/// <summary>
/// Create and initialize new orbit state from orbital elements.
/// </summary>
/// <param name="eccentricity">Eccentricity.</param>
/// <param name="semiMajorAxis">Main axis semi width.</param>
/// <param name="meanAnomalyDeg">Mean anomaly in degrees.</param>
/// <param name="inclinationDeg">Orbit inclination in degrees.</param>
/// <param name="argOfPerifocusDeg">Orbit argument of perifocus in degrees.</param>
/// <param name="ascendingNodeDeg">Longitude of ascending node in degrees.</param>
/// <param name="attractorMass">Attractor mass.</param>
/// <param name="gConst">Gravitational constant.</param>
public KeplerOrbitData(double eccentricity, double semiMajorAxis, double meanAnomalyDeg, double inclinationDeg, double argOfPerifocusDeg, double ascendingNodeDeg, double attractorMass,
double gConst)
{
this.Eccentricity = eccentricity;
this.SemiMajorAxis = semiMajorAxis;
if (eccentricity < 1.0)
{
this.SemiMinorAxis = SemiMajorAxis * Math.Sqrt(1 - Eccentricity * Eccentricity);
}
else if (eccentricity > 1.0)
{
this.SemiMinorAxis = SemiMajorAxis * Math.Sqrt(Eccentricity * Eccentricity - 1);
}
else
{
this.SemiMajorAxis = 0;
}
var normal = EclipticNormal.normalized;
var ascendingNode = EclipticRight.normalized;
ascendingNodeDeg %= 360;
if (ascendingNodeDeg > 180)
{
ascendingNodeDeg -= 360;
}
inclinationDeg %= 360;
if (inclinationDeg > 180)
{
inclinationDeg -= 360;
}
argOfPerifocusDeg %= 360;
if (argOfPerifocusDeg > 180)
{
argOfPerifocusDeg -= 360;
}
ascendingNode = KeplerOrbitUtils.RotateVectorByAngle(ascendingNode, ascendingNodeDeg * KeplerOrbitUtils.Deg2Rad, normal).normalized;
normal = KeplerOrbitUtils.RotateVectorByAngle(normal, inclinationDeg * KeplerOrbitUtils.Deg2Rad, ascendingNode).normalized;
Periapsis = ascendingNode;
Periapsis = KeplerOrbitUtils.RotateVectorByAngle(Periapsis, argOfPerifocusDeg * KeplerOrbitUtils.Deg2Rad, normal).normalized;
this.SemiMajorAxisBasis = Periapsis;
this.SemiMinorAxisBasis = Vector3d.Cross(Periapsis, normal);
this.MeanAnomaly = meanAnomalyDeg * KeplerOrbitUtils.Deg2Rad;
this.EccentricAnomaly = KeplerOrbitUtils.ConvertMeanToEccentricAnomaly(this.MeanAnomaly, this.Eccentricity);
this.TrueAnomaly = KeplerOrbitUtils.ConvertEccentricToTrueAnomaly(this.EccentricAnomaly, this.Eccentricity);
this.AttractorMass = attractorMass;
this.GravConst = gConst;
CalculateOrbitStateFromOrbitalElements();
}
