org.vizzini.math.orbit
Class CircularOrbit

java.lang.Object
  org.vizzini.math.orbit.AbstractOrbit
      org.vizzini.math.orbit.EllipticOrbit
          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