public void TrueAnomalyCalcs(OrbitDB orbitDB)
{
double sgp = orbitDB.GravitationalParameterAU;
double o_a = orbitDB.SemiMajorAxis;
double o_e = orbitDB.Eccentricity;
double o_i = Angle.ToRadians(orbitDB.Inclination);
double o_Ω = Angle.ToRadians(orbitDB.LongitudeOfAscendingNode);
double o_M0 = Angle.ToRadians(orbitDB.MeanAnomalyAtEpoch);
double o_n = Angle.ToRadians(orbitDB.MeanMotion);
double o_ω = Angle.ToRadians(orbitDB.ArgumentOfPeriapsis);
double o_lop = OrbitMath.LonditudeOfPeriapsis2d(o_Ω, o_ω, o_i);
DateTime o_epoch = orbitDB.Epoch;
double periodInSeconds = orbitDB.OrbitalPeriod.TotalSeconds;
double segmentTime = periodInSeconds / 16;
//lets break the orbit up and check the paremeters at different points of the orbit:
for (int i = 0; i < 16; i++)
{
TimeSpan timeSinceEpoch = TimeSpan.FromSeconds(segmentTime * i);
DateTime segmentDatetime = o_epoch + timeSinceEpoch;
double o_M = OrbitMath.GetMeanAnomalyFromTime(o_M0, o_n, timeSinceEpoch.TotalSeconds); //orbitProcessor uses this calc directly
double o_E = OrbitProcessor.GetEccentricAnomaly(orbitDB, o_M);
double o_ν = OrbitProcessor.GetTrueAnomaly(orbitDB, segmentDatetime);
var pos = OrbitProcessor.GetPosition_AU(orbitDB, segmentDatetime);
Vector3 vel = (Vector3)OrbitMath.InstantaneousOrbitalVelocityVector(sgp, pos, o_a, o_e, o_ν);
double aop = OrbitMath.ArgumentOfPeriapsis2(pos, i, o_Ω, o_ν);
double ea = o_e * o_a;
double eccentricAnomaly = OrbitMath.GetEccentricAnomalyFromStateVectors(pos, o_a, ea, aop);
double ν1 = OrbitMath.TrueAnomaly(sgp, pos, vel);
double ν2 = OrbitMath.TrueAnomaly(o_E, pos, vel);
double ν3 = OrbitMath.TrueAnomalyFromEccentricAnomaly(o_e, eccentricAnomaly);
double ν4 = OrbitMath.TrueAnomalyFromEccentricAnomaly2(o_e, eccentricAnomaly);
//var ν5 = OrbitMath.TrueAnomaly2(ev, pos, vel);
//var ν6 = OrbitMath.TrueAnomaly(pos, aop);
double d1 = Angle.ToDegrees(ν1);
double d2 = Angle.ToDegrees(ν2);
double d3 = Angle.ToDegrees(ν3);
double d4 = Angle.ToDegrees(ν4);
//var d5 = Angle.ToDegrees(ν5);
//var d6 = Angle.ToDegrees(ν6);
Assert.AreEqual(0, Angle.DifferenceBetweenRadians(o_ν, ν1), 1.0E-7, "True Anomaly ν expected: " + Angle.ToDegrees(o_ν) + " was: " + Angle.ToDegrees(ν1));
Assert.AreEqual(0, Angle.DifferenceBetweenRadians(o_ν, ν2), 1.0E-7, "True Anomaly ν expected: " + Angle.ToDegrees(o_ν) + " was: " + Angle.ToDegrees(ν2));
