public void RendezvousToggleChanged(bool value)
{
HohmannXfer hohmannXfer = (HohmannXfer)transfer;
transfer = hohmannXfer.CreateTransferCopy(rendezvousToggle.isOn);
UpdateUI(transfer);
}
/// <summary>
/// Callback to compute the launch transfer times and display them in the scene.
/// </summary>
public void Compute()
{
int itemNo = destDropdown.value;
NBody toNbody = destinations[itemNo].GetComponent <NBody>();
OrbitData fromOrbit = new OrbitData();
fromOrbit.SetOrbit(fromNbody, centerNbody);
OrbitData toOrbit = new OrbitData();
toOrbit.SetOrbit(toNbody, centerNbody);
HohmannXfer hohmannXfer = new HohmannXfer(fromOrbit, toOrbit, true);
// Find launch windows
double[] times = hohmannXfer.LaunchTimes(numWindows);
List <Dropdown.OptionData> items = new List <Dropdown.OptionData>();
foreach (double t in times)
{
Dropdown.OptionData item = new Dropdown.OptionData();
item.text = GravityScaler.GetWorldTimeFormatted(t, GravityScaler.Units.SOLAR);
items.Add(item);
}
launchTimes.ClearOptions();
launchTimes.AddOptions(items);
}
/// <summary>
/// Raise a circular orbit by the specified percent
/// - only on-rail is implemented
/// </summary>
/// <param name="percentRaise"></param>
private void NewCircularOrbit(float percentRaise)
{
if (onRails)
{
KeplerSequence keplerSeq = spaceship.GetComponent <KeplerSequence>();
OrbitUniversal orbitU = keplerSeq.GetCurrentOrbit();
// check orbit is circular
if (orbitU.eccentricity < 1E-2)
{
// circular, ok to proceed
OrbitData fromOrbit = new OrbitData(orbitU);
OrbitData toOrbit = new OrbitData(fromOrbit);
toOrbit.a = percentRaise * fromOrbit.a;
const bool rendezvous = false;
OrbitTransfer hohmannXfer = new HohmannXfer(fromOrbit, toOrbit, rendezvous);
keplerSeq.RemoveFutureSegments();
keplerSeq.AddManeuvers(hohmannXfer.GetManeuvers());
}
}
else
{
// assume we're in orbit around the moon
OrbitData orbitData = new OrbitData();
orbitData.SetOrbitForVelocity(spaceship, moonBody);
OrbitData toOrbit = new OrbitData(orbitData);
toOrbit.a = percentRaise * orbitData.a;
const bool rendezvous = false;
OrbitTransfer hohmannXfer = new HohmannXfer(orbitData, toOrbit, rendezvous);
ge.AddManeuvers(hohmannXfer.GetManeuvers());
}
}
/// <summary>
/// Raise a circular orbit by the specified percent
/// - only on-rail is implemented
/// </summary>
/// <param name="percentRaise"></param>
private void NewCircularOrbit(float percentRaise)
{
KeplerSequence keplerSeq = spaceship.GetComponent <KeplerSequence>();
OrbitUniversal orbitU = keplerSeq.GetCurrentOrbit();
// check orbit is circular
if (orbitU.eccentricity < 1E-2)
{
// circular, ok to proceed
OrbitData fromOrbit = new OrbitData(orbitU);
OrbitData toOrbit = new OrbitData(fromOrbit);
toOrbit.a = percentRaise * fromOrbit.a;
const bool rendezvous = false;
OrbitTransfer hohmannXfer = new HohmannXfer(fromOrbit, toOrbit, rendezvous);
keplerSeq.RemoveFutureSegments();
keplerSeq.AddManeuvers(hohmannXfer.GetManeuvers());
}
}
public HohmannXfer CreateTransferCopy(bool rendezvous)
{
HohmannXfer newXfer = new HohmannXfer(this.fromOrbit, this.toOrbit, rendezvous);
return(newXfer);
}
/// <summary>
/// Calculate the transfer maneuver from a circular initial orbit to the sphere of influence (SOI) of a smaller mass
/// orbiting the same body as the spaceship (e.g. Earth to Moon transfer).
///
/// Assumes the moon orbit is spherical and co-planar with the spaceship initial orbit.
///
/// Patched conic is an approximation that assumes the ship moves in only the field of the central body until
/// it gets to the SOI. In reality (and GE evolution) there will be an influence from the Moon and the actual result
/// will differ slightly.
///
/// </summary>
/// <param name="fromOrbit"></param>
/// <param name="toOrbit"></param>
/// <param name="lambda1">Angle of arrival wrt planet-moon line (0..90 degrees)</param>
public PatchedConicXfer(OrbitData fromOrbit, OrbitData toOrbit, double lambda1Deg) : base(fromOrbit, toOrbit)
{
name = "PatchedConicXfer";
// Patched conic xfer is via an ellipse from one circle to another. The ellipse is uniquely
// defined by the radius of from and to.
