//---------------------------------------------------------------------
// 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);
}
//---------------------------------------------------------------------
// Get transfer orbit
//---------------------------------------------------------------------
public static double get_transfer_orbit(double t,
CelestialBody depBody,
CelestialBody arrivBody,
double phi,
ref Orbit orbit,
ref double destLambda)
{
// Is bodies has same reference body
if (depBody.get_ref_body() != arrivBody.get_ref_body())
return -1;
OrbitPos pos = new OrbitPos();
EclipticPos epos = new EclipticPos();
depBody.get_position(t, ref pos);
depBody.get_ecliptic_coords(pos.theta, ref epos);
destLambda = epos.lambda + Math.PI - phi;
destLambda = math.Trunc2PiN(destLambda);
double destTheta = get_dest_theta(arrivBody, destLambda);
Vector3D x1 = depBody.get_cartesian_pos(pos.theta);
Vector3D x2 = arrivBody.get_cartesian_pos(destTheta);
double u = 0;
get_transfer_orientation(x1, x2, ref orbit.i, ref orbit.Omega, ref u);
double r1 = x1.lenght();
double r2 = x2.lenght();
orbit.omega = u / math.RAD;
BodyData data = new BodyData();
arrivBody.get_data(ref data);
double transTime = 0;
double mu = depBody.get_refGravParameter();
double E = 0;
double theta = 0;
theta = x1.angle(x2);
orbit.e = (r2 - r1) / (r1 - r2 * Math.Cos(theta));
if ( (orbit.e > - 1) && (orbit.e < 1) )
{
orbit.a = r1 / (1 - orbit.e);
double n = Math.Sqrt(mu / orbit.a) / orbit.a;
double tgE2 = Math.Sqrt((1 - orbit.e) / (1 + orbit.e)) * Math.Tan(theta / 2);
E = 2 * Math.Atan(tgE2);
double M = E - orbit.e * Math.Sin(E);
transTime = M / n;
}
if (orbit.e == 1)
{
orbit.a = 2*r1;
transTime = r1*Math.Sqrt(2*r1/mu)*(Math.Tan(theta/2) + Math.Pow(Math.Tan(theta/2), 3)/3);
}
if (orbit.e > 1)
{
orbit.a = r1 / (orbit.e - 1);
double n = Math.Sqrt(mu / orbit.a) / orbit.a;
double thE2 = Math.Sqrt((orbit.e - 1) / (orbit.e + 1)) * Math.Tan(theta / 2);
double H = Math.Log((1 + thE2) / (1 - thE2));
double M = orbit.e * Math.Sinh(H) - H;
transTime = M / n;
}
return transTime;
}
//---------------------------------------------------------------------
//
//---------------------------------------------------------------------
public static double LambdaErr(double t,
CelestialBody arivBody,
CelestialBody destBody,
double phi)
{
Orbit orbit = new Orbit();
double destLambda = 0;
double transTime = get_transfer_orbit(t, arivBody, destBody, phi, ref orbit, ref destLambda);
OrbitPos pos = new OrbitPos();
EclipticPos epos = new EclipticPos();
destBody.get_position(t + transTime, ref pos);
destBody.get_ecliptic_coords(pos.theta, ref epos);
return get_phase(epos.lambda - destLambda);
}
//---------------------------------------------------------------------
//
//---------------------------------------------------------------------
void DrawTransOrbit(Panel panel, Transfer trans,
CelestialBody arivBody,
CelestialBody destBody,
CelestialBody craft)
{
Graphics graph = panel.CreateGraphics();
graph.Clear(Color.Black);
Pen pen = new Pen(Color.LightGray, 2.0F);
int width = panel.Width;
int height = panel.Height;
float x0 = width / 2;
float y0 = height / 2;
float x = 0;
float y = 0;
float x1 = 0;
float y1 = 0;
float x2 = 0;
float y2 = 0;
double scale = 0;
int Delta = 25;
BodyData ariv_data = new BodyData();
BodyData dest_data = new BodyData();
arivBody.get_data(ref ariv_data);
destBody.get_data(ref dest_data);
double ariv_ra = ariv_data.orbit.a / (1 - ariv_data.orbit.e);
double dest_ra = dest_data.orbit.a / (1 - dest_data.orbit.e);
double r_max = 0;
if (ariv_ra > dest_ra)
r_max = ariv_ra;
else
r_max = dest_ra;
if (width > height)
{
scale = (height / 2 - Delta) / r_max;
}
else
{
scale = (width / 2 - Delta) / r_max;
}
// Arrive Body orbit
Vector3D pos;
OrbitPos orbit_pos = new OrbitPos();
double V0 = 0;
double V = V0;
double V1 = 360.0;
double dV = 5.0;
while (V <= V1)
{
pos = arivBody.get_cartesian_pos(V * RAD);
x1 = x0 + Convert.ToSingle(scale * pos.x);
y1 = y0 - Convert.ToSingle(scale * pos.y);
V += dV;
pos = arivBody.get_cartesian_pos(V * RAD);
x2 = x0 + Convert.ToSingle(scale * pos.x);
y2 = y0 - Convert.ToSingle(scale * pos.y);
if (pos.z >= 0)
pen.DashStyle = System.Drawing.Drawing2D.DashStyle.Solid;
else
pen.DashStyle = System.Drawing.Drawing2D.DashStyle.Dash;
graph.DrawLine(pen, x1, y1, x2, y2);
}
// Departure Body orbit
V0 = 0;
V = V0;
V1 = 360.0;
dV = 5.0;
while (V <= V1)
{
pos = destBody.get_cartesian_pos(V * RAD);
x1 = x0 + Convert.ToSingle(scale * pos.x);
y1 = y0 - Convert.ToSingle(scale * pos.y);
V += dV;
pos = destBody.get_cartesian_pos(V * RAD);
x2 = x0 + Convert.ToSingle(scale * pos.x);
y2 = y0 - Convert.ToSingle(scale * pos.y);
if (pos.z >= 0)
pen.DashStyle = System.Drawing.Drawing2D.DashStyle.Solid;
else
pen.DashStyle = System.Drawing.Drawing2D.DashStyle.Dash;
graph.DrawLine(pen, x1, y1, x2, y2);
}
V0 = 0;
V = V0;
V1 = Lambert.get_dest_theta(craft, trans.destLambda) / RAD;
dV = 5.0;
pen.Color = Color.Red;
do
{
pos = craft.get_cartesian_pos(V