Assert.AreEqual(0, Angle.DifferenceBetweenRadians(o_ν, ν3), 1.0E-7, "True Anomaly ν expected: " + Angle.ToDegrees(o_ν) + " was: " + Angle.ToDegrees(ν3));
Assert.AreEqual(0, Angle.DifferenceBetweenRadians(o_ν, ν4), 1.0E-7, "True Anomaly ν expected: " + Angle.ToDegrees(o_ν) + " was: " + Angle.ToDegrees(ν4));
//Assert.AreEqual(0, Angle.DifferenceBetweenRadians(directAngle, aop - ν5), angleΔ);
//Assert.AreEqual(0, Angle.DifferenceBetweenRadians(directAngle, aop - ν6), angleΔ);
}
}
public void TestEccentricAnomalyCalcs(OrbitDB orbitDB)
{
double sgp = orbitDB.GravitationalParameterAU;
double o_a = orbitDB.SemiMajorAxis;
double o_e = orbitDB.Eccentricity;
double o_i = Angle.ToRadians(orbitDB.Inclination);
double o_Ω = Angle.ToRadians(orbitDB.LongitudeOfAscendingNode);
double o_M0 = Angle.ToRadians(orbitDB.MeanAnomalyAtEpoch);
double o_n = Angle.ToRadians(orbitDB.MeanMotion);
double o_ω = Angle.ToRadians(orbitDB.ArgumentOfPeriapsis);
double o_lop = OrbitMath.LonditudeOfPeriapsis2d(o_Ω, o_ω, o_i);
DateTime o_epoch = orbitDB.Epoch;
double periodInSeconds = orbitDB.OrbitalPeriod.TotalSeconds;
double segmentTime = periodInSeconds / 16;
//lets break the orbit up and check the paremeters at different points of the orbit:
for (int i = 0; i < 16; i++)
{
TimeSpan timeSinceEpoch = TimeSpan.FromSeconds(segmentTime * i);
DateTime segmentDatetime = o_epoch + timeSinceEpoch;
double o_M = OrbitMath.GetMeanAnomalyFromTime(o_M0, o_n, timeSinceEpoch.TotalSeconds); //orbitProcessor uses this calc directly
double o_E = OrbitProcessor.GetEccentricAnomaly(orbitDB, o_M);
double o_ν = OrbitProcessor.GetTrueAnomaly(orbitDB, segmentDatetime);
var pos = OrbitProcessor.GetPosition_AU(orbitDB, segmentDatetime);
var vel = OrbitMath.InstantaneousOrbitalVelocityVector(sgp, pos, o_a, o_e, o_ν);
double linierEccentricity = o_e * o_a;
var E1 = OrbitMath.GetEccentricAnomalyNewtonsMethod(o_e, o_M); //newtons method.
var E2 = OrbitMath.GetEccentricAnomalyNewtonsMethod2(o_e, o_M); //newtons method.
var E3 = OrbitMath.GetEccentricAnomalyFromTrueAnomaly(o_ν, o_e);
var E4 = OrbitMath.GetEccentricAnomalyFromStateVectors(pos, o_a, linierEccentricity, o_ω);
//var E5 = OrbitMath.GetEccentricAnomalyFromStateVectors2(sgp, o_a, pos, vel);
Assert.Multiple(() =>
{
Assert.AreEqual(o_E, E1, "EccentricAnomaly E expected: " + Angle.ToDegrees(o_E) + " was: " + Angle.ToDegrees(E1));// these two should be calculatd the same way.
