org.vizzini.math.orbit
Class HyperbolicOrbit

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

All Implemented Interfaces:

IOrbit

public class HyperbolicOrbit
extends AbstractOrbit

Provides a hyperbolic orbit.

Since:

v0.3

Version:

v0.3

Author:

Jeffrey M. Thompson

Constructor Summary

HyperbolicOrbit(double mu, double a, double ecc, double i, double omega, double w, double trueAnomaly0)
Construct this object using the given parameters.

HyperbolicOrbit(double mu, double a, double ecc, double i, double omega, double w, double trueAnomaly0, double t0)
Construct this object using the given parameters.

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

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

Method Summary

Methods inherited from class org.vizzini.math.orbit.AbstractOrbit

getA, getE, getEcc, getEccentricAnomaly, getEccentricAnomaly0, getH, getI, getMeanAnomaly, getMeanAnomaly0, getMu, getN, getOmega, getPeriod, 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

HyperbolicOrbit

public HyperbolicOrbit(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

HyperbolicOrbit

public HyperbolicOrbit(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

HyperbolicOrbit

public HyperbolicOrbit(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

HyperbolicOrbit

public HyperbolicOrbit(double mu,
                       double a,
                       double ecc,
                       double i,
                       double omega,
                       double w,
                       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)

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)

Since:

v0.3