private void OnDrawGizmos()
{
Gizmos.color = Color.yellow;
Gizmos.DrawSphere(transform.position + transform.TransformDirection(Rb.centerOfMass), 0.3f);
Gizmos.color = Color.blue;
Vector3 centerOfLift = new Vector3();
float totalLift = 0;
foreach (VehiclePart part in Parts)
{
Aerodynamics aerodynamics = new Aerodynamics();
if (part.Type == VehiclePartType.MoveableStructural)
{
aerodynamics = ((TMoveableStructure)part).Aerodynamics;
}
else if (part.Type == VehiclePartType.Structural)
{
aerodynamics = ((TStructuralPart)part).Aerodynamics;
}
Vector3 worldAC = transform.position + transform.TransformDirection(aerodynamics.LocalAerodynamicCenter);
float magnitude = aerodynamics.LiftVector.magnitude;
centerOfLift += magnitude * worldAC;
totalLift += magnitude;
}
centerOfLift /= totalLift;
Gizmos.DrawSphere(centerOfLift, 0.3f);
}
private void OnDrawGizmos()
{
Gizmos.color = Color.yellow;
//Gizmos.DrawSphere(transform.position + transform.TransformDirection(Rb.centerOfMass), 0.3f);
Gizmos.DrawSphere(transform.position + transform.TransformDirection(CenterOfMass), 0.3f);
Gizmos.color = Color.blue;
Vector3 centerOfLift = new Vector3();
float totalLift = 0;
foreach (VehiclePart part in Parts)
{
if (part is IAerodynamicPart)
{
Aerodynamics aerodynamics = (part as IAerodynamicPart).Aerodynamics;
Vector3 worldAC = aerodynamics.GetAdjustedWorldAerodynamicCenter(part); //part.transform.position + part.transform.TransformDirection(aerodynamics.LocalAerodynamicCenter);
Vector3 relativePosition = worldAC - transform.position;
float magnitude = aerodynamics.LiftVector.magnitude;
centerOfLift += magnitude * relativePosition;
totalLift += magnitude;
}
}
centerOfLift /= totalLift;
Gizmos.DrawSphere(centerOfLift + transform.position, 0.3f);
}
public void CorrectGetAerodynamicsByString(string input)
{
var pilots = new Mock <ICarServices>();
var parts = new Aerodynamics
{
Name = "Aerodynamics",
Price = 100,
Speed = 40,
Strength = 50,
IsDeleted = false,
};
pilots.Setup(x => x.GetAerodynamics(It.IsAny <string>()))
.Returns(parts);
var result = pilots.Object.GetAerodynamics(input);
var resultName = result.Name;
var resultPrice = result.Price;
var resultSpeed = result.Speed;
var resultId = result.IsDeleted;
Assert.Equal(false, resultId);
Assert.Equal(40, resultSpeed);
Assert.Equal(100, resultPrice);
Assert.Equal("Aerodynamics", resultName);
}
public string GetLogMessage()
{
return(string.Format(@"------------- Simulation ------------
{0}
{1}
{2}
{3}
{4}
{5}
{6}
{7}
{8}
{9}
------------- Simulation ------------",
this.ToLogMessage(),
Acceleration.ToLogMessage(),
Aerodynamics.ToLogMessage(),
Atmosphere.ToLogMessage(),
Control.ToLogMessage(),
Control.ControlInterval.ToLogMessage(),
Control.QAlpha.ToLogMessage(),
Coordinates.ToLogMessage(),
Pitch.ToLogMessage(),
Velocity.ToLogMessage()));
}
private void OnCoordinatesParsed(object source, CoordinatesParsedEventArgs args)
{
Vector vInfinity = new Vector(new double[] {
Math.Cos(args.AOA) * Math.Cos(args.AOY) * args.MagnitudeOfVInfinity,
-Math.Sin(args.AOY) * args.MagnitudeOfVInfinity,
Math.Sin(args.AOA) * Math.Cos(args.AOY) * args.MagnitudeOfVInfinity
});
// Parse the airfoil file for the 2-dimensional coordinates of the camber line
double[,] camberLine = AirfoilGeometryApproximator.GetCamberLine(args.Coordinates,
args.NumberOfTilesChordwise + 1);
// Generate an array of wing tiles
WingTile[] wingTiles = AirfoilGeometryApproximator.GetWingTiles(camberLine,
args.Chord,
args.WingSpan,
args.NumberOfTilesSpanwise);
// Generate a matrix with the aerodynamic linear equations
Matrix <double> EquationMatrix = Aerodynamics.ConstructAICCirculationEquationMatrix(wingTiles, vInfinity);
// Solve said equations for gammas (vorticities) with Gaussian elimination
double[] gammas = Matrix <double> .SolveWithGaussianElimination(EquationMatrix);
// Get the total aerodynamic reaction.