Assert.AreEqual(o_E, E2, 1.0E-7, "EccentricAnomaly E expected: " + Angle.ToDegrees(o_E) + " was: " + Angle.ToDegrees(E2));
Assert.AreEqual(o_E, E3, 1.0E-7, "EccentricAnomaly E expected: " + Angle.ToDegrees(o_E) + " was: " + Angle.ToDegrees(E3));
Assert.AreEqual(o_E, E4, 1.0E-7, "EccentricAnomaly E expected: " + Angle.ToDegrees(o_E) + " was: " + Angle.ToDegrees(E4));
//Assert.AreEqual(o_E, E5, 1.0E-7, "EccentricAnomaly E expected: " + Angle.ToDegrees(o_E) + " was: " + Angle.ToDegrees(E5));
});
}
}
public void TestAngleOfPeriapsCalcs(OrbitDB orbitDB)
{
double sgp = orbitDB.GravitationalParameterAU;
double o_a = orbitDB.SemiMajorAxis;
double o_e = orbitDB.Eccentricity;
double o_i = Angle.ToRadians(orbitDB.Inclination);
double o_Ω = Angle.ToRadians(orbitDB.LongitudeOfAscendingNode);
double o_M0 = Angle.ToRadians(orbitDB.MeanAnomalyAtEpoch);
double o_n = Angle.ToRadians(orbitDB.MeanMotion);
double o_ω = Angle.ToRadians(orbitDB.ArgumentOfPeriapsis);
double o_lop = OrbitMath.LonditudeOfPeriapsis2d(o_Ω, o_ω, o_i);
DateTime o_epoch = orbitDB.Epoch;
double periodInSeconds = orbitDB.OrbitalPeriod.TotalSeconds;
double segmentTime = periodInSeconds / 16;
//lets break the orbit up and check the paremeters at different points of the orbit:
for (int i = 0; i < 16; i++)
{
TimeSpan timeSinceEpoch = TimeSpan.FromSeconds(segmentTime * i);
DateTime segmentDatetime = o_epoch + timeSinceEpoch;
double o_M = OrbitMath.GetMeanAnomalyFromTime(o_M0, o_n, timeSinceEpoch.TotalSeconds); //orbitProcessor uses this calc directly
double o_E = OrbitProcessor.GetEccentricAnomaly(orbitDB, o_M);
double o_ν = OrbitProcessor.GetTrueAnomaly(orbitDB, segmentDatetime);
var pos = OrbitProcessor.GetPosition_AU(orbitDB, segmentDatetime);
Vector3 vel = (Vector3)OrbitMath.InstantaneousOrbitalVelocityVector(sgp, pos, o_a, o_e, o_ν);
Vector3 angularVelocity = Vector3.Cross(pos, vel);
Vector3 nodeVector = Vector3.Cross(new Vector3(0, 0, 1), angularVelocity);
Vector3 eccentVector = OrbitMath.EccentricityVector(sgp, pos, vel);
//var ω1 = OrbitMath.ArgumentOfPeriapsis(nodeVector, eccentVector, position, velocity);
//var ω2 = OrbitMath.ArgumentOfPeriapsis(nodeVector, eccentVector, position, velocity, o_Ω);
var ω3 = OrbitMath.ArgumentOfPeriapsis2(pos, o_i, o_Ω, o_ν);
Assert.Multiple(() =>
{
//Assert.AreEqual(o_ω, ω1, 1.0E-7, "AoP ω expected: " + Angle.ToDegrees(o_ω) + " was: " + Angle.ToDegrees(ω1));
//Assert.AreEqual(ω1, ω2, 1.0E-7, "AoP ω expected: " + Angle.ToDegrees(ω1) + " was: " + Angle.ToDegrees(ω2));
Assert.AreEqual(o_ω, ω3, 1.0E-7, "AoP ω expected: " + Angle.ToDegrees(o_ω) + " was: " + Angle.ToDegrees(ω3));
});
}
}
public void TestMeanAnomalyCalcs(OrbitDB orbitDB)
{
double sgp = orbitDB.GravitationalParameterAU;
double o_a = orbitDB.SemiMajorAxis;
double o_e = orbitDB.Eccentricity;
double o_i = Angle.ToRadians(orbitDB.Inclination);
double o_Ω = Angle.ToRadians(orbitDB.LongitudeOfAscendingNode);
double o_M0 = Angle.ToRadians(orbitDB.MeanAnomalyAtEpoch);
double o_n = Angle.ToRadians(orbitDB.MeanMotion);
double o_ω = Angle.ToRadians(orbitDB.ArgumentOfPeriapsis);
double o_lop = OrbitMath.LonditudeOfPeriapsis2d(o_Ω, o_ω, o_i);
