Package talonsoalbi_at_gmail_dot_com.ssoxmatch.actions

Class MinorBodyPropagator

java.lang.Object

talonsoalbi_at_gmail_dot_com.ssoxmatch.actions.MinorBodyPropagator

public class MinorBodyPropagator
extends Object

To propagate the orbits of the minor objects to certain final epoch.

Author:

talonso

Method Summary

Modifier and Type	Method	Description
static String	getFile(String folder, double jd)	Returns the path to a given binary file
static ArrayList<String>	getFilenamesInLocalFolder(String directoryName)	Returns the list of files in the provided local folder
static int	getNumberOfPerturbersUsed(File f)	Returns the number of perturbing asteroids used in a given preintegrated file, provided that the file is complete, including the calculations for comets
static OrbitalElement	getOrbitalElementsFromPositionAndVelocity(double[] pos, double[] v, double jd, double mass, String name, boolean checkTolerance)	Obtain a set of orbital elements knowing the position and velocity vectors in certain instant, according to the classical theory of the two body motion.
static OrbitalElement	getOrbitalElementsFromPositionAndVelocity(double[] pos, double[] v, double jd, double mass, String name, double checkTolerance)	Obtain a set of orbital elements knowing the position and velocity vectors in certain instant, according to the classical theory of the two body motion.
static void	main(String[] args)	Main program.
static void	preIntegrate(ArrayList<OrbitalElement> aster, ArrayList<OrbitalElement> comet, Double forceStartJD)	Preintegration program
static void	preIntegrate(ArrayList<OrbitalElement> aster, ArrayList<OrbitalElement> comet, Double forceStartJD, Double forceEndJD)	Preintegration program
static ArrayList<OrbitalElement>	readElements(File f, boolean jpl, boolean checkList)	Reads the data contained in a given file and returns the list of orbital elements from the position and velocity vector on it, for all minor bodies
static ArrayList<OrbitalElement>	readElements(File f, boolean jpl, boolean checkList, int limitAster, int limitComet)	Reads the data contained in a given file and returns the list of orbital elements from the position and velocity vector on it, for all minor bodies
static void	reset()	Reset all the private static variables in this class

Methods inherited from class java.lang.Object

equals, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Method Details

main

public static void main(String[] args)
                 throws InterruptedException,
IOException,
spice.basic.SpiceErrorException

Main program.

Parameters:

args - Not used.

Throws:

InterruptedException - Threading errors

IOException - File system errors

spice.basic.SpiceErrorException - Ephemeris/kernel errors

reset

public static void reset()

Reset all the private static variables in this class

preIntegrate

public static void preIntegrate(ArrayList<OrbitalElement> aster,
 ArrayList<OrbitalElement> comet,
 Double forceStartJD)
                         throws InterruptedException,
IOException,
spice.basic.SpiceErrorException

Preintegration program

Parameters:

aster - Asteroids list, or null

comet - Comets list, or null

forceStartJD - Julian day to be used for the first reference date of the preintegrated files, or null to take it from the elements

Throws:

InterruptedException - Threading errors

IOException - File system errors

spice.basic.SpiceErrorException - Ephemeris/kernel errors

preIntegrate

public static void preIntegrate(ArrayList<OrbitalElement> aster,
 ArrayList<OrbitalElement> comet,
 Double forceStartJD,
 Double forceEndJD)
                         throws InterruptedException,
IOException,
spice.basic.SpiceErrorException

Preintegration program

Parameters:

aster - Asteroids list, or null

comet - Comets list, or null

forceStartJD - Julian day to be used for the first reference date of the preintegrated files, or null to take it from the elements

forceEndJD - Julian day for the oldest observation, or null to get it from the properties

Throws:

InterruptedException - Threading errors

IOException - File system errors

spice.basic.SpiceErrorException - Ephemeris/kernel errors

getFilenamesInLocalFolder

public static ArrayList<String> getFilenamesInLocalFolder(String directoryName)
                                                   throws spice.basic.SpiceErrorException,
IOException

Returns the list of files in the provided local folder

Parameters:

directoryName - Name of folder in the local system

Returns:

List of files

Throws:

spice.basic.SpiceErrorException - Whatever problem reading the missions

IOException - Whatever problem reading the properties file (when not read before)

getFile

public static String getFile(String folder,
 double jd)
                      throws spice.basic.SpiceErrorException,
IOException

Returns the path to a given binary file

Parameters:

folder - Folder where the files are located, respect the local folder

jd - Julian day for the file name, or <= 0 for the index file

Returns:

Path to the preintegration file for the date and folder provided

Throws:

spice.basic.SpiceErrorException - Whatever problem reading the missions

IOException - Whatever problem reading the properties file (when not read before)

getNumberOfPerturbersUsed

public static int getNumberOfPerturbersUsed(File f)
                                     throws IOException

