org.vizzini.math.orbit
Interface IOrbit

All Known Implementing Classes:

AbstractOrbit, CircularOrbit, EllipticOrbit, HyperbolicOrbit, ParabolicOrbit

public interface IOrbit

Defines methods required by orbits.

Since:

v0.3

Version:

v0.3

Author:

Jeffrey M. Thompson

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 the 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.

Method Detail

getA

double getA()

Return the semi-major axis. (km)

Since:

v0.3

getE

Vector getE()

Return the eccentricity vector.

Since:

v0.3

getEcc

double getEcc()

Return the eccentricity.

Since:

v0.3

getEccentricAnomaly

double getEccentricAnomaly(double t)

Return the eccentric anomaly. (radians)

Parameters:

t - Time of interest. (sec)

Since:

v0.3

getEccentricAnomaly0

double getEccentricAnomaly0()

Return the eccentric anomaly at epoch. (radians)

Since:

v0.3

getH

Vector getH()

Return the angular momentum vector.

Since:

v0.3

getI

double getI()

Return the inclination. (radians)

Since:

v0.3

getMeanAnomaly

double getMeanAnomaly(double t)

Return the mean anomaly. (radians)

Parameters:

t - Time of interest. (sec)

Since:

v0.3

getMeanAnomaly0

double getMeanAnomaly0()

Return the mean anomaly at epoch. (radians)

Since:

v0.3

getMu

double getMu()

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

Since:

v0.3

getN

Vector getN()

Return the node vector.

Since:

v0.3

getOmega

double getOmega()

Return the longitude of the ascending node. (radians)

Since:

v0.3

getPeriod

double getPeriod()

Return the orbital period. (sec)

Since:

v0.3

getR

Vector getR(double t)

Return the position vector. (km)

Parameters:

t - Time of interest. (sec)

Since:

v0.3

getR0

Vector getR0()

Return the position vector at epoch. (km)

Since:

v0.3

getRa

double getRa()

Return the apoapsis radius. (km)

Since:

v0.3

getRp

double getRp()

Return the periapsis radius. (km)

Since:

v0.3

getT0

double getT0()

Return the time of epoch. (sec)

Since:

v0.3

getTrueAnomaly

double getTrueAnomaly(double t)

Return the true anomaly. (radians)

Parameters:

t - Time of interest. (sec)

Since:

v0.3

getTrueAnomaly0

double getTrueAnomaly0()

Return the true anomaly at epoch. (radians)

Since:

v0.3

getV

Vector getV(double t)

Return the velocity vector. (km/sec)

Parameters:

t - Time of interest. (sec)

Since:

v0.3

getV0

Vector getV0()

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

Since:

v0.3

getVa

double getVa()

Return the apoapsis speed. (km/sec)

Since:

v0.3

getVp

double getVp()

Return the periapsis speed. (km/sec)

Since:

v0.3

getW

double getW()

Return the argument of periapsis. (radians)

Since:

v0.3

isVectorBased

boolean isVectorBased()

Return true if this orbit is vector based.

Since:

v0.3