DateTime o_epoch = orbitDB.Epoch;
double periodInSeconds = orbitDB.OrbitalPeriod.TotalSeconds;
double segmentTime = periodInSeconds / 16;
//lets break the orbit up and check the paremeters at different points of the orbit:
for (int i = 0; i < 16; i++)
{
TimeSpan timeSinceEpoch = TimeSpan.FromSeconds(segmentTime * i);
DateTime segmentDatetime = o_epoch + timeSinceEpoch;
double o_M = OrbitMath.GetMeanAnomalyFromTime(o_M0, o_n, timeSinceEpoch.TotalSeconds); //orbitProcessor uses this calc directly
double o_E = OrbitProcessor.GetEccentricAnomaly(orbitDB, o_M);
double o_ν = OrbitProcessor.GetTrueAnomaly(orbitDB, segmentDatetime);
var pos = OrbitProcessor.GetPosition_AU(orbitDB, segmentDatetime);
var vel = OrbitMath.InstantaneousOrbitalVelocityVector(sgp, pos, o_a, o_e, o_ν);
var M1 = OrbitMath.GetMeanAnomaly(o_e, o_E);
Assert.AreEqual(o_M, M1, 1.0E-7, "MeanAnomaly M expected: " + Angle.ToDegrees(o_M) + " was: " + Angle.ToDegrees(M1));
}
}
public void TestingKeplerConversions(OrbitDB orbitDB)
{
double sgp = orbitDB.GravitationalParameterAU;
double o_a = orbitDB.SemiMajorAxis;
double o_e = orbitDB.Eccentricity;
double o_i = Angle.ToRadians(orbitDB.Inclination);
double o_Ω = Angle.ToRadians(orbitDB.LongitudeOfAscendingNode);
double o_M0 = Angle.ToRadians(orbitDB.MeanAnomalyAtEpoch);
double o_n = Angle.ToRadians(orbitDB.MeanMotion);
double o_ω = Angle.ToRadians(orbitDB.ArgumentOfPeriapsis);
double o_lop = OrbitMath.LonditudeOfPeriapsis2d(o_Ω, o_ω, o_i);
DateTime o_epoch = orbitDB.Epoch;
double periodInSeconds = OrbitMath.GetOrbitalPeriodInSeconds(sgp, o_a);
Assert.AreEqual(periodInSeconds, orbitDB.OrbitalPeriod.TotalSeconds, 0.1);
//lets break the orbit up and check the rest of the paremeters at different points of the orbit:
double segmentTime = periodInSeconds / 16;
for (int i = 0; i < 16; i++)
{
TimeSpan timeSinceEpoch = TimeSpan.FromSeconds(segmentTime * i);
DateTime segmentDatetime = o_epoch + timeSinceEpoch;
double o_M = OrbitMath.GetMeanAnomalyFromTime(o_M0, o_n, timeSinceEpoch.TotalSeconds); //orbitProcessor uses this calc directly
double o_E = OrbitProcessor.GetEccentricAnomaly(orbitDB, o_M);
double o_ν = OrbitProcessor.GetTrueAnomaly(orbitDB, segmentDatetime);
var pos = OrbitProcessor.GetPosition_AU(orbitDB, segmentDatetime);
var vel = (Vector3)OrbitMath.InstantaneousOrbitalVelocityVector(sgp, pos, o_a, o_e, o_ν);
var ke = OrbitMath.KeplerFromPositionAndVelocity(sgp, pos, vel, segmentDatetime);
var ke_epoch = ke.Epoch;
double ke_a = ke.SemiMajorAxis;
double ke_e = ke.Eccentricity;
double ke_i = ke.Inclination;
double ke_Ω = ke.LoAN;
double ke_M0 = ke.MeanAnomalyAtEpoch;
double ke_n = ke.MeanMotion;
double ke_ω = ke.AoP;
double ke_E = OrbitMath.GetEccentricAnomalyNewtonsMethod(ke.Eccentricity, ke_M0);
double ke_ν = OrbitMath.TrueAnomalyFromEccentricAnomaly(ke_e, ke_E);
Assert.Multiple(() =>
{
//these should not change (other than floating point errors) between each itteration
Assert.AreEqual(o_a, ke_a, 0.001, "SemiMajorAxis a"); //should be more accurate than this, though if testing from a given set of ke to state, and back, the calculated could be more acurate...
