org.vizzini.math.orbit
Class ParabolicOrbit

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

public class ParabolicOrbit
extends AbstractOrbit

Provides a parabolic orbit.

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

Constructor Summary
ParabolicOrbit(double mu, double a, double i, double omega, double w, double trueAnomaly0)
          Construct this object using the given parameters.
ParabolicOrbit(double mu, double a, double i, double omega, double w, double trueAnomaly0, double t0)
          Construct this object using the given parameters.
ParabolicOrbit(double mu, Vector r, Vector v)
          Construct this object using the given parameters.
ParabolicOrbit(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

ParabolicOrbit

public ParabolicOrbit(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

ParabolicOrbit

public ParabolicOrbit(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

ParabolicOrbit

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

ParabolicOrbit

public ParabolicOrbit(double mu,
                      double a,
                      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)
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