public static double GetRadiusOfOrbit(AstronomicalBody satellite, AstronomicalBody primary, double relativeTangentialSpeed)
{
double requiredRadiusNotFixed = GravitationalConstant * primary.Mass / (relativeTangentialSpeed * relativeTangentialSpeed);
double requiredRadiusFixed = requiredRadiusNotFixed * GravitationalConstantDecimalFix;
return(requiredRadiusFixed);
}
public static double GetRelativeTangentialSpeedForOrbit(AstronomicalBody satellite, AstronomicalBody primary)
{
double distance = GetDistanceBetweenPoints(satellite.Center, primary.Center);
double requiredTangentialSpeedFixed = Math.Sqrt((GravitationalConstant * primary.Mass / distance) * GravitationalConstantDecimalFix);
return(requiredTangentialSpeedFixed);
}
// Methods
public void AdvanceMovement(double timeInSeconds)
{
AstronomicalBody dummyBody = new AstronomicalBody(this.Center, this.Mass, this.Radius, this.Velocity, this.Name);
Physics.AdvanceMovementOfBody(ref dummyBody, timeInSeconds);
this.Center = dummyBody.Center;
}
public void ApplyForce(Vector force, double secondsUnderForce)
{
AstronomicalBody dummyBody = new AstronomicalBody(this.Center, this.Mass, this.Radius, this.Velocity, this.Name);
Physics.ApplyForceToBody(ref dummyBody, force, secondsUnderForce);
this.Center = dummyBody.Center;
this.Velocity = dummyBody.Velocity;
}
public static AstronomicalBody AdvanceMovementOfBody(ref AstronomicalBody body, double timeInSeconds)
{
double resultingX = body.Center.X + (body.Velocity.X * timeInSeconds);
double resultingY = body.Center.Y + (body.Velocity.Y * timeInSeconds);
double resultingZ = body.Center.Z + (body.Velocity.Z * timeInSeconds);
Point newCenter = new Point(resultingX, resultingY, resultingZ);
body.Center = newCenter;
return(new AstronomicalBody(body));
}
public static double GetGravitationalForceMagnitude(AstronomicalBody body1, AstronomicalBody body2)
{
double distance = GetDistanceBetweenPoints(body1.Center, body2.Center);
double resultNotFixed = GravitationalConstant *
(body1.Mass * body2.Mass) /
(distance * distance);
double result = resultNotFixed * GravitationalConstantDecimalFix;
return(result);
}
public static Vector GetFinalVelocityVectorFromForce(
AstronomicalBody body,
Vector forceVector,
double secondsUnderForce)
{
Vector accelerationVector = GetAccelerationVector(body, forceVector);
Vector velocityVector = GetFinalVelocityVectorFromAcceleration(
body, accelerationVector, secondsUnderForce);
return(velocityVector);
}
public static Vector GetFinalVelocityVectorFromAcceleration(
AstronomicalBody body,
Vector accelerationVector,
double secondsUnderAcceleration)
{
Vector startingVelocity = body.Velocity;
Vector deltaVelocity = accelerationVector * secondsUnderAcceleration;
Vector finalVelocity = startingVelocity + deltaVelocity;
return(finalVelocity);
}
public static Vector GetGravitationalForceVector(AstronomicalBody body1, AstronomicalBody body2)
{
double forceMagnitude = GetGravitationalForceMagnitude(body1, body2);
Vector prototypeVector = new Vector(new Point(
body2.Center.X - body1.Center.X,
body2.Center.Y - body1.Center.Y,
body2.Center.Z - body1.Center.Z));
prototypeVector.Length = forceMagnitude;
return(prototypeVector);
}
public static AstronomicalBody ApplyForceToBody(ref AstronomicalBody body, Vector force, double secondsUnderForce)
{
Vector startingVelocity = new Vector(body.Velocity);
Vector finalVelocityFromForce = GetFinalVelocityVectorFromForce(body, force, secondsUnderForce);
Vector averageVelocity = Vector.GetAverage(new List <Vector> {
startingVelocity, finalVelocityFromForce
});
body.Velocity = averageVelocity;
AdvanceMovementOfBody(ref body, secondsUnderForce);
body.Velocity = finalVelocityFromForce;
return(body);
}
public static void EnterOrbitByGivenSpeed <T>(ref T satellite, AstronomicalBody primary, double relativeTangentialSpeed, double coveredAngle
/*Vector orbitAxis, double StartingPointOffset*/) where T : AstronomicalBody, new()
{
// startingPointOffset == 0 => point with the highest x
// orbit axis - right hand rule
// TODO: Implement orbital axis and startingPointOffset
double radius = GetRadiusOfOrbit(satellite, primary, relativeTangentialSpeed);
satellite.Center = new Point(
primary.Center.X + (radius * Math.Cos(coveredAngle)),
primary.Center.Y + (radius * Math.Sin(coveredAngle)),
primary.Center.Z);
Vector satelliteRelativeVelocity = new Vector(relativeTangentialSpeed, Math.PI / 2, (Math.PI / 2) + coveredAngle);
if (satellite is Moon)
{
satelliteRelativeVelocity = satelliteRelativeVelocity.GetOpposite();
}
Vector satelliteAbsoluteVelocity = satelliteRelativeVelocity + primary.Velocity;
satellite.Velocity = satelliteAbsoluteVelocity;
}
public static Vector GetAccelerationVector(AstronomicalBody body, Vector forceVector)
{
Vector resultingVector = forceVector / body.Mass;
return(resultingVector);
}
public AstronomicalBody(AstronomicalBody body)
: this(body.Center, body.Mass, body.Radius, body.Velocity, body.Name)
{
}
