public RgbaColor(double red, double green, double blue, double alpha = 1.0)
{
Red = DirectBindingMath.Clamp(red, 0, 1);
Green = DirectBindingMath.Clamp(green, 0, 1);
Blue = DirectBindingMath.Clamp(blue, 0, 1);
Alpha = DirectBindingMath.Clamp(alpha, 0, 1);
}
public void UpdateAutopilot(FlightCtrlState c)
{
Vector3d translate = translateProvider();
c.X = (float)DirectBindingMath.Clamp(translate.x, -1, 1);
c.Y = (float)DirectBindingMath.Clamp(translate.y, -1, 1);
c.Z = (float)DirectBindingMath.Clamp(translate.z, -1, 1);
}
public double UTAtMeanAnomaly(double meanAnomaly, double ut)
{
double currentMeanAnomaly = MeanAnomalyAtUt(ut);
double meanDifference = meanAnomaly - currentMeanAnomaly;
if (eccentricity < 1)
{
meanDifference = DirectBindingMath.ClampRadians2Pi(meanDifference);
}
return(ut + meanDifference / MeanMotion);
}
public double MeanAnomalyAtUt(double ut)
{
// We use ObtAtEpoch and not meanAnomalyAtEpoch because somehow meanAnomalyAtEpoch
// can be wrong when using the RealSolarSystem mod. ObtAtEpoch is always correct.
double ret = (orbitTimeAtEpoch + (ut - epoch)) * MeanMotion;
if (eccentricity < 1)
{
ret = DirectBindingMath.ClampRadians2Pi(ret);
}
return(ret);
}
public double GetMeanAnomalyAtEccentricAnomaly(double ecc)
{
double e = eccentricity;
if (e < 1)
{
//elliptical orbits
return(DirectBindingMath.ClampRadians2Pi(ecc - (e * Math.Sin(ecc))));
}
else
{
//hyperbolic orbits
return((e * Math.Sinh(ecc)) - ecc);
}
}
public void UpdateAutopilot(FlightCtrlState c)
{
if (!(vessel.vessel.horizontalSrfSpeed > 0.1f))
{
return;
}
if (Math.Abs(ExtraMath.AngleDelta(vessel.Heading, vessel.VelocityHeading)) <= 90)
{
c.wheelSteer = (float)DirectBindingMath.Clamp(bearingProvider() / -10, -1, 1);
}
else
{
c.wheelSteer = -(float)DirectBindingMath.Clamp(bearingProvider() / -10, -1, 1);
}
}
public double GetEccentricAnomalyAtTrueAnomaly(double trueAnomaly)
{
double e = eccentricity;
trueAnomaly = DirectBindingMath.ClampRadians2Pi(trueAnomaly);
if (e < 1)
{
//elliptical orbits
double cosE = (e + Math.Cos(trueAnomaly)) / (1 + e * Math.Cos(trueAnomaly));
double sinE = Math.Sqrt(1 - (cosE * cosE));
if (trueAnomaly > Math.PI)
{
sinE *= -1;
}
return(DirectBindingMath.ClampRadians2Pi(Math.Atan2(sinE, cosE)));
}
else
{
//hyperbolic orbits
double coshE = (e + Math.Cos(trueAnomaly)) / (1 + e * Math.Cos(trueAnomaly));
if (coshE < 1)
{
throw new ArgumentException("OrbitExtensions.GetEccentricAnomalyAtTrueAnomaly: True anomaly of " +
trueAnomaly + " radians is not attained by orbit with eccentricity " +
eccentricity);
}
double ecc = DirectBindingMath.Acosh(coshE);
if (trueAnomaly > Math.PI)
{
ecc *= -1;
}
return(ecc);
}
}
public void UpdateAutopilot(FlightCtrlState c)
{
c.wheelThrottle = (float)DirectBindingMath.Clamp(throttleProvider(), 0, 1);
}
public double DescendingNodeTrueAnomaly(KSPOrbitModule.IOrbit b) => DirectBindingMath.ClampRadians2Pi(AscendingNodeTrueAnomaly(b) + Math.PI);
