//---------------------------------------------------------------------
//
//---------------------------------------------------------------------
public static bool get_launch_params(CelestialBody depBody,
ref DepManuever manuever)
{
BodyData depData = new BodyData();
depBody.get_data(ref depData);
double mu = depData.gravParameter;
double R = depData.radius;
double r0 = R + manuever.h;
double vk = Math.Sqrt(mu / r0);
double i = manuever.orbit.i * math.RAD;
double Omega = manuever.orbit.Omega * math.RAD;
if (i < Math.Abs(manuever.launchLat))
return false;
double sin_A = Math.Cos(i)/Math.Cos(manuever.launchLat);
double A = Math.Asin(sin_A);
double ny = -Math.Cos(A);
double nz = sin_A;
double D = ny * ny + nz * nz * Math.Pow(Math.Sin(manuever.launchLat), 2);
double sin_d = -(nz * Math.Cos(Omega) * Math.Sin(manuever.launchLat) + ny * Math.Sin(Omega)) * Math.Sin(i) / D;
double cos_d = (nz * Math.Sin(Omega) * Math.Sin(manuever.launchLat) - ny * Math.Cos(Omega)) * Math.Sin(i) / D;
double d = math.arg(sin_d, cos_d);
double rotAngle_ref = d - manuever.launchLon;
double omega = 2 * Math.PI / depData.rotationPeriod;
double rotAngle = depBody.get_rotation_angle(manuever.startTime)*math.RAD;
double dT = 0;
if (rotAngle >= rotAngle_ref)
{
dT = (rotAngle - rotAngle_ref) / omega;
}
else
{
dT = 21600 - (rotAngle_ref - rotAngle) / omega;
}
manuever.launchTime = manuever.startTime - dT;
KCalendar.sec_to_date(manuever.launchTime, ref manuever.launchDate);
// Debug
rotAngle = depBody.get_rotation_angle(manuever.launchTime)*math.RAD;
// Relative azimuth calculation
double vs = omega*R*Math.Cos(manuever.launchLat);
double sin_Ar = (vk * sin_A - vs) / Math.Sqrt(vk * vk + vs * vs - 2 * vk * vs * sin_A);
manuever.azimuth = Math.Asin(sin_Ar) / math.RAD;
return true;
}
//---------------------------------------------------------------------
// Transfer dV calculation
//---------------------------------------------------------------------
public static void get_depatrure_manuever(CelestialBody depBody,
CelestialBody craft,
double t1,
ref DepManuever manuever)
{
OrbitPos depPos = new OrbitPos();
depBody.get_position(t1, ref depPos);
// Calculation SOI departure velocity
Vector3D Vd = depBody.get_velocity(depPos.theta);
Vector3D Vc = craft.get_velocity(0);
Vector3D Vro = Vc - Vd;
double v_ro = Vro.lenght();
// Depatrure hyperbolic orbit calculation
Vector3D x1 = depBody.get_cartesian_pos(depPos.theta);
double u = 0;
get_transfer_orientation(x1, Vro, ref manuever.orbit.i, ref manuever.orbit.Omega, ref u);
if (manuever.orbit.i > 90.0)
{
manuever.orbit.i = 180.0 - manuever.orbit.i;
manuever.orbit.Omega += 180.0;
if (manuever.orbit.Omega > 360)
manuever.orbit.Omega -= 360;
}
// Eject dV calculation
BodyData depData = new BodyData();
depBody.get_data(ref depData);
double ro = depData.sphereOfInfluence;
double R = depData.radius;
double mu = depData.gravParameter;
double h = manuever.h;
double v0 = Math.Sqrt(2 * mu * (1 / (R + h) - 1 / ro) + v_ro * v_ro);
manuever.dv = v0 - Math.Sqrt(mu / (R + h));
// Time of hyperbolic departure calculation
double vk = Math.Sqrt(mu / (R + h));
manuever.orbit.e = (v0 * v0 / vk / vk - 1);
double p = (R + h) * (1 + manuever.orbit.e);
double cos_theta = (p / ro - 1) / manuever.orbit.e;
double theta = Math.Acos(cos_theta);
manuever.orbit.a = p / (manuever.orbit.e * manuever.orbit.e - 1);
double n = Math.Sqrt(mu / manuever.orbit.a) / manuever.orbit.a;
double thH2 = Math.Sqrt((manuever.orbit.e - 1) / (manuever.orbit.e + 1)) * Math.Tan(theta / 2);
double H = Math.Log((1 + thH2) / (1 - thH2));
double M = manuever.orbit.e * Math.Sinh(H) - H;
double dT = M / n;
manuever.orbit.omega = (Math.Acos(1/manuever.orbit.e) - Math.PI/2) / math.RAD;
// Low orbit wait time calculation
double waitTime = manuever.turns * 2 * Math.PI * (R + h) / vk;
manuever.ejectTime = t1 - dT;
manuever.startTime = t1 - dT - waitTime;
KCalendar.sec_to_date(manuever.ejectTime, ref manuever.ejectDate);
KCalendar.sec_to_date(manuever.startTime, ref manuever.startDate);
}
//---------------------------------------------------------------------
//
//---------------------------------------------------------------------
private void buttonHomanSearch_Click(object sender, EventArgs e)
{
double t0 = KCalendar.date_to_sec(int.Parse(textBeginYear.Text.ToString()),
int.Parse(comboBeginDay.Text.ToString()),
int.Parse(comboBeginHour.Text.ToString()),
int.Parse(comboBeginMin.Text.ToString()),
int.Parse(comboBeginSec.Text.ToString()));
double t1 = KCalendar.date_to_sec(int.Parse(textEndYear.Text.ToString()),
int.Parse(comboEndDay.Text.ToString()),
int.Parse(comboEndHour.Text.ToString()),
int.Parse(comboEndMin.Text.ToString()),
int.Parse(comboEndSec.Text.ToString()));
int dep_idx = get_body_index(comboHomanArrivList.Text.ToString());
int arr_idx = get_body_index(comboHomanDepList.Text.ToString());
// Check same reference body!!!