Returns the number of perturbing asteroids used in a given preintegrated file, provided that the file is complete, including the calculations for comets

Parameters:

f - The file

Returns:

The number of perturbing asteroids

Throws:

IOException - If the file does not exists, is not complete, or an IO error happened

readElements

public static ArrayList<OrbitalElement> readElements(File f,
 boolean jpl,
 boolean checkList)
                                              throws spice.basic.SpiceErrorException,
IOException

Reads the data contained in a given file and returns the list of orbital elements from the position and velocity vector on it, for all minor bodies

Parameters:

f - File to read

jpl - If the file belongs to JPL elements, or Lowell ones

checkList - True to check the objects in the output list, comparing with NBodyIntegrator.getOrbitalElements()

Returns:

List of orbital elements

Throws:

spice.basic.SpiceErrorException - Ephemeris errors

IOException - Whatever problem reading the elements file

readElements

public static ArrayList<OrbitalElement> readElements(File f,
 boolean jpl,
 boolean checkList,
 int limitAster,
 int limitComet)
                                              throws spice.basic.SpiceErrorException,
IOException

Reads the data contained in a given file and returns the list of orbital elements from the position and velocity vector on it, for all minor bodies

Parameters:

f - File to read

jpl - If the file belongs to JPL elements, or Lowell ones

checkList - True to check the objects in the output list, comparing with NBodyIntegrator.getOrbitalElements()

limitAster - Maximum number of asteroids to read, or -1 to read them all

limitComet - Maximum number of comets to read, or -1 to read them all

Returns:

List of orbital elements

Throws:

spice.basic.SpiceErrorException - Ephemeris errors

IOException - Whatever problem reading the elements file

getOrbitalElementsFromPositionAndVelocity

public static OrbitalElement getOrbitalElementsFromPositionAndVelocity(double[] pos,
 double[] v,
 double jd,
 double mass,
 String name,
 boolean checkTolerance)
                                                                throws IllegalArgumentException,
IOException,
spice.basic.SpiceErrorException

Obtain a set of orbital elements knowing the position and velocity vectors in certain instant, according to the classical theory of the two body motion.
For reference see Practical Ephemeris Calculations, by Oliver Montenbruck, chapter 3

Parameters:

pos - Geometric heliocentric position vector in ecliptic coordinates, in AU. Velocities can be included here in case v is set to null

v - Heliocentric velocity vector in ecliptic coordinates, in AU / day. Velocities can be included in pos when v is null

jd - Time of vectors as Julian day

mass - Mass of the orbiting body in Msun. Can be set to zero if it is very low or unknown

name - Body name

checkTolerance - True will check the output and set converge flag to false in case the elements will not recover accurately the input vector, using as tolerance 1E-10 AU

Returns:

A set of orbital elements describing the shape and orientation of the orbit, and ready for subsequent ephemeris calculations (all data except magnitude, mag slope, name, and applicable times). Mean equinox and ecliptic of the input vector (assumed J2000)

Throws:

IllegalArgumentException - If the orbit is a straight line through the sun

IOException - File system errors

spice.basic.SpiceErrorException - Ephemeris/kernel errors

getOrbitalElementsFromPositionAndVelocity

public static OrbitalElement getOrbitalElementsFromPositionAndVelocity(double[] pos,
 double[] v,
 double jd,
 double mass,
 String name,
 double checkTolerance)
                                                                throws IllegalArgumentException,
IOException,
spice.basic.SpiceErrorException

Obtain a set of orbital elements knowing the position and velocity vectors in certain instant, according to the classical theory of the two body motion.
For reference see Practical Ephemeris Calculations, by Oliver Montenbruck, chapter 3.

Parameters:

pos - Geometric heliocentric position vector in ecliptic coordinates, in AU. Velocities can be included here in case v is set to null.

v - Heliocentric velocity vector in ecliptic coordinates, in AU / day. Velocities can be included in pos when v is null

jd - Time of vectors as Julian day.

mass - Mass of the orbiting body in Msun. Can be set to zero if it is very low or unknown.

name - Body name

checkTolerance - Tolerance value to consider the elements computed as wrong. Set to <=0 to skip this check.

Returns:

A set of orbital elements describing the shape and orientation of the orbit, and ready for subsequent ephemeris calculations (all data except magnitude, mag slope, name, and applicable times). Mean equinox and ecliptic of the input vector (assumed J2000).

Throws:

IllegalArgumentException - If the orbit is a straight line through the sun.

spice.basic.SpiceErrorException - If the JPL constant GMS cannot be read

IOException - File system errors