private void ComputeTransfer()
{
Vector3d r_from = GravityEngine.Instance().GetPositionDoubleV3(spaceship);
Vector3d r_to = new Vector3d(targetPoint.transform.position);
OrbitData shipOrbit = new OrbitData();
shipOrbit.SetOrbitForVelocity(spaceship, centralMass);
// compute the min energy path (this will be in the short path direction)
lambertU = new LambertUniversal(shipOrbit, r_from, r_to, shortPath);
// apply any time of flight change
double t_flight = tflightFactor * lambertU.GetTMin();
bool reverse = !shortPath;
const bool df = false;
const int nrev = 0;
int error = lambertU.ComputeXfer(reverse, df, nrev, t_flight);
if (error != 0)
{
Debug.LogWarning("Lambert failed to find solution.");
maneuverSegment.gameObject.SetActive(false);
return;
}
Vector3 dv = lambertU.GetTransferVelocity() - GravityEngine.Instance().GetVelocity(spaceship);
dvText.text = string.Format("dV = {0:00.00} Time={1:00.00}", dv.magnitude, t_flight);
maneuverOrbitPredictor.SetVelocity(lambertU.GetTransferVelocity());
maneuverSegment.gameObject.SetActive(true);
maneuverSegment.SetDestination(r_to.ToVector3());
maneuverSegment.SetVelocity(lambertU.GetTransferVelocity());
}
private void ComputeTransfer()
{
shipData = new OrbitData();
shipData.centralMass = starNBody;
shipData.SetOrbitForVelocity(spaceshipNBody, starNBody);
targetData = new OrbitData(targetEllipses[selectedEllipse].orbitData);
targetData.phase = targetEllipses[selectedEllipse].manueverPhase;
// compute the min energy path (this will be in the short path direction)
lambertU = new LambertUniversal(shipData, targetData, shortPath);
// apply any time of flight change
transferTime = tflightFactor * lambertU.GetTMin();
bool reverse = !shortPath;
// recompute with updated time
const bool df = false;
const int nrev = 0;
int error = lambertU.ComputeXfer(reverse, df, nrev, transferTime);
if (error != 0)
{
Debug.LogWarning("Lambert failed to find solution.");
maneuverSegment.gameObject.SetActive(false);
return;
}
Vector3 vel = lambertU.GetTransferVelocity();
maneuverOrbitPredictor.SetVelocity(vel);
maneuverSegment.SetVelocity(vel);
maneuverOrbitPredictor.gameObject.SetActive(true);
maneuverSegment.gameObject.SetActive(true);
}
private void DoTestForPhase(double fromPhase, double toPhase)
{
const float mass = 1000f;
const bool reverse = false;
GameObject star = TestSetupUtils.CreateNBody(mass, new Vector3(0, 0, 0));
NBody starNbody = star.GetComponent <NBody>();
float orbitRadius = 20f;
GameObject planet = TestSetupUtils.CreatePlanetInOrbitUniversal(starNbody, 0f, orbitRadius);
OrbitUniversal orbitU = planet.GetComponent <OrbitUniversal>();
orbitU.phase = fromPhase;
orbitU.SetMajorAxisInspector(orbitRadius);
orbitRadius = 30.0f;
GameObject planet2 = TestSetupUtils.CreatePlanetInOrbitUniversal(starNbody, 0f, orbitRadius);
OrbitUniversal orbitU2 = planet2.GetComponent <OrbitUniversal>();
orbitU2.phase = toPhase;
orbitU2.SetMajorAxisInspector(orbitRadius);
GravityEngine.Instance().UnitTestAwake();
GravityEngine.Instance().AddBody(star);
GravityEngine.Instance().AddBody(planet);
GravityEngine.Instance().AddBody(planet2);
GravityEngine.Instance().Setup();
Debug.Log("Find transfers");
OrbitData fromOrbit = new OrbitData(orbitU);
OrbitData toOrbit = new OrbitData(orbitU2);
LambertUniversal lambertU = new LambertUniversal(fromOrbit, toOrbit, true);
Assert.AreNotEqual(lambertU, null);
double time = 0.8f * lambertU.GetTMin();
lambertU.ComputeXfer(reverse, false, 0, time);
LambertBattin lambertB = new LambertBattin(fromOrbit, toOrbit);
int error = lambertB.ComputeXfer(reverse, false, 0, time);
Assert.AreEqual(error, 0);
Assert.AreNotEqual(lambertB, null);
Assert.AreNotEqual(lambertB.GetTransferVelocity(), null);
Debug.LogFormat("initial velocity {0} vs {1}", lambertU.GetTransferVelocity(), lambertB.GetTransferVelocity());
Debug.LogFormat("initial velocity mag {0} vs {1}",
lambertU.GetTransferVelocity().magnitude, lambertB.GetTransferVelocity().magnitude);
Debug.LogFormat("final velocity {0} vs {1}", lambertU.GetFinalVelocity(), lambertB.GetFinalVelocity());
Debug.LogFormat("final velocity mag {0} vs {1}",
lambertU.GetFinalVelocity().magnitude, lambertB.GetFinalVelocity().magnitude);
// best can do for 180 degree case is E-2 accuracy on the magnitude. Not sure why...seems too big
Assert.IsTrue(GEUnit.DoubleEqual(lambertU.GetTransferVelocity().magnitude,
lambertB.GetTransferVelocity().magnitude,
1E-2));
}
private void ExecuteTransfer()
{
// Need to account for phasing, rotate ship forward to correct launch point and
// rotate TLI vector. (This assumes circular orbit in the XY plane with the planet at the origin!)