// Equations from Chobotov Ch 5.4
double r_inner = 0f;
double r_outer = 0f;
if (fromOrbit.a < toOrbit.a)
{
r_inner = fromOrbit.a;
r_outer = toOrbit.a;
}
else
{
r_inner = toOrbit.a;
r_outer = fromOrbit.a;
}
// Start with assumption of xfer from inner more massive to outer
// patched conic follows 7.4 in Fundamentals of Astrodynamics (Bate/Mueller/White) 1971
// Algorithm takes as input (r0, v0, phi0, lambda1)
// and determines r1, v1, delta0, delta1
// See Fig 7.4-1 p336
double D = r_outer - r_inner;
// radius of sphere of influence
double Rs = D * System.Math.Pow(toOrbit.nbody.mass / toOrbit.centralMass.mass, 0.4f);
double lambda1 = Mathf.Deg2Rad * lambda1Deg;
// 1. r0 is given (current circular orbit). Find a v0 that is energetic enough to cross the moons orbit.
// (Can use a non-rdzv Hohmann)
HohmannXfer hohmann = new HohmannXfer(fromOrbit, toOrbit, false);
maneuvers = hohmann.GetManeuvers();
double r0 = r_inner;
double v0 = System.Math.Sqrt(fromOrbit.mu / r0) + maneuvers[0].dV;
// assume we thrust along orbit: phi0 = 0
double E = v0 * v0 / 2f - fromOrbit.mu / r_inner;
double h = v0 * r0; // cos(phi0) = 1
double r1 = System.Math.Sqrt(D * D + Rs * Rs - 2f * D * Rs * System.Math.Cos(lambda1));
// xfer orbit details
double p = h * h / fromOrbit.mu;
double a = -0.5f * fromOrbit.mu / E;
double ecc = System.Math.Sqrt(1 - p / a);
double cos_nu0 = System.Math.Min((p - r0) / (r0 * ecc), 1f);
double cos_nu1 = System.Math.Min((p - r1) / (r1 * ecc), 1f);
// eccentric anomolies
double cos_E0 = (ecc + cos_nu0) / (1 + ecc * cos_nu0);
double E0 = System.Math.Acos(cos_E0); // quadrant issues?
double cos_E1 = (ecc + cos_nu1) / (1 + ecc * cos_nu1);
double E1 = System.Math.Acos(cos_E1); // quadrant issues ?
//Debug.LogFormat("PatchedConic ({0}): p={1} a={2} ecc={3} cos_nu0={4} cos_nu1={5} E0={6} E1={7}",
// lambda1Deg, p, a, ecc, cos_nu0, cos_nu1, E0, E1);
// time of flight
t_flight = System.Math.Sqrt(a * a * a / fromOrbit.mu) * (E1 - ecc * System.Math.Sin(E1)) - (E0 - ecc * System.Math.Sin(E0));
// delta0 is phase angle at departure
double nu0 = System.Math.Acos(cos_nu0);
double nu1 = System.Math.Acos(cos_nu1);
double gamma1 = System.Math.Asin(Rs / r1 * System.Math.Sin(lambda1)); // quadrant?
double w_m = 2f * System.Math.PI / toOrbit.period;
double gamma0 = nu1 - nu0 - gamma1 - w_m * t_flight;
// Debug.LogFormat("PatchedConic: nu0={0} nu1={1} g0(deg)={2} g1(deg)={3}", nu0, nu1, System.Math.Rad2Deg*gamma0, System.Math.Rad2Deg*gamma1);
// gamma0 is the phase delta initial burn needs to have wrt to the phase of body 2
// find current angular seperation
double phase_gap = (toOrbit.phase + toOrbit.omega_lc) - (fromOrbit.phase + fromOrbit.omega_lc);
if (phase_gap < 0)
{
phase_gap += 360f;
}
// need seperation to be delta0
double dTheta = Mathf.Deg2Rad * phase_gap - gamma0;
if (dTheta < 0)
{
dTheta += TWO_PI;
}
// need to wait for phase_gap to reduce to this value. It reduces at a speed based on the difference
// in the angular velocities.
double dOmega = TWO_PI / fromOrbit.period - TWO_PI / toOrbit.period;
double tWait = dTheta / dOmega;
// Debug.LogFormat("PatchedConic: r1={0} E={1} t_flight={2} delta0={3} tWait={4}", r1, E, t_flight, delta0, tWait);
// adjust time of the first Hohmann burn
maneuvers[0].worldTime += (float)tWait;
// remove the second maneuver to allow PatchedConicSOI to trigger when it detects SOI
maneuvers.RemoveAt(1);
}