bool LambertSolutionExists()
{
// Make local copies of departure and arrival orbits.
OrbitData earthCopy = null;
OrbitData asteroidCopy = null;
foreach (Body body in Bodies)
{
if (body.tag == "Earth")
{
earthCopy = new OrbitData(body.Orbit);
}
else if (body.tag == "Asteroid")
{
asteroidCopy = new OrbitData(body.Orbit);
}
}
// Advance orbits to epoch of impact for Lambert solver
earthCopy.Epoch = ImpactEpoch;
asteroidCopy.Epoch = ImpactEpoch;
// Get the transfer orbit and C3 from the Lambert solution
LambertSolution lambertSolution = Lambert.GetTransferOrbit(earthCopy, asteroidCopy, TimeOfDeflection, TransferTime, -1);
if (lambertSolution == null)
{
Debug.Log("No Lambert solution found\nTry different mission values.");
ShowInfeasibleLaunchWindow();
return(false);
}
if (lambertSolution.C3 <= 0.0)
{
Debug.Log("Lambert solution requires negative C3");
ShowInfeasibleLaunchWindow();
return(false);
}
double deliverableMass = LaunchVehicleType.ComputeDeliverableMass(lambertSolution.C3, NumLaunches * EffectMultiplier);
if (deliverableMass <= 0.0)
{
Debug.LogFormat("Launch C3 = {0:F4}\nLaunch Vehicle unable to obtain required launch energy",
lambertSolution.C3);
ShowInfeasibleLaunchWindow();
return(false);
}
Debug.LogFormat("Launch C3 = {0:F4}Impact Mass = {1:F4}; Impact Vel. = {2:E4}",
lambertSolution.C3, MassKI, lambertSolution.arrDV.magnitude);
SetMissionValuesText(deliverableMass, lambertSolution.C3, lambertSolution.arrDV.magnitude);
return(true);
}
/// <summary>
/// Launches a spacecraft from Earth to intercept/deflect the asteroid.
/// </summary>
public void LaunchSpacecraft()
{
// Make local copies of departure and arrival orbits.
OrbitData earth = null;
OrbitData asteroid = null;
foreach (Body body in Bodies)
{
if (body.tag == "Earth")
{
earth = new OrbitData(body.Orbit);
}
else if (body.tag == "Asteroid")
{
asteroid = new OrbitData(body.Orbit);
}
}
if (earth == null || asteroid == null)
{
Debug.LogError("Error finding departure/arrival orbits from bodies list by tag");
return;
}
// Advance orbits to epoch of impact for Lambert solver
earth.Epoch = ImpactEpoch;
asteroid.Epoch = ImpactEpoch;
// Get the transfer orbit and C3 from the Lambert solution
LambertSolution lambertSolution = Lambert.GetTransferOrbit(earth, asteroid, TimeOfDeflection, TransferTime, -1);
if (lambertSolution == null || lambertSolution.C3 <= 0.0)
{
DisplayTextWithFadeEffect(MessageText, "No Lambert solution found");
return;
}
// MassKI calculated here will be used in ProcessCollisionEnter
MassKI = LaunchVehicleType.ComputeDeliverableMass(lambertSolution.C3, NumLaunches * EffectMultiplier);
if (MassKI <= 0.0)
{
DisplayTextWithFadeEffect(MessageText, string.Format("Launch vehicle unable to achieve C3 {0:E3} (km/s)^2", lambertSolution.C3));
return;
}
// TODO: Initialize spacecraft from prefab here
//GameObject prefab = Instantiate(Resources.Load("Spacecraft.prefab", typeof(GameObject)) as GameObject);
Body spacecraft = spacecraftObject.GetComponent <Body>();
if (spacecraft == null)
{
Debug.LogError("Instantiated spacecraft prefab does not have Body component");
}
spacecraft.InitOrbit(lambertSolution.TransferOrbit);
spacecraft.SetImpactEpoch(ImpactEpoch - TimeOfDeflection);
spacecraft.gameObject.SetActive(true);
Bodies = FindObjectsOfType <Body>(); // Update bodies list
string message = string.Format("Launch successful!\nC3 = {0:F3} (km/s)^2\nMass = {1:F1} kg", lambertSolution.C3, MassKI);
DisplayTextWithFadeEffect(MessageText, message);
}
