public void Deinit()
{
// Environment
StaticAirTemperature.Remove();
StaticPressure.Remove();
// Orbit
Apoapsis.Remove();
Periapsis.Remove();
TimeToApoapsis.Remove();
// Vessel
Altitude.Remove();
AngularVelocity.Remove();
AvailablePosTorque.Remove();
AvailableRCSForce.Remove();
AvailableThrust.Remove();
AvailableTorque.Remove();
Direction.Remove();
DryMass.Remove();
Forward.Remove();
Mass.Remove();
MaxVacuumThrust.Remove();
MomentOfInertia.Remove();
Position.Remove();
Right.Remove();
Thrust.Remove();
Up.Remove();
VacuumSpecificImpulse.Remove();
Velocity.Remove();
}
private void InitializeModules()
{
modules = new List <IInfoModule>();
peri = new Periapsis("Periapsis", currentVessel);
apo = new Apoapsis("Apoapsis", currentVessel);
sma = new SemiMajorAxis("Semi-Major Axis", currentVessel);
ecc = new Eccentricity("Eccentricity", currentVessel);
inc = new Inclination("Inclination", currentVessel);
alt = new Altitude("Current Altitude", currentVessel);
vel = new Velocity("Current Speed", currentVessel);
acc = new Acceleration("Current Acceleration", currentVessel);
peri.IsVisible = PTGUI_Settings.Instance.showPeriapsis;
apo.IsVisible = PTGUI_Settings.Instance.showApoapsis;
sma.IsVisible = PTGUI_Settings.Instance.showSMA;
ecc.IsVisible = PTGUI_Settings.Instance.showApoapsis;
inc.IsVisible = PTGUI_Settings.Instance.showInclination;
alt.IsVisible = PTGUI_Settings.Instance.showAltitude;
vel.IsVisible = PTGUI_Settings.Instance.showVelocity;
acc.IsVisible = PTGUI_Settings.Instance.showAcceleration;
modules.Add(peri);
modules.Add(apo);
modules.Add(sma);
modules.Add(ecc);
modules.Add(inc);
modules.Add(alt);
modules.Add(vel);
modules.Add(acc);
}
private List <IBasicModule> AddOrbitModules()
{
List <IBasicModule> modules = new List <IBasicModule>();
apo = new Apoapsis("Apoapsis");
peri = new Periapsis("Periapsis");
inc = new Inclination("Inclination");
ecc = new Eccentricity("Eccentricity");
period = new Period("Period");
SMA = new SemiMajorAxis("Semi Major Axis");
LAN = new LongAscending("LAN");
AoPE = new ArgOfPeriapsis("Arg of Pe");
altitude = new OrbitAltitude("Altitude");
radar = new RadarAltitude("Radar Altitude");
terrain = new TerrainAltitude("Terrain Altitude");
location = new Location("Location");
apo.IsVisible = settings.showApoapsis;
apo.AlwaysShow = settings.showApoapsisAlways;
peri.IsVisible = settings.showPeriapsis;
peri.AlwaysShow = settings.showPeriapsisAlways;
inc.IsVisible = settings.showInclination;
inc.AlwaysShow = settings.showInclinationAlways;
ecc.IsVisible = settings.showEccentricity;
ecc.AlwaysShow = settings.showEccentricityAlways;
period.IsVisible = settings.showPeriod;
period.AlwaysShow = settings.showPeriodAlways;
SMA.IsVisible = settings.showSMA;
SMA.AlwaysShow = settings.showSMAAlways;
LAN.IsVisible = settings.showLAN;
LAN.AlwaysShow = settings.showLANAlways;
AoPE.IsVisible = settings.showAoPe;
AoPE.AlwaysShow = settings.showAoPeAlways;
altitude.IsVisible = settings.showOrbitAltitude;
altitude.AlwaysShow = settings.showOrbitAltitudeAlways;
radar.IsVisible = settings.showRadar;
radar.AlwaysShow = settings.showRadarAlways;
terrain.IsVisible = settings.showTerrain;
terrain.AlwaysShow = settings.showTerrainAlways;
location.IsVisible = settings.showLocation;
location.AlwaysShow = settings.showLocationAlways;
modules.Add(AoPE);
modules.Add(LAN);
modules.Add(SMA);
modules.Add(terrain);
modules.Add(radar);
modules.Add(altitude);
modules.Add(location);
modules.Add(period);
modules.Add(ecc);
modules.Add(inc);
modules.Add(peri);
modules.Add(apo);
return(modules);
}
public void TestKeplerElementsFromVectors()
{
Vector3 position = new Vector3()
{
X = Distance.KmToAU(405400)
}; //moon at apoapsis
Vector3 velocity = new Vector3()
{
Y = Distance.KmToAU(0.97)
}; //approx velocity of moon at apoapsis
double parentMass = 5.97237e24;
double objMass = 7.342e22;
double sgp = OrbitMath.CalculateStandardGravityParameter(parentMass, objMass);
KeplerElements elements = OrbitMath.KeplerFromPositionAndVelocity(sgp, position, velocity, new DateTime());
Vector3 postionKm = new Vector3()
{
X = 405400
};
Vector3 velocityKm = new Vector3()
{
Y = 0.97
};
double sgpKm = OrbitMath.CalculateStandardGravityParameterInM3S2(parentMass, objMass);
KeplerElements elementsKm = OrbitMath.KeplerFromPositionAndVelocity(sgpKm, postionKm, velocityKm, new DateTime());
//check that the function is unit agnostic.
