org.vizzini.math.orbit
Class EllipticOrbit

java.lang.Object
  extended by org.vizzini.math.orbit.AbstractOrbit
      extended by org.vizzini.math.orbit.EllipticOrbit
All Implemented Interfaces:
IOrbit
Direct Known Subclasses:
CircularOrbit

public class EllipticOrbit
extends AbstractOrbit

Provides an elliptic orbit.

Since:
v0.3
Version:
v0.3
Author:
Jeffrey M. Thompson

Constructor Summary
EllipticOrbit(double mu, double a, double ecc, double i, double omega, double w, double trueAnomaly0)
          Construct this object using the given parameters.
EllipticOrbit(double mu, double a, double ecc, double i, double omega, double w, double trueAnomaly, double t0)
          Construct this object using the given parameters.
EllipticOrbit(double mu, Vector r, Vector v)
          Construct this object using the given parameters.
EllipticOrbit(double mu, Vector r, Vector v, double t0)
          Construct this object using the given parameters.
 
Method Summary
 double getPeriod()
          Return the orbital period.
 
Methods inherited from class org.vizzini.math.orbit.AbstractOrbit
getA, getE, getEcc, getEccentricAnomaly, getEccentricAnomaly0, getH, getI, getMeanAnomaly, getMeanAnomaly0, getMu, getN, getOmega, getR, getR0, getRa, getRp, getT0, getTrueAnomaly, getTrueAnomaly0, getV, getV0, getVa, getVp, getW, isVectorBased, setA, setEcc, setI, setMu, setOmega, setR0, setT0, setTrueAnomaly0, setV0, setW, toString
 
Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, wait, wait, wait
 

Constructor Detail

EllipticOrbit

public EllipticOrbit(double mu,
                     Vector r,
                     Vector v)
Construct this object using the given parameters.

Parameters:
mu - Gravitational parameter of central body. (km^3 sec^-2)
r - Position vector. (km)
v - Velocity vector. (km/sec)
Since:
v0.3

EllipticOrbit

public EllipticOrbit(double mu,
                     Vector r,
                     Vector v,
                     double t0)
Construct this object using the given parameters.

Parameters:
mu - Gravitational parameter of central body. (km^3 sec^-2)
r - Position vector. (km)
v - Velocity vector. (km/sec)
t0 - Epoch time of parameters. (sec)
Since:
v0.3

EllipticOrbit

public EllipticOrbit(double mu,
                     double a,
                     double ecc,
                     double i,
                     double omega,
                     double w,
                     double trueAnomaly0)
Construct this object using 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)
Since:
v0.3

EllipticOrbit

public EllipticOrbit(double mu,
                     double a,
                     double ecc,
                     double i,
                     double omega,
                     double w,
                     double trueAnomaly,
                     double t0)
Construct this object using 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)
trueAnomaly - True anomaly at epoch. (radians)
t0 - Epoch time of parameters. (sec)
Since:
v0.3
Method Detail

getPeriod

public double getPeriod()
Return the orbital period.

Specified by:
getPeriod in interface IOrbit
Overrides:
getPeriod in class AbstractOrbit
Since:
v0.3


Copyright 2007 Vizzini.org. All Rights Reserved. 2007.12.25.03.00.02