/// <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 += Mathd.PI_2 * deltaTime / Period;
}
MeanAnomaly %= Mathd.PI_2;
if (MeanAnomaly < 0)
{
MeanAnomaly = Mathd.PI_2 - MeanAnomaly;
}
EccentricAnomaly = CelestialBodyUtils.KeplerSolver(MeanAnomaly, Eccentricity);
var cosE = Math.Cos(EccentricAnomaly);
TrueAnomaly = Math.Acos((cosE - Eccentricity) / (1 - Eccentricity * cosE));
if (MeanAnomaly > Mathd.PI)
{
TrueAnomaly = Mathd.PI_2 - TrueAnomaly;
}
if (double.IsNaN(MeanAnomaly) || double.IsInfinity(MeanAnomaly))
{
Debug.Log("SpaceGravity2D: NaN(INF) MEAN ANOMALY"); //litle paranoya
Debug.Break();
}
if (double.IsNaN(EccentricAnomaly) || double.IsInfinity(EccentricAnomaly))
{
Debug.Log("SpaceGravity2D: NaN(INF) ECC ANOMALY");
Debug.Break();
}
if (double.IsNaN(TrueAnomaly) || double.IsInfinity(TrueAnomaly))
{
Debug.Log("SpaceGravity2D: NaN(INF) TRUE ANOMALY");
Debug.Break();
}
}
else
{
double n = Math.Sqrt(AttractorMass * GravitationalConstant / Math.Pow(SemiMajorAxis, 3));
MeanAnomaly = MeanAnomaly + n * deltaTime;
EccentricAnomaly = CelestialBodyUtils.KeplerSolverHyperbolicCase(MeanAnomaly, Eccentricity);
TrueAnomaly = Math.Atan2(Math.Sqrt(Eccentricity * Eccentricity - 1.0) * Math.Sinh(EccentricAnomaly), Eccentricity - Math.Cosh(EccentricAnomaly));
}
}
public void UpdateOrbitAnomaliesByTime(double deltaTime)
{
if (eccentricity < 1)
{
if (period > 1e-5)
{
meanAnomaly += Mathd.PI_2 * deltaTime / period;
}
meanAnomaly %= Mathd.PI_2;
if (meanAnomaly < 0)
{
meanAnomaly = Mathd.PI_2 - meanAnomaly;
}
eccentricAnomaly = CelestialBodyUtils.KeplerSolver(meanAnomaly, eccentricity);
var cosE = System.Math.Cos(eccentricAnomaly);
trueAnomaly = System.Math.Acos((cosE - eccentricity) / (1 - eccentricity * cosE));
if (meanAnomaly > Mathd.PI)
{
trueAnomaly = Mathd.PI_2 - trueAnomaly;
}
if (double.IsNaN(meanAnomaly) || double.IsInfinity(meanAnomaly))
{
Debug.Log("SpaceGravity2D: NaN(INF) MEAN ANOMALY"); //litle paranoya
Debug.Break();
}
if (double.IsNaN(eccentricAnomaly) || double.IsInfinity(eccentricAnomaly))
{
Debug.Log("SpaceGravity2D: NaN(INF) ECC ANOMALY");
Debug.Break();
}
if (double.IsNaN(trueAnomaly) || double.IsInfinity(trueAnomaly))
{
Debug.Log("SpaceGravity2D: NaN(INF) TRUE ANOMALY");
Debug.Break();
}
}
else
{
double n = System.Math.Sqrt(attractorMass * gravConst / System.Math.Pow(semiMajorAxis, 3)) * Mathd.Sign(orbitNormalDotEclipticNormal);
meanAnomaly = meanAnomaly - n * deltaTime;
eccentricAnomaly = CelestialBodyUtils.KeplerSolverHyperbolicCase(meanAnomaly, eccentricity);
trueAnomaly = System.Math.Atan2(System.Math.Sqrt(eccentricity * eccentricity - 1.0) * System.Math.Sinh(eccentricAnomaly), eccentricity - System.Math.Cosh(eccentricAnomaly));
}
}
/// <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 % Mathd.PI_2;
if (Eccentricity < 1)
{
if (MeanAnomaly < 0)
{
MeanAnomaly += Mathd.PI_2;
}
EccentricAnomaly = CelestialBodyUtils.KeplerSolver(MeanAnomaly, Eccentricity);
TrueAnomaly = CelestialBodyUtils.ConvertEccentricToTrueAnomaly(EccentricAnomaly, Eccentricity);
}
else
{
EccentricAnomaly = CelestialBodyUtils.KeplerSolverHyperbolicCase(MeanAnomaly, Eccentricity);
TrueAnomaly = CelestialBodyUtils.ConvertEccentricToTrueAnomaly(EccentricAnomaly, Eccentricity);
}
SetPositionByCurrentAnomaly();
SetVelocityByCurrentAnomaly();
}
/// <summary>
/// Sets the eccentricity and updates all corresponding orbit state values.