Assert.AreEqual(o_e, ke_e, 0.00001, "Eccentricity e");
Assert.AreEqual(o_i, ke_i, 1.0E-7, "Inclination i expected: " + Angle.ToDegrees(o_i) + " was: " + Angle.ToDegrees(ke_i));
Assert.AreEqual(o_Ω, ke_Ω, 1.0E-7, "LoAN Ω expected: " + Angle.ToDegrees(o_Ω) + " was: " + Angle.ToDegrees(ke_Ω));
Assert.AreEqual(o_ω, ke_ω, 1.0E-7, "AoP ω expected: " + Angle.ToDegrees(o_ω) + " was: " + Angle.ToDegrees(ke_ω));
Assert.AreEqual(o_n, ke_n, 1.0E-7, "MeanMotion n expected: " + Angle.ToDegrees(o_n) + " was: " + Angle.ToDegrees(ke_n));
//these will change between itterations:
Assert.AreEqual(o_E, ke_E, 1.0E-7, "EccentricAnomaly E expected: " + Angle.ToDegrees(o_E) + " was: " + Angle.ToDegrees(ke_E));
Assert.AreEqual(o_ν, ke_ν, 1.0E-7, "True Anomaly ν expected: " + Angle.ToDegrees(o_ν) + " was: " + Angle.ToDegrees(ke_ν));
Assert.AreEqual(o_M, ke_M0, 1.0E-7, "MeanAnomaly M expected: " + Angle.ToDegrees(o_M) + " was: " + Angle.ToDegrees(ke_M0));
});
}
}
public void TestOrbitalVelocityCalcs(OrbitDB orbitDB)
{
double sgp = orbitDB.GravitationalParameterAU;
double o_a = orbitDB.SemiMajorAxis;
double o_e = orbitDB.Eccentricity;
double o_i = Angle.ToRadians(orbitDB.Inclination);
double o_Ω = Angle.ToRadians(orbitDB.LongitudeOfAscendingNode);
double o_M0 = Angle.ToRadians(orbitDB.MeanAnomalyAtEpoch);
double o_n = Angle.ToRadians(orbitDB.MeanMotion);
double o_ω = Angle.ToRadians(orbitDB.ArgumentOfPeriapsis);
double o_lop = OrbitMath.LonditudeOfPeriapsis2d(o_Ω, o_ω, o_i);
DateTime o_epoch = orbitDB.Epoch;
double periodInSeconds = orbitDB.OrbitalPeriod.TotalSeconds;
double segmentTime = periodInSeconds / 16;
//lets break the orbit up and check the paremeters at different points of the orbit:
for (int i = 0; i < 16; i++)
{
TimeSpan timeSinceEpoch = TimeSpan.FromSeconds(segmentTime * i);
DateTime segmentDatetime = o_epoch + timeSinceEpoch;
double o_M = OrbitMath.GetMeanAnomalyFromTime(o_M0, o_n, timeSinceEpoch.TotalSeconds); //orbitProcessor uses this calc directly
double o_E = OrbitProcessor.GetEccentricAnomaly(orbitDB, o_M);
double o_ν = OrbitProcessor.GetTrueAnomaly(orbitDB, segmentDatetime);
var pos = OrbitProcessor.GetPosition_AU(orbitDB, segmentDatetime);
var vel = (Vector3)OrbitMath.InstantaneousOrbitalVelocityVector(sgp, pos, o_a, o_e, o_ν);
Vector3 angularVelocity = Vector3.Cross(pos, vel);
double r = pos.Length();
double speedau = OrbitMath.InstantaneousOrbitalSpeed(sgp, r, o_a);
(double speed, double heading)polarVelocity = OrbitMath.InstantaneousOrbitalVelocityPolarCoordinate(sgp, pos, o_a, o_e, o_ν);
//Tuple<double, double> polarVelocity2 = OrbitMath.PreciseOrbitalVelocityPolarCoordinate2(sgp, pos, o_a, o_e, o_ν, o_lop);
double heading = OrbitMath.HeadingFromPeriaps(pos, o_e, o_a, o_ν);
heading += o_lop;
//Assert.IsTrue(angularVelocity.Z > 0); //TODO:this will break if we test an anti clockwise orbit.
Assert.IsTrue(speedau > 0); //I'm assuming that speed will be <0 if retrograde orbit.
