org.vizzini.math.orbit
Class EllipticOrbit

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