Assert.AreEqual(Distance.AuToKm(elements.SemiMajorAxis), elementsKm.SemiMajorAxis, 0.001);
Assert.AreEqual(elements.Eccentricity, elementsKm.Eccentricity, 1.0e-9); //this is where inacuarcy from units stars creaping in, not much can do about that.
Assert.AreEqual(Distance.AuToKm(elements.Apoapsis), elementsKm.Apoapsis, 0.001);
Assert.AreEqual(Distance.AuToKm(elements.Periapsis), elementsKm.Periapsis, 0.001);
//var ta = OrbitMath.TrueAnomalyFromEccentricAnomaly(elements.Eccentricity, elements.)
var speedAU = OrbitMath.InstantaneousOrbitalSpeed(sgp, position.Length(), elements.SemiMajorAxis);
//var speedVectorAU = OrbitMath.PreciseOrbitalVelocityVector(sgp, position, elements.SemiMajorAxis, elements.Eccentricity, elements.LoAN + elements.AoP);
//Assert.AreEqual(speedAU, speedVectorAU.Length());
Assert.AreEqual(elementsKm.Apoapsis + elementsKm.Periapsis, elementsKm.SemiMajorAxis * 2, 0.001);
var speedKm = velocityKm.Length();
var speedKm2 = OrbitMath.InstantaneousOrbitalSpeed(sgpKm, postionKm.Length(), elementsKm.SemiMajorAxis);
Assert.AreEqual(speedKm, speedKm2, 0.001);
Assert.GreaterOrEqual(elements.Apoapsis, elements.Periapsis);
Assert.GreaterOrEqual(elementsKm.Apoapsis, elementsKm.Periapsis);
//below was some experimentation with different ways of calculating things, and an attempt to use decimal for Eccentricity.
//not sure it's worth the minor slowdown or complication, didn't seem to fix the problem I was seeing in anycase.
#region experimentation
var H = Vector3.Cross(postionKm, velocityKm).Length();
var p = H * H / sgpKm;
var sma = 1 / (2 / postionKm.Length() - velocityKm.Length() * velocityKm.Length() / sgpKm); // semi-major axis
decimal E;
double Periapsis;
double Apoapsis;
if (sma < (double)decimal.MaxValue)
{
decimal smad = (decimal)sma;
E = GMath.Sqrt(1 - (decimal)p / smad);
decimal PlusMinus = smad * E;
Periapsis = (double)(smad - PlusMinus);
Apoapsis = (double)(smad + PlusMinus);
}
else
{
E = (decimal)Math.Sqrt(1 - p / sma); // eccentricity
double PlusMinus = sma * (double)E;
Periapsis = sma - PlusMinus;
Apoapsis = sma + PlusMinus;
}
Assert.AreEqual(Periapsis + Apoapsis, sma * 2, 0.0001);
var peStr = Periapsis.ToString("R");
var apStr = Apoapsis.ToString("R");
//Assert.AreEqual(elementsKm.SemiMajorAxis, sma);
var difference1 = (Periapsis + Apoapsis) - sma * 2;
var difference2 = (elementsKm.Apoapsis + elementsKm.Periapsis) - elementsKm.SemiMajorAxis * 2;
#endregion
if (velocity.Z == 0)
{
Assert.IsTrue(elements.Inclination == 0);
}
}