/// <summary>
/// Sets the mean anomaly and updates all other anomalies.
/// </summary>
/// <param name="m">The m.</param>
public void SetMeanAnomaly(double m)
{
if (!IsValidOrbit)
{
return;
}
MeanAnomaly = m % KeplerOrbitUtils.PI_2;
if (Eccentricity < 1.0)
{
if (MeanAnomaly < 0)
{
MeanAnomaly += KeplerOrbitUtils.PI_2;
}
EccentricAnomaly = KeplerOrbitUtils.KeplerSolver(MeanAnomaly, Eccentricity);
TrueAnomaly = KeplerOrbitUtils.ConvertEccentricToTrueAnomaly(EccentricAnomaly, Eccentricity);
}
else if (Eccentricity > 1.0)
{
EccentricAnomaly = KeplerOrbitUtils.KeplerSolverHyperbolicCase(MeanAnomaly, Eccentricity);
TrueAnomaly = KeplerOrbitUtils.ConvertEccentricToTrueAnomaly(EccentricAnomaly, Eccentricity);
}
else
{
EccentricAnomaly = KeplerOrbitUtils.ConvertMeanToEccentricAnomaly(MeanAnomaly, Eccentricity);
TrueAnomaly = EccentricAnomaly;
}
SetPositionByCurrentAnomaly();
SetVelocityByCurrentAnomaly();
}
/// <summary>
/// Updates the value of orbital anomalies by defined deltatime.
/// </summary>
/// <param name="deltaTime">The delta time.</param>
/// <remarks>
/// Only anomalies values will be changed.
/// Position and velocity states needs to be updated too after this method call.
/// </remarks>
public void UpdateOrbitAnomaliesByTime(double deltaTime)
{
if (Eccentricity < 1.0)
{
MeanAnomaly += MeanMotion * deltaTime;
MeanAnomaly %= KeplerOrbitUtils.PI_2;
if (MeanAnomaly < 0)
{
MeanAnomaly = KeplerOrbitUtils.PI_2 - MeanAnomaly;
}
EccentricAnomaly = KeplerOrbitUtils.KeplerSolver(MeanAnomaly, Eccentricity);
double cosE = Math.Cos(EccentricAnomaly);
TrueAnomaly = Math.Acos((cosE - Eccentricity) / (1 - Eccentricity * cosE));
if (MeanAnomaly > Math.PI)
{
TrueAnomaly = KeplerOrbitUtils.PI_2 - TrueAnomaly;
}
}
else if (Eccentricity > 1.0)
{
MeanAnomaly = MeanAnomaly + MeanMotion * deltaTime;
EccentricAnomaly = KeplerOrbitUtils.KeplerSolverHyperbolicCase(MeanAnomaly, Eccentricity);
TrueAnomaly = Math.Atan2(Math.Sqrt(Eccentricity * Eccentricity - 1.0) * Math.Sinh(EccentricAnomaly), Eccentricity - Math.Cosh(EccentricAnomaly));
}
else
{
MeanAnomaly = MeanAnomaly + MeanMotion * deltaTime;
EccentricAnomaly = KeplerOrbitUtils.ConvertMeanToEccentricAnomaly(MeanAnomaly, Eccentricity);
TrueAnomaly = EccentricAnomaly;
}
}
/// <summary>
/// Updates the value of orbital anomalies by defined deltatime.
/// </summary>
/// <param name="deltaTime">The delta time.</param>
/// <remarks>
/// Only anomalies values will be changed.
/// Position and velocity states needs to be updated too after this method call.
/// </remarks>
public void UpdateOrbitAnomaliesByTime(double deltaTime)
{
if (Eccentricity < 1)
{
if (Period > 1e-5)
{
MeanAnomaly += KeplerOrbitUtils.PI_2 * deltaTime / Period;
}
MeanAnomaly %= KeplerOrbitUtils.PI_2;
if (MeanAnomaly < 0)
{
MeanAnomaly = KeplerOrbitUtils.PI_2 - MeanAnomaly;
}
EccentricAnomaly = KeplerOrbitUtils.KeplerSolver(MeanAnomaly, Eccentricity);
var cosE = Math.Cos(EccentricAnomaly);
TrueAnomaly = Math.Acos((cosE - Eccentricity) / (1 - Eccentricity * cosE));
if (MeanAnomaly > Math.PI)
{
TrueAnomaly = KeplerOrbitUtils.PI_2 - TrueAnomaly;
}
if (double.IsNaN(MeanAnomaly) || double.IsInfinity(MeanAnomaly))
{
Debug.Log("KeplerOrbitData: NaN(INF) MEAN ANOMALY"); //little paranoya
Debug.Break();
}
if (double.IsNaN(EccentricAnomaly) || double.IsInfinity(EccentricAnomaly))
{
Debug.Log("KeplerOrbitData: NaN(INF) ECC ANOMALY");
Debug.Break();
}
if (double.IsNaN(TrueAnomaly) || double.IsInfinity(TrueAnomaly))
{
Debug.Log("KeplerOrbitData: NaN(INF) TRUE ANOMALY");
Debug.Break();
}
}
else
{
double n = Math.Sqrt(AttractorMass * GravConst / Math.Pow(SemiMajorAxis, 3));// * Math.Sign(OrbitNormalDotEclipticNormal);
MeanAnomaly = MeanAnomaly + n * deltaTime;
EccentricAnomaly = KeplerOrbitUtils.KeplerSolverHyperbolicCase(MeanAnomaly, Eccentricity);
TrueAnomaly = Math.Atan2(Math.Sqrt(Eccentricity * Eccentricity - 1.0) * Math.Sinh(EccentricAnomaly), Eccentricity - Math.Cosh(EccentricAnomaly));
}
}
/// <summary>
/// Updates the value of orbital anomalies by defined deltatime.