if (Bodies[dep_idx].get_ref_body() != Bodies[arr_idx].get_ref_body())
{
labelNoTransfer.Text = "Bodies must have same reference body!\nPlease, change other bodies";
return;
}
Transfer trans = new Transfer();
double psi = Convert.ToDouble(textPsi.Text) * RAD;
bool ready = Lambert.get_transfer_date(t0, t1, Bodies[dep_idx], Bodies[arr_idx], psi, ref trans);
if (!ready)
{
panelHomanRes.Visible = false;
labelNoTransfer.Text = "Transfer is imposible in changed period";
return;
}
labelNoTransfer.Text = "";
panelHomanRes.Visible = true;
KDate deltaDate = new KDate();
KCalendar.DeltaDate(trans.arrivTime - trans.depTime, ref deltaDate);
labelArivDate.Text = trans.depDate.year.ToString() + "y " +
trans.depDate.day.ToString() + "d " +
trans.depDate.hour.ToString() + "h " +
trans.depDate.min.ToString() + "m " +
trans.depDate.sec.ToString() + "s";
labelDepDate.Text = trans.arrivDate.year.ToString() + "y " +
trans.arrivDate.day.ToString() + "d " +
trans.arrivDate.hour.ToString() + "h " +
trans.arrivDate.min.ToString() + "m " +
trans.arrivDate.sec.ToString() + "s";
labelTransTime.Text = deltaDate.year.ToString() + "y " +
deltaDate.day.ToString() + "d " +
deltaDate.hour.ToString() + "h " +
deltaDate.min.ToString() + "m " +
deltaDate.sec.ToString() + "s";
labelSmiMajorAxis.Text = Math.Round(trans.orbit.a, 0).ToString() + " m";
labelEccentricity.Text = Math.Round(trans.orbit.e, 4).ToString();
labelInclination.Text = Math.Round(trans.orbit.i, 4).ToString() + " deg";
labelLAN.Text = Math.Round(trans.orbit.Omega, 4).ToString() + " deg";
labelArgPe.Text = Math.Round(trans.orbit.omega, 4).ToString() + " deg";
CelestialBody craft = new CelestialBody();
BodyData craft_data = new BodyData();
craft_data.name = "Space craft";
craft_data.orbit = trans.orbit;
craft.set_data(ref craft_data);
craft.set_refGravParameter(Bodies[dep_idx].get_refGravParameter());
DepManuever manuever = new DepManuever();
manuever.h = double.Parse(textAltitude.Text)*1000.0;
manuever.turns = int.Parse(textWaitTurns.Text);
Lambert.get_depatrure_manuever(Bodies[dep_idx],
craft,
trans.depTime,
ref manuever);
labelDeltaV.Text = Math.Round(manuever.dv, 2).ToString();
labelInc.Text = Math.Round(manuever.orbit.i, 4).ToString();
labelStartLAN.Text = Math.Round(manuever.orbit.Omega, 4).ToString();
labelEjectDate.Text = manuever.ejectDate.year.ToString() + "y " +
manuever.ejectDate.day.ToString() + "d " +
manuever.ejectDate.hour.ToString() + "h " +
manuever.ejectDate.min.ToString() + "m " +
manuever.ejectDate.sec.ToString() + "s";
double latDeg = double.Parse(textLatDeg.Text);
double latMin = double.Parse(textLatMin.Text);
double latSec = double.Parse(textLatSec.Text);
double lonDeg = double.Parse(textLonDeg.Text);
double lonMin = double.Parse(textLonMin.Text);
double lonSec = double.Parse(textLonSec.Text);
manuever.launchLat = (latDeg + latMin / 60.0 + latSec / 3600.0) * RAD;
manuever.launchLon = (lonDeg + lonMin / 60.0 + lonSec / 3600.0) * RAD;
if (radioButtonSouth.Checked)
manuever.launchLat = -manuever.launchLat;
if (radioButtonWest.Checked)
manuever.launchLon = -manuever.launchLon;
bool flag = Lambert.get_launch_params(Bodies[dep_idx], ref manuever);
if (flag)
{
labelStartDate.Text = manuever.launchDate.year.ToString() + "y " +
manuever.launchDate.day.ToString() + "d " +
manuever.launchDate.hour.ToString() + "h " +
manuever.launchDate.min.ToString() + "m " +
manuever.launchDate.sec.ToString() + "s";
labelAzimuth.Text = Math.Round(manuever.azimuth, 2).ToString();
}
// Draw trajectory
DrawTransOrbit(panelTransOrbit, trans, Bodies[dep_idx], Bodies[arr_idx], craft);
}