Assert.AreEqual(vel.Length(), speedau, 1.0E-7);
Assert.AreEqual(vel.Length(), polarVelocity.Item1, 1.0E-7);
double hackHeading = OrbitMath.HackVelocityHeading(orbitDB, segmentDatetime);
double hackheadD = Angle.ToDegrees(hackHeading);
double headingD = Angle.ToDegrees(heading);
if (o_e == 0) //we can make this work with ellipses if we add the lop to the position.
{
if (pos.X > 0 && pos.Y > 0) //top right quadrant
{
//Assert.IsTrue(polarVelocity.Item2 > Math.PI * 0.5 && polarVelocity.Item2 < Math.PI);
//Assert.IsTrue(hackHeading > Math.PI * 0.5 && hackHeading < Math.PI);
Assert.IsTrue(heading >= Math.PI * 0.5 && heading <= Math.PI);
}
if (pos.X < 0 && pos.Y > 0)//top left quadrant
{
//Assert.IsTrue(polarVelocity.Item2 > Math.PI && polarVelocity.Item2 < Math.PI * 1.5);
//Assert.IsTrue(hackHeading > Math.PI && hackHeading < Math.PI * 1.5);
Assert.IsTrue(heading >= Math.PI && heading <= Math.PI * 1.5);
}
if (pos.X < 0 && pos.Y < 0)//bottom left quadrant
{
//Assert.IsTrue(polarVelocity.Item2 > Math.PI * 1.5 && polarVelocity.Item2 < Math.PI * 2);
//Assert.IsTrue(hackHeading > Math.PI * 1.5 && hackHeading < Math.PI * 2);
Assert.IsTrue(heading >= Math.PI * 1.5 && heading <= Math.PI * 2);
}
if (pos.X > 0 && pos.Y < 0)//bottom right quadrant
{
//Assert.IsTrue(polarVelocity.Item2 > 0 && polarVelocity.Item2 < Math.PI * 0.5);
//Assert.IsTrue(hackHeading > 0 && hackHeading < Math.PI * 0.5);
Assert.IsTrue(heading >= 0 && heading <= Math.PI * 0.5);
}
}
}
}
public void TestOrbitDBFromVectors(double parentMass, double objMass, Vector3 position, Vector3 velocity)
{
double angleΔ = 0.0000000001;
double sgp_m = OrbitMath.CalculateStandardGravityParameterInM3S2(objMass, parentMass);
KeplerElements ke = OrbitMath.KeplerFromPositionAndVelocity(sgp_m, position, velocity, new DateTime());
Game game = new Game();
EntityManager man = new EntityManager(game, false);
BaseDataBlob[] parentblobs = new BaseDataBlob[3];
parentblobs[0] = new PositionDB(man.ManagerGuid)
{
X_AU = 0, Y_AU = 0, Z_AU = 0
};
parentblobs[1] = new MassVolumeDB()
{
Mass = parentMass
};
parentblobs[2] = new OrbitDB();
Entity parentEntity = new Entity(man, parentblobs);
OrbitDB objOrbit = OrbitDB.FromVector(parentEntity, objMass, parentMass, sgp_m, position, velocity, new DateTime());
Vector3 resultPos = OrbitProcessor.GetPosition_AU(objOrbit, new DateTime());
//check LoAN
var objLoAN = objOrbit.LongitudeOfAscendingNode;
var keLoAN = ke.LoAN;
var loANDifference = objLoAN - keLoAN;
Assert.AreEqual(keLoAN, objLoAN, angleΔ);
//check AoP
var objAoP = objOrbit.ArgumentOfPeriapsis;
var keAoP = ke.AoP;
var difference = objAoP - keAoP;
Assert.AreEqual(keAoP, objAoP, angleΔ);
//check MeanAnomalyAtEpoch
var objM0 = objOrbit.MeanAnomalyAtEpoch;
var keM0 = ke.MeanAnomalyAtEpoch;
Assert.AreEqual(keM0, objM0, angleΔ);
