org.vizzini.math.orbit
Class AbstractOrbit

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

All Implemented Interfaces:

IOrbit

Direct Known Subclasses:

EllipticOrbit, HyperbolicOrbit, ParabolicOrbit

public abstract class AbstractOrbit
extends Object
implements IOrbit

Provides base functionality for an orbit.

N = kg m sec^-2
a = F / m => N kg^-1 = m sec^-2
So define a kilo-Newton = 1000 N
a = F / m => kN kg^-1 = km sec^-2

Since:

v0.3

Version:

v0.3

Author:

Jeffrey M. Thompson

Constructor Summary

protected	AbstractOrbit(double mu, double a, double ecc, double i, double omega, double w, double nu0) Construct this object using the given parameters.
protected	AbstractOrbit(double mu, double a, double ecc, double i, double omega, double w, double nu0, double t0) Construct this object using the given parameters.
protected	AbstractOrbit(double mu, Vector r, Vector v) Construct this object using the given parameters.
protected	AbstractOrbit(double mu, Vector r0, Vector v0, double t0) Construct this object using the given parameters.

Method Summary

double	getA() Return the semi-major axis.
Vector	getE() Return the eccentricity vector.
double	getEcc() Return the eccentricity.
double	getEccentricAnomaly(double t) Return the eccentric anomaly.
double	getEccentricAnomaly0() Return the eccentric anomaly at epoch.
Vector	getH() Return the angular momentum vector.
double	getI() Return the inclination.
double	getMeanAnomaly(double t) Return the mean anomaly.
double	getMeanAnomaly0() Return the mean anomaly at epoch.
double	getMu() Return the gravitational parameter of central body.
Vector	getN() Return the node vector.
double	getOmega() Return the longitude of the ascending node.
double	getPeriod() Return the orbital period.
Vector	getR(double t) Return the position vector.
Vector	getR0() Return the position vector at epoch.
double	getRa() Return the apoapsis radius.
double	getRp() Return the periapsis radius.
double	getT0() Return the time of epoch.
double	getTrueAnomaly(double t) Return the true anomaly.
double	getTrueAnomaly0() Return the true anomaly at epoch.
Vector	getV(double t) Return the velocity vector.
Vector	getV0() Return the velocity vector at epoch.
double	getVa() Return the apoapsis speed.
double	getVp() Return the periapsis speed.
double	getW() Return the argument of periapsis.
boolean	isVectorBased() Return true if this orbit is vector based.
protected void	setA(double a)
protected void	setEcc(double ecc)
protected void	setI(double i)
protected void	setMu(double mu)
protected void	setOmega(double omega)
protected void	setR0(Vector r0)
protected void	setT0(double t0)
protected void	setTrueAnomaly0(double nu0)
protected void	setV0(Vector v0)
protected void	setW(double w)
String	toString() Return a string representation of this object.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, wait, wait, wait

Constructor Detail

AbstractOrbit

protected AbstractOrbit(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

AbstractOrbit

protected AbstractOrbit(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

AbstractOrbit

protected AbstractOrbit(double mu,
                        double a,
                        double ecc,
                        double i,
                        double omega,
                        double w,
                        double nu0)

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)

nu0 - True anomaly at epoch. (radians)

Since:

v0.3

AbstractOrbit

protected AbstractOrbit(double mu,
                        double a,
                        double ecc,
                        double i,
                        double omega,
                        double w,
                        double nu0,
                        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)

nu0 - True anomaly at epoch. (radians)

t0 - Epoch time of parameters. (sec)

Since:

v0.3

Method Detail

getA

public double getA()

Return the semi-major axis. (km)

Specified by:

getA in interface IOrbit

Since:

v0.3

getE

public Vector getE()

Return the eccentricity vector.

Specified by:

getE in interface IOrbit

Since:

v0.3

getEcc

public double getEcc()

Return the eccentricity.

Specified by:

getEcc in interface IOrbit

Since:

v0.3

getEccentricAnomaly

public double getEccentricAnomaly(double t)

Return the eccentric anomaly.

Specified by:

getEccentricAnomaly in interface IOrbit

Parameters:

t - Time of interest. (sec)

Since:

v0.3

getEccentricAnomaly0

public double getEccentricAnomaly0()

Return the eccentric anomaly at epoch. (radians)

Specified by:

getEccentricAnomaly0 in interface IOrbit

Since:

v0.3

getH

public Vector getH()

Return the angular momentum vector.