// Should set as a maneuver, but just jump there for demonstration code
double transferTime = tflightFactor * lambertU.GetTMin();
float moonOmega = (float)System.Math.Sqrt(ge.GetMass(planet)) / Mathf.Sqrt(moonRadius * moonRadius * moonRadius);
float shipThetaDeg = (float)(transferTime * moonOmega) * Mathf.Rad2Deg;
Debug.LogFormat("t={0} theta={1} deg. omega={2} rad", transferTime, shipThetaDeg, moonOmega);
// Inclination support. Recompute the transfer using inclination
// @TODO: HACK XY only
Vector3 shipPos = ge.GetPhysicsPosition(spaceship);
Vector3 shipPosPhased = Quaternion.AngleAxis(shipThetaDeg, Vector3.forward) * shipPos;
Vector3 shipVelPhased = Quaternion.AngleAxis(shipThetaDeg, Vector3.forward) * lambertU.GetTransferVelocity();
if (onRails)
{
TransferOnRails(transferTime, shipPosPhased, shipVelPhased, moonOmega);
}
else
{
Debug.LogFormat("tli NBody mode r={0} v={1}", shipPosPhased, shipVelPhased);
ge.UpdatePositionAndVelocity(spaceship, shipPosPhased, shipVelPhased);
}
// remove placeholder ships/orbit visualizers
ge.RemoveBody(shipExitSOI.gameObject);
shipExitSOI.gameObject.SetActive(false);
ge.RemoveBody(shipEnterSOI.gameObject);
shipEnterSOI.gameObject.SetActive(false);
SetOrbitDisplays(false);
ge.SetEvolve(true);
running = true;
}
/// <summary>
/// Computes the transfer with the moon on the +X axis without accounting for the moon motion during
/// transit. (That is accounted for in the ExecuteTransfer routine).
///
/// This allows a co-rotating visualization of the orbit.
/// </summary>
/// <returns></returns>
private Vector3 ComputeTransfer()
{
OrbitData shipOrbit = new OrbitData();
shipOrbit.SetOrbitForVelocity(spaceship, planet);
// compute the min energy path (this will be in the short path direction)
lambertU = new LambertUniversal(shipOrbit, startPoint, targetPoint, shortPath);
// apply any time of flight change
double t_flight = tflightFactor * lambertU.GetTMin();
bool reverse = !shortPath;
const bool df = false;
const int nrev = 0;
int error = lambertU.ComputeXfer(reverse, df, nrev, t_flight);
if (error != 0)
{
Debug.LogWarning("Lambert failed to find solution.");
aroundMoonSegment.gameObject.SetActive(false);
return(Vector3.zero);
}
// Check Lambert is going in the correct direction
Vector3 shipOrbitAxis = Vector3.Cross(ge.GetVelocity(spaceship), ge.GetPhysicsPosition(spaceship)).normalized;
Vector3 tliOrbitAxis = Vector3.Cross(lambertU.GetTransferVelocity(), startPoint.ToVector3());
if (Vector3.Dot(shipOrbitAxis, tliOrbitAxis) < 0)
{
error = lambertU.ComputeXfer(!reverse, df, nrev, t_flight);
if (error != 0)
{
Debug.LogWarning("Lambert failed to find solution for reverse path. error=" + error);
return(Vector3.zero);
}
}
Vector3 tliVelocity = lambertU.GetTransferVelocity();
toMoonOrbit.SetVelocity(tliVelocity);
toMoonSegment.SetVelocity(tliVelocity);
aroundMoonSegment.gameObject.SetActive(true);
// Set velocity for orbit around moon
Vector3 soiEnterVel = lambertU.GetFinalVelocity();
aroundMoonSegment.SetVelocity(soiEnterVel);
// update shipEnterSOI object
ge.UpdatePositionAndVelocity(shipEnterSOI, targetPoint.ToVector3(), soiEnterVel);
// Find the orbit around the moon. By using the mirror position we're assuming it's
// a hyperbola (since there is no course correction at SOI this is true).
// (Moon is in correct position for these calcs so can use world positions, relativePos=false)
Vector3d soiEnterV = new Vector3d(lambertU.GetFinalVelocity());
OrbitUtils.OrbitElements oe = OrbitUtils.RVtoCOE(targetPoint, soiEnterV, moonBody, false);
Vector3d soiExitR = new Vector3d();
Vector3d soiExitV = new Vector3d();
OrbitUtils.COEtoRVMirror(oe, moonBody, ref soiExitR, ref soiExitV, false);
// Set position and vel for exit ship, so exit orbit predictor can run. Moon offset/vel already added.
ge.SetPositionDoubleV3(shipExitSOI, soiExitR);
ge.SetVelocityDoubleV3(shipExitSOI, soiExitV);
aroundMoonSegment.UpdateOrbit();
return(tliVelocity);
}