Vector[] forces = Aerodynamics.GetForces(wingTiles, vInfinity, gammas, args.Rho);
Vector totalForce = Aerodynamics.GetTotalForce(forces);
Vector totalMoment = Aerodynamics.GetTotalMoment(new Vector(new double[] {
args.Chord / 4,
args.WingSpan / 2,
0
}),
forces,
wingTiles);
// Get the magnitude of the lift and drag forces.
double lift = totalForce.Coordinates[2] * Math.Cos(args.AOA) - totalForce.Coordinates[0] * Math.Sin(args.AOA);
double inducedDrag = totalForce.Coordinates[2] * Math.Sin(args.AOA) + totalForce.Coordinates[0] * Math.Cos(args.AOA);
// Get the coefficient of lift.
double factor = 2 / (args.Rho * vInfinity.MagS * args.WingSpan * args.Chord);
double CL = factor * lift;
double CDI = factor * inducedDrag;
double CM = factor * totalMoment.Coordinates[1] / args.Chord;
// Display
Console.WriteLine("------------------------- Data -----------------------------");
Console.WriteLine($"CL = {CL}");
SimulationComplete?.Invoke(this, new SimulationCompleteEventArgs(camberLine,
wingTiles,
forces,
CL,
CDI,
CM));
}
// Initialisation
private void Start()
{
im = GetComponent <InputManager>();
rb = GetComponent <Rigidbody>();
ty = GetComponent <Tyres>();
engine = GetComponent <Engine>();
trans = GetComponent <Transmission>();
aero = GetComponent <Aerodynamics>();
brakes = GetComponent <Brakes>();
diff = GetComponent <Differential>();
steer = GetComponent <Steering>();
wheels = GetComponent <Wheels>();
if (CM)
{
rb.centerOfMass = CM.localPosition;
}
}
private bool Allocate()
{
bool result = true;
atmosphere = new Atmosphere(this);
propulsion = new Propulsion(this);
aerodynamics = new Aerodynamics(this);
FCS = new FlightControlSystem(this);
groundReactions = new GroundReactions(this);
inertial = new Inertial(this);
massBalance = new MassBalance(this);
propagate = new Propagate(this);
auxiliary = new Auxiliary(this);
aircraft = new Aircraft(this);
//output = new Output(this);
input = new Input(this);
groundCallback = new GroundCallback();
state = new State(this); // This must be done here, as the State
// class needs valid pointers to the above model classes
// Initialize models so they can communicate with each other
if (!atmosphere.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("Atmosphere model init failed");
}
error += 1;
}
if (!FCS.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("FCS model init failed");
}
error += 2;
}
if (!propulsion.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("Propulsion model init failed");
}
error += 4;
}
if (!massBalance.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("MassBalance model init failed");
}
error += 8;
}
if (!aerodynamics.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("Aerodynamics model init failed");
}
error += 16;
}
if (!inertial.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("Inertial model init failed");
}
error += 32;
}
if (!groundReactions.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("Ground Reactions model init failed");
}
error += 64;
}
if (!aircraft.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("Aircraft model init failed");
}
error += 128;
}
if (!propagate.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("Propagate model init failed");
}
error += 256;
}
if (!auxiliary.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("Auxiliary model init failed");
}
error += 512;
}
if (!input.InitModel())
{
if (log.IsErrorEnabled)
{
log.Error("Intput model init failed");
}
error += 1024;
}
if (error > 0)
{
result = false;
}
ic = new InitialCondition(this);
// Schedule a model. The second arg (the integer) is the pass number. For
// instance, the atmosphere model gets executed every fifth pass it is called
// by the executive. Everything else here gets executed each pass.
// IC and Trim objects are NOT scheduled.
Schedule(input, 1);
Schedule(atmosphere, 1);
Schedule(FCS, 1);
Schedule(propulsion, 1);
Schedule(massBalance, 1);
Schedule(aerodynamics, 1);
Schedule(inertial, 1);
Schedule(groundReactions, 1);
Schedule(aircraft, 1);
Schedule(propagate, 1);
Schedule(auxiliary, 1);
//Schedule(output, 1);
modelLoaded = false;
return(result);
}