org.vizzini.math.orbit
Class HyperbolicOrbit

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


Copyright 2007 Vizzini.org. All Rights Reserved. 2007.12.25.03.00.02