/// </summary>
/// <param name="e">The new eccentricity value.</param>
/// <remarks>
/// Mean anomaly will try to preserve.
/// </remarks>
public void SetEccentricity(double e)
{
if (!IsValidOrbit)
{
return;
}
e = Mathd.Abs(e);
var _periapsis = PeriapsisDistance; // Periapsis remains constant
Eccentricity = e;
var compresion = Eccentricity < 1 ? (1 - Eccentricity * Eccentricity) : (Eccentricity * Eccentricity - 1);
SemiMajorAxis = Math.Abs(_periapsis / (1 - Eccentricity));
FocalParameter = SemiMajorAxis * compresion;
SemiMinorAxis = SemiMajorAxis * Mathd.Sqrt(compresion);
CenterPoint = SemiMajorAxis * Math.Abs(Eccentricity) * SemiMajorAxisBasis;
if (Eccentricity < 1)
{
EccentricAnomaly = CelestialBodyUtils.KeplerSolver(MeanAnomaly, Eccentricity);
var cosE = Math.Cos(EccentricAnomaly);
TrueAnomaly = Math.Acos((cosE - Eccentricity) / (1 - Eccentricity * cosE));
if (MeanAnomaly > Mathd.PI)
{
TrueAnomaly = Mathd.PI_2 - TrueAnomaly;
}
}
else
{
EccentricAnomaly = CelestialBodyUtils.KeplerSolverHyperbolicCase(MeanAnomaly, Eccentricity);
TrueAnomaly = Math.Atan2(Math.Sqrt(Eccentricity * Eccentricity - 1) * Math.Sinh(EccentricAnomaly), Eccentricity - Math.Cosh(EccentricAnomaly));
}
SetVelocityByCurrentAnomaly();
SetPositionByCurrentAnomaly();
CalculateNewOrbitData();
}
public void SetEccentricity(double e)
{
if (!isValidOrbit)
{
return;
}
e = Mathd.Abs(e);
var _periapsis = periapsisDistance; // Periapsis remains constant
eccentricity = e;
var compresion = eccentricity < 1 ? (1 - eccentricity * eccentricity) : (eccentricity * eccentricity - 1);
semiMajorAxis = System.Math.Abs(_periapsis / (1 - eccentricity));
focalParameter = semiMajorAxis * compresion;
semiMinorAxis = semiMajorAxis * Mathd.Sqrt(compresion);
centerPoint = semiMajorAxis * System.Math.Abs(eccentricity) * semiMajorAxisBasis;
if (eccentricity < 1)
{
eccentricAnomaly = CelestialBodyUtils.KeplerSolver(meanAnomaly, eccentricity);
var cosE = System.Math.Cos(eccentricAnomaly);
trueAnomaly = System.Math.Acos((cosE - eccentricity) / (1 - eccentricity * cosE));
if (meanAnomaly > Mathd.PI)
{
trueAnomaly = Mathd.PI_2 - trueAnomaly;
}
}
else
{
eccentricAnomaly = CelestialBodyUtils.KeplerSolverHyperbolicCase(meanAnomaly, eccentricity);
trueAnomaly = System.Math.Atan2(System.Math.Sqrt(eccentricity * eccentricity - 1) * System.Math.Sinh(eccentricAnomaly), eccentricity - System.Math.Cosh(eccentricAnomaly));
}
SetVelocityByCurrentAnomaly();
SetPositionByCurrentAnomaly();
CalculateNewOrbitData();
}