Specified by:

getH in interface IOrbit

Since:

v0.3

getI

public double getI()

Return the inclination. (radians)

Specified by:

getI in interface IOrbit

Since:

v0.3

getMeanAnomaly

public double getMeanAnomaly(double t)

Return the mean anomaly. (radians)

Specified by:

getMeanAnomaly in interface IOrbit

Parameters:

t - Time of interest. (sec)

Since:

v0.3

getMeanAnomaly0

public double getMeanAnomaly0()

Return the mean anomaly at epoch. (radians)

Specified by:

getMeanAnomaly0 in interface IOrbit

Since:

v0.3

getMu

public double getMu()

Return the gravitational parameter of central body. (km^3 sec^-2)

Specified by:

getMu in interface IOrbit

Since:

v0.3

getN

public Vector getN()

Return the node vector.

Specified by:

getN in interface IOrbit

Since:

v0.3

getOmega

public double getOmega()

Return the longitude of the ascending node. (radians)

Specified by:

getOmega in interface IOrbit

Since:

v0.3

getPeriod

public double getPeriod()

Return the orbital period. (sec)

Specified by:

getPeriod in interface IOrbit

Since:

v0.3

getR

public Vector getR(double t)

Return the position vector. (km)

Specified by:

getR in interface IOrbit

Parameters:

t - Time of interest. (sec)

Since:

v0.3

getR0

public Vector getR0()

Return the position vector at epoch. (km)

Specified by:

getR0 in interface IOrbit

Since:

v0.3

getRa

public double getRa()

Return the apoapsis radius. (km)

Specified by:

getRa in interface IOrbit

Since:

v0.3

getRp

public double getRp()

Return the periapsis radius. (km)

Specified by:

getRp in interface IOrbit

Since:

v0.3

getT0

public double getT0()

Return the time of epoch. (sec)

Specified by:

getT0 in interface IOrbit

Since:

v0.3

getTrueAnomaly

public double getTrueAnomaly(double t)

Description copied from interface: IOrbit

Return the true anomaly. (radians)

Specified by:

getTrueAnomaly in interface IOrbit

Parameters:

t - Time of interest. (sec)

Returns:

Return nu0. (radians)

Since:

v0.3

getTrueAnomaly0

public double getTrueAnomaly0()

Description copied from interface: IOrbit

Return the true anomaly at epoch. (radians)

Specified by:

getTrueAnomaly0 in interface IOrbit

Returns:

Return true anomaly at epoch. (radians)

Since:

v0.3

getV

public Vector getV(double t)

Return the velocity vector. (km/sec)

Specified by:

getV in interface IOrbit

Parameters:

t - Time of interest. (sec)

Since:

v0.3

getV0

public Vector getV0()

Return the velocity vector at epoch. (km/sec)

Specified by:

getV0 in interface IOrbit

Since:

v0.3

getVa

public double getVa()

Return the apoapsis speed. (km/sec)

Specified by:

getVa in interface IOrbit

Since:

v0.3

getVp

public double getVp()

Return the periapsis speed. (km/sec)

Specified by:

getVp in interface IOrbit

Since:

v0.3

getW

public double getW()

Return the argument of periapsis. (radians)

Specified by:

getW in interface IOrbit

Since:

v0.3

isVectorBased

public boolean isVectorBased()

Return true if this orbit is vector based.

Specified by:

isVectorBased in interface IOrbit

Since:

v0.3

toString

public String toString()

Return a string representation of this object.

Overrides:

toString in class Object

Since:

v0.3

setA

protected void setA(double a)

Parameters:

a - The a to set. (km)

Since:

v0.3

setEcc

protected void setEcc(double ecc)

Parameters:

ecc - The ecc to set.

Since:

v0.3

setI

protected void setI(double i)

Parameters:

i - The i to set. (radians)

Since:

v0.3

setMu

protected void setMu(double mu)

Parameters:

mu - The mu to set. (km^3 sec^-2)

Since:

v0.3

setOmega

protected void setOmega(double omega)

Parameters:

omega - The omega to set. (radians)

Since:

v0.3

setR0

protected void setR0(Vector r0)

Parameters:

r0 - The r0 to set. (km)

Since:

v0.3

setT0

protected void setT0(double t0)

Parameters:

t0 - The t0 to set. (sec)

Since:

v0.3

setTrueAnomaly0

protected void setTrueAnomaly0(double nu0)

Parameters:

nu0 - The nu0 to set. (radians)

Since:

v0.3

setV0

protected void setV0(Vector v0)

Parameters:

v0 - The v0 to set. (km/sec)

Since:

v0.3

setW

protected void setW(double w)

Parameters:

w - The w to set. (radians)

Since:

v0.3