Assert.AreEqual(objM0, OrbitMath.GetMeanAnomalyFromTime(objM0, objOrbit.MeanMotion_DegreesSec, 0), "meanAnomalyError");
//checkEpoch
var objEpoch = objOrbit.Epoch;
var keEpoch = ke.Epoch;
Assert.AreEqual(keEpoch, objEpoch);
//check EccentricAnomaly:
var objE = (OrbitProcessor.GetEccentricAnomaly(objOrbit, objOrbit.MeanAnomalyAtEpoch_Degrees));
//var keE = (OrbitMath.Gete(position, ke.SemiMajorAxis, ke.LinearEccentricity, ke.AoP));
/*
* if (objE != keE)
* {
* var dif = objE - keE;
* Assert.AreEqual(keE, objE, angleΔ);
* }
*/
//check trueAnomaly
var orbTrueAnom = OrbitProcessor.GetTrueAnomaly(objOrbit, new DateTime());
var orbtaDeg = Angle.ToDegrees(orbTrueAnom);
var differenceInRadians = orbTrueAnom - ke.TrueAnomalyAtEpoch;
var differenceInDegrees = Angle.ToDegrees(differenceInRadians);
if (ke.TrueAnomalyAtEpoch != orbTrueAnom)
{
Vector3 eccentVector = OrbitMath.EccentricityVector(sgp_m, position, velocity);
var tacalc1 = OrbitMath.TrueAnomaly(eccentVector, position, velocity);
var tacalc2 = OrbitMath.TrueAnomaly(sgp_m, position, velocity);
var diffa = differenceInDegrees;
var diffb = Angle.ToDegrees(orbTrueAnom - tacalc1);
var diffc = Angle.ToDegrees(orbTrueAnom - tacalc2);
var ketaDeg = Angle.ToDegrees(tacalc1);
}
Assert.AreEqual(0, Angle.DifferenceBetweenRadians(ke.TrueAnomalyAtEpoch, orbTrueAnom), angleΔ,
"more than " + angleΔ + " radians difference, at " + differenceInRadians + " \n " +
"(more than " + Angle.ToDegrees(angleΔ) + " degrees difference at " + differenceInDegrees + ")" + " \n " +
"ke Angle: " + ke.TrueAnomalyAtEpoch + " obj Angle: " + orbTrueAnom + " \n " +
"ke Angle: " + Angle.ToDegrees(ke.TrueAnomalyAtEpoch) + " obj Angle: " + Angle.ToDegrees(orbTrueAnom));
Assert.AreEqual(ke.Eccentricity, objOrbit.Eccentricity);
Assert.AreEqual(ke.SemiMajorAxis, objOrbit.SemiMajorAxis);
var lenke1 = ke.SemiMajorAxis * 2;
var lenke2 = ke.Apoapsis + ke.Periapsis;
Assert.AreEqual(lenke1, lenke2, 1.0E-10);
var lendb1 = objOrbit.SemiMajorAxis_AU * 2;
var lendb2 = objOrbit.Apoapsis_AU + objOrbit.Periapsis_AU;
Assert.AreEqual(lendb1, lendb2, 1.0E-10);
Assert.AreEqual(lenke1, lendb1, 1.0E-10);
Assert.AreEqual(lenke2, lendb2, 1.0E-10);
var ke_apkm = Distance.AuToKm(ke.Apoapsis);
var db_apkm = Distance.AuToKm(objOrbit.Apoapsis_AU);
var differnce = ke_apkm - db_apkm;
Assert.AreEqual(ke.Apoapsis, objOrbit.Apoapsis_AU, 1.0E-10);
Assert.AreEqual(ke.Periapsis, objOrbit.Periapsis_AU, 1.0E-10);
Vector3 posKM = Distance.AuToKm(position);
Vector3 resultKM = Distance.AuToKm(resultPos);
double keslr = EllipseMath.SemiLatusRectum(ke.SemiMajorAxis, ke.Eccentricity);
double keradius = OrbitMath.RadiusAtAngle(ke.TrueAnomalyAtEpoch, keslr, ke.Eccentricity);
Vector3 kemathPos = OrbitMath.GetRalitivePosition(ke.LoAN, ke.AoP, ke.Inclination, ke.TrueAnomalyAtEpoch, keradius);
