org.vizzini.math.orbit
Class OrbitFactory

java.lang.Object
  org.vizzini.math.orbit.OrbitFactory

public class OrbitFactory
extends Object

Provides a factory for orbit instances.

Since:

v0.3

Version:

v0.3

Author:

Jeffrey M. Thompson

Method Summary

IOrbit	create(double mu, double a, double ecc, double i, double omega, double w, double trueAnomaly0) Return an orbit instance for the given parameters.
IOrbit	create(double mu, double a, double ecc, double i, double omega, double w, double trueAnomaly0, double t0) Return an orbit instance for the given parameters.
IOrbit	create(double mu, Vector r0, Vector v0, double t0) Return an orbit instance for the given parameters.
static OrbitFactory	getInstance() Return the singleton instance.

Methods inherited from class java.lang.Object

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

Method Detail

getInstance

public static OrbitFactory getInstance()

Return the singleton instance.

Since:

v0.3

create

public IOrbit create(double mu,
                     Vector r0,
                     Vector v0,
                     double t0)

Return an orbit instance for the given parameters.

Parameters:

mu - Gravitational parameter of central body. (km^3 sec^-2)

r0 - Position vector at epoch. (km)

v0 - Velocity vector at epoch. (km/sec)

t0 - Epoch time of parameters. (sec)

create

public IOrbit create(double mu,
                     double a,
                     double ecc,
                     double i,
                     double omega,
                     double w,
                     double trueAnomaly0)

Return an orbit instance for the given parameters.

Parameters:

mu - Gravitational parameter of central body. (km^3 sec^-2)

a - Semi-major axis. (km)

ecc - Eccentricity.

i - Inclination. (radians)

omega - Longitude of the ascending node. (radians)

w - Argument of periapsis. (radians)

trueAnomaly0 - True anomaly at epoch. (radians)

create

public IOrbit create(double mu,
                     double a,
                     double ecc,
                     double i,
                     double omega,
                     double w,
                     double trueAnomaly0,
                     double t0)

Return an orbit instance for the given parameters.

Parameters:

mu - Gravitational parameter of central body. (km^3 sec^-2)

a - Semi-major axis. (km)

ecc - Eccentricity.

i - Inclination. (radians)

omega - Longitude of the ascending node. (radians)

w - Argument of periapsis. (radians)

trueAnomaly0 - True anomaly at epoch. (radians)

t0 - Epoch time of parameters. (sec)