public LambertBattin(OrbitData _fromOrbit, OrbitData _toOrbit) : base(_fromOrbit, _toOrbit)
{
name = "LambertBattin";
// Fundamentals of Astrodynamics and Applications, Vallado, 4th Ed., Algorithm 56 p475
// Take r0, r => a_min, e_min, t_min, v0
GravityEngine ge = GravityEngine.Instance();
// If Nbody is available get position directly. If not (target marker) then
// use orbit phase to compute position
center3d = ge.GetPositionDoubleV3(_fromOrbit.centralMass);
if (fromOrbit.nbody != null)
{
r1 = ge.GetPositionDoubleV3(fromOrbit.nbody);
r1crossv1 = _fromOrbit.GetAxis();
}
else
{
r1 = new Vector3d(toOrbit.GetPhysicsPositionforEllipse(fromOrbit.phase));
Debug.LogError("Code incomplete need to get v1");
}
if (toOrbit.nbody != null)
{
r2 = ge.GetPositionDoubleV3(toOrbit.nbody);
}
else
{
r2 = new Vector3d(toOrbit.GetPhysicsPositionforEllipse(toOrbit.phase));
}
r1 = r1 - center3d;
r2 = r2 - center3d;
if (fromOrbit.a < toOrbit.a)
{
innerOrbit = fromOrbit;
outerOrbit = toOrbit;
innerToOuter = true;
}
else
{
innerOrbit = toOrbit;
outerOrbit = fromOrbit;
innerToOuter = false;
}
fromNBody = fromOrbit.nbody;
mu = ge.GetPhysicsMass(fromOrbit.centralMass);
}
public LambertBattin(NBody fromBody, NBody centerNBody, Vector3d r_from, Vector3d r_to, Vector3d fromAxis) : base()
{
name = "LambertBattin";
fromNBody = fromBody;
GravityEngine ge = GravityEngine.Instance();
centerBody = centerNBody;
center3d = ge.GetPositionDoubleV3(centerNBody);
mu = ge.GetPhysicsMass(centerNBody);
r1 = r_from - center3d;
r1crossv1 = fromAxis;
r2 = r_to - center3d;
innerOrbit = fromOrbit;
innerToOuter = true;
}
/// <summary>
/// Create a Lambert transfer from a given NBody orbit to a position in physics space.
///
/// The constructor will compute the minimum energy transfer to the point taking the shortest
/// path setting into account. The time for the transfer can then be retreived.
/// </summary>
/// <param name="_fromOrbit"></param>
/// <param name="r_from"></param>
/// <param name="r_to"></param>
/// <param name="shortPath"></param>
public LambertUniversal(OrbitData _fromOrbit, Vector3d r_from, Vector3d r_to, bool shortPath) : base(_fromOrbit)
{
name = "LambertUniversal";
GravityEngine ge = GravityEngine.Instance();
center3d = ge.GetPositionDoubleV3(centerBody);
r1 = r_from - center3d;
r2 = r_to - center3d;
fromOrbit = _fromOrbit;
innerOrbit = fromOrbit;
innerToOuter = true;
mu = ge.GetPhysicsMass(fromOrbit.centralMass);
// determine t_min.
double[] r0 = new double[] { r1.x, r1.y, r1.z };
double[] r = new double[] { r2.x, r2.y, r2.z };
ComputeMinTime(ref r0, ref r, _fromOrbit.centralMass, shortPath);
}
/// <summary>
/// Setup for Lambert Universal construction. Calculation is done via ComputeXfer and may be
/// done more than once for different transit times.
///
/// Initial conditions are passed in when created.
///
/// The transfer assumes there is an active NBody at the fromOrbit to be maneuvered to the
/// orbit specified by the toOrbit. One of the from/to orbit data elements must have a
/// centerNBody.
///
/// </summary>
/// <param name="fromOrbit"></param>
/// <param name="toOrbit"></param>
/// <param name="shortPath">Take shortest path along the ellipse (if xfer is an ellipse)</param>
public LambertUniversal(OrbitData _fromOrbit, OrbitData _toOrbit, bool shortPath) : base(_fromOrbit, _toOrbit)
{
name = "LambertUniversal";
// Fundamentals of Astrodynamics and Applications, Vallado, 4th Ed., Algorithm 56 p475
// Take r0, r => a_min, e_min, t_min, v0
double[] r1_array = new double[] { 0, 0, 0 };
double[] r2_array = new double[] { 0, 0, 0 };
double[] center = new double[] { 0, 0, 0 };
GravityEngine ge = GravityEngine.Instance();
// If Nbody is available get position directly. If not (target marker) then
// use orbit phase to compute position
ge.GetPositionDouble(centerBody, ref center);
center3d = new Vector3d(ref center);
if (fromOrbit.nbody != null)
{
ge.GetPositionDouble(fromOrbit.nbody, ref r1_array);
}
else
{
Vector3 pos = toOrbit.GetPhysicsPositionforEllipse(fromOrbit.phase);
r1_array = new double[] { pos.x, pos.y, pos.z };
}
if (toOrbit.nbody != null)
{
ge.GetPositionDouble(toOrbit.nbody, ref r2_array);
}
else
{
Vector3 pos = toOrbit.GetPhysicsPositionforEllipse(toOrbit.phase);
r2_array = new double[] { pos.x, pos.y, pos.z };
}
r1 = new Vector3d(ref r1_array) - center3d;
r2 = new Vector3d(ref r2_array) - center3d;
if (fromOrbit.a < toOrbit.a)
{
innerOrbit = fromOrbit;
outerOrbit = toOrbit;
innerToOuter = true;
}
else
{
innerOrbit = toOrbit;
outerOrbit = fromOrbit;
innerToOuter = false;
}
mu = ge.GetPhysicsMass(fromOrbit.centralMass);
// determine t_min.
// If Nbody is available get position directly. If not (target marker) then
// use orbit phase to compute position
double[] r0 = new double[] { 0, 0, 0 };
double[] r = new double[] { 0, 0, 0 };
if (innerOrbit.nbody != null)
{
ge.GetPositionDouble(innerOrbit.nbody, ref r0);
}
else
{
Vector3 pos = toOrbit.GetPhysicsPositionforEllipse(innerOrbit.phase);
r0 = new double[] { pos.x, pos.y, pos.z };
}
if (outerOrbit.nbody != null)
{
ge.GetPositionDouble(outerOrbit.nbody, ref r);
}
else
{
Vector3 pos = toOrbit.GetPhysicsPositionforEllipse(outerOrbit.phase);
r = new double[] { pos.x, pos.y, pos.z };
}
ComputeMinTime(ref r0, ref r, fromOrbit.centralMass, shortPath);
}
