - the mean angular motion of the object per day

dragCoefficient - the drag coefficient

epoch - the epoch

GM - the gravitational constant, in km^3/sec^2

Method Detail

getEccentricity

public double getEccentricity()

Return the orbital eccentricity

Returns:

the double value of the orbital eccentricity

getInclination

public Longitude getInclination()

Return the orbital inclination

Returns:

the orbital inclination

getLongitudeOfTheAscendingNode

public Longitude getLongitudeOfTheAscendingNode()

Return the longitude of the ascending node

Returns:

the longitude of the ascending node

getArgumentOfPeriapsis

public Longitude getArgumentOfPeriapsis()

Return the argument of periapsis

Returns:

the argument of periapsis

getDistanceOfPeriapsis

public Length getDistanceOfPeriapsis()

Return the distance of periapsis

Returns:

the distance of periapsis

getSemiMajorAxis

public Length getSemiMajorAxis()

Return the semi-major axis

Returns:

the semi-major axis

getSemiMinorAxis

public Length getSemiMinorAxis()

Return the semi-minor axis

Returns:

the semi-minor axis

getMeanMotion

public DecimalAngle getMeanMotion()

Return the mean motion (per day)

Returns:

the mean motion (per day)

getTimeOfPeriapsis

public Epoch getTimeOfPeriapsis()

Return the Julian Day of the time of periapsis

Returns:

the Julian Day of the time of periapsis

getMeanAnomalyAtTheEpoch

public Longitude getMeanAnomalyAtTheEpoch()

Return the mean anomaly at the epoch

Returns:

the mean anomaly at the epoch

getDragCoefficient

public double getDragCoefficient()

Return the drag coefficient

Returns:

the drag coefficient

getEpoch

public Epoch getEpoch()

Return the epoch

Returns:

the epoch

getType

public OrbitalElementsType getType()

Return the instantiation type of these orbital elements

Returns:

the instantiation type of these orbital elements

hashCode

public int hashCode()

Calculate the hashcode

Returns:

the hashcode

equals

public boolean equals(java.lang.Object obj)

Compare two OrbitalElements objects for equality. The result is true if and only if the argument object is not null, is an OrbitalElements object and represents an identical element set as this OrbitalElements object.

Two OrbitalElements objects are equal only if it's constituent objects are equal.

Parameters:

obj - the object to compare with

Returns:

true if the OrbitalElements objects are the same; false otherwise.