/// </summary>
/// <param name="deltaTime">The delta time.</param>
/// <remarks>
/// Only anomalies values will be changed.
/// Position and velocity states needs to be updated too after this method call.
/// </remarks>
public void UpdateOrbitAnomaliesByTime(double deltaTime)
{
if (Eccentricity < 1)
{
if (Period > KeplerOrbitUtils.Epsilon)
{
MeanAnomaly += MeanMotion * deltaTime;
}
MeanAnomaly %= KeplerOrbitUtils.PI_2;
if (MeanAnomaly < 0)
{
MeanAnomaly = KeplerOrbitUtils.PI_2 - MeanAnomaly;
}
EccentricAnomaly = KeplerOrbitUtils.KeplerSolver(MeanAnomaly, Eccentricity);
double cosE = Math.Cos(EccentricAnomaly);
TrueAnomaly = Math.Acos((cosE - Eccentricity) / (1 - Eccentricity * cosE));
if (MeanAnomaly > Math.PI)
{
TrueAnomaly = KeplerOrbitUtils.PI_2 - TrueAnomaly;
}
if (double.IsNaN(MeanAnomaly) || double.IsInfinity(MeanAnomaly))
{
Debug.Log("KeplerOrbitData: NaN(INF) MEAN ANOMALY"); //little paranoya
Debug.Break();
}
if (double.IsNaN(EccentricAnomaly) || double.IsInfinity(EccentricAnomaly))
{
Debug.Log("KeplerOrbitData: NaN(INF) ECC ANOMALY");
Debug.Break();
}
if (double.IsNaN(TrueAnomaly) || double.IsInfinity(TrueAnomaly))
{
Debug.Log("KeplerOrbitData: NaN(INF) TRUE ANOMALY");
Debug.Break();
}
}
else
{
MeanAnomaly = MeanAnomaly + MeanMotion * deltaTime;
EccentricAnomaly = KeplerOrbitUtils.KeplerSolverHyperbolicCase(MeanAnomaly, Eccentricity);
TrueAnomaly = Math.Atan2(Math.Sqrt(Eccentricity * Eccentricity - 1.0) * Math.Sinh(EccentricAnomaly), Eccentricity - Math.Cosh(EccentricAnomaly));
}
}
/// <summary>
/// Sets the eccentricity and updates all corresponding orbit state values.
/// </summary>
/// <param name="e">The new eccentricity value.</param>
public void SetEccentricity(double e)
{
if (!IsValidOrbit)
{
return;
}
e = Math.Abs(e);
double periapsis = PeriapsisDistance; // Periapsis remains constant
Eccentricity = e;
double compresion = Eccentricity < 1 ? (1 - Eccentricity * Eccentricity) : (Eccentricity * Eccentricity - 1);
SemiMajorAxis = Math.Abs(periapsis / (1 - Eccentricity));
FocalParameter = SemiMajorAxis * compresion;
SemiMinorAxis = SemiMajorAxis * Math.Sqrt(compresion);
CenterPoint = SemiMajorAxis * Math.Abs(Eccentricity) * SemiMajorAxisBasis;
if (Eccentricity < 1.0)
{
EccentricAnomaly = KeplerOrbitUtils.KeplerSolver(MeanAnomaly, Eccentricity);
double cosE = Math.Cos(EccentricAnomaly);
TrueAnomaly = Math.Acos((cosE - Eccentricity) / (1 - Eccentricity * cosE));
if (MeanAnomaly > Math.PI)
{
TrueAnomaly = KeplerOrbitUtils.PI_2 - TrueAnomaly;
}
}
else if (Eccentricity > 1.0)
{
EccentricAnomaly = KeplerOrbitUtils.KeplerSolverHyperbolicCase(MeanAnomaly, Eccentricity);
TrueAnomaly = Math.Atan2(Math.Sqrt(Eccentricity * Eccentricity - 1) * Math.Sinh(EccentricAnomaly), Eccentricity - Math.Cosh(EccentricAnomaly));
}
else
{
EccentricAnomaly = KeplerOrbitUtils.ConvertMeanToEccentricAnomaly(MeanAnomaly, Eccentricity);
TrueAnomaly = EccentricAnomaly;
}
SetVelocityByCurrentAnomaly();
SetPositionByCurrentAnomaly();
CalculateOrbitStateFromOrbitalVectors();
}