Vector3 kemathPosKM = Distance.AuToKm(kemathPos);
Assert.AreEqual(kemathPosKM.Length(), posKM.Length(), 0.01);
Assert.AreEqual(posKM.Length(), resultKM.Length(), 0.01, "TA: " + orbtaDeg);
Assert.AreEqual(posKM.X, resultKM.X, 0.01, "TA: " + orbtaDeg);
Assert.AreEqual(posKM.Y, resultKM.Y, 0.01, "TA: " + orbtaDeg);
Assert.AreEqual(posKM.Z, resultKM.Z, 0.01, "TA: " + orbtaDeg);
if (velocity.Z == 0)
{
Assert.IsTrue(ke.Inclination == 0);
Assert.IsTrue(objOrbit.Inclination_Degrees == 0);
}
//var speedVectorAU = OrbitProcessor.PreciseOrbitalVector(sgp, position, ke.SemiMajorAxis);
//var speedVectorAU2 = OrbitProcessor.PreciseOrbitalVector(objOrbit, new DateTime());
//Assert.AreEqual(speedVectorAU, speedVectorAU2);
}
public OrbitalDebugWidget(EntityState entityState) : base(entityState.OrbitIcon.BodyPositionDB)
{
var orbitIcon = entityState.OrbitIcon;
_bodyPosition = orbitIcon.BodyPositionDB;
_orbitDB = entityState.Entity.GetDataBlob <OrbitDB>();
if (_orbitDB.Parent == null) //primary star
{
_positionDB = orbitIcon.BodyPositionDB;
}
else
{
_positionDB = _orbitDB.Parent.GetDataBlob <PositionDB>(); //orbit's position is parent's body position.
}
EntityGuid = entityState.Entity.Guid;
_loan = Angle.ToRadians(_orbitDB.LongitudeOfAscendingNode);
_aop = Angle.ToRadians(_orbitDB.ArgumentOfPeriapsis);
_loP = orbitIcon._loP_radians;
var cP = new PointD()
{
X = orbitIcon.WorldPosition.X, Y = orbitIcon.WorldPosition.Y
};
cP.X -= orbitIcon._linearEccentricity;
var f1 = new PointD()
{
X = cP.X + orbitIcon._linearEccentricity, Y = cP.Y
};
var f2 = new PointD()
{
X = cP.X - orbitIcon._linearEccentricity, Y = cP.Y
};
var coVertex = new PointD()
{
X = cP.X, Y = cP.Y + orbitIcon.SemiMinor
};
var periapsisPnt = new PointD()
{
X = cP.X - orbitIcon.SemiMaj, Y = cP.Y
};
var apoapsisPnt = new PointD()
{
X = cP.X + orbitIcon.SemiMaj, Y = cP.Y
};
_cP = DrawTools.RotatePoint(cP, _loP);
_f1 = DrawTools.RotatePoint(f1, _loP);
_f2 = DrawTools.RotatePoint(f2, _loP);
_coVertex = DrawTools.RotatePoint(coVertex, _loP);
_periapsisPnt = DrawTools.RotatePoint(periapsisPnt, _loP);
_apoapsisPnt = DrawTools.RotatePoint(apoapsisPnt, _loP);
_semiMajAxis = orbitIcon.SemiMaj;
_semiMinAxis = orbitIcon.SemiMinor;
DateTime systemDateTime = _orbitDB.Parent.Manager.ManagerSubpulses.StarSysDateTime;
_trueAnom = OrbitProcessor.GetTrueAnomaly(_orbitDB, systemDateTime);
double secondsFromEpoch = (systemDateTime - _orbitDB.Epoch).TotalSeconds;
_meanAnom = OrbitMath.GetMeanAnomalyFromTime(Angle.ToRadians(_orbitDB.MeanAnomalyAtEpoch), Angle.ToRadians(_orbitDB.MeanMotion), secondsFromEpoch);
_eccentricAnom = OrbitProcessor.GetEccentricAnomaly(_orbitDB, _meanAnom);
_bodyPosPnt = new PointD()
{
X = (_bodyPosition.AbsolutePosition_AU + _worldPosition).X,
Y = (_bodyPosition.AbsolutePosition_AU + _worldPosition).Y
};
CreateLines();
}