org.vizzini.math.orbit
Class CircularOrbit

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

public class CircularOrbit
extends EllipticOrbit

Provides a circular orbit.

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

Constructor Summary
CircularOrbit(double mu, double a, double i, double omega, double trueAnomaly0)
          Construct this object using the given parameters.
CircularOrbit(double mu, double a, double i, double omega, double trueAnomaly0, double t0)
          Construct this object using the given parameters.
CircularOrbit(double mu, Vector r0, Vector v0)
          Construct this object using the given parameters.
CircularOrbit(double mu, Vector r0, Vector v0, double t0)
          Construct this object using the given parameters.
 
Method Summary
 Vector getE()
          Return the eccentricity vector.
 double getW()
          Return the argument of periapsis.
 
Methods inherited from class org.vizzini.math.orbit.EllipticOrbit
getPeriod
 
Methods inherited from class org.vizzini.math.orbit.AbstractOrbit
getA, getEcc, getEccentricAnomaly, getEccentricAnomaly0, getH, getI, getMeanAnomaly, getMeanAnomaly0, getMu, getN, getOmega, getR, getR0, getRa, getRp, getT0, getTrueAnomaly, getTrueAnomaly0, getV, getV0, getVa, getVp, 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

CircularOrbit

public CircularOrbit(double mu,
                     Vector r0,
                     Vector v0)
Construct this object using 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)
Since:
v0.3

CircularOrbit

public CircularOrbit(double mu,
                     Vector r0,
                     Vector v0,
                     double t0)
Construct this object using 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)
Since:
v0.3

CircularOrbit

public CircularOrbit(double mu,
                     double a,
                     double i,
                     double omega,
                     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)
i - Inclination. (radians)
omega - Longitude of the ascending node. (radians)
trueAnomaly0 - True anomaly at epoch. (radians)
Since:
v0.3

CircularOrbit

public CircularOrbit(double mu,
                     double a,
                     double i,
                     double omega,
                     double trueAnomaly0,
                     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)
i - Inclination. (radians)
omega - Longitude of the ascending node. (radians)
trueAnomaly0 - True anomaly at epoch. (radians)
t0 - Epoch time of parameters. (sec)
Since:
v0.3
Method Detail

getE

public Vector getE()
Return the eccentricity vector.

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

getW

public double getW()
Return the argument of periapsis.

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


Copyright 2007 Vizzini.org. All Rights Reserved. 2007.12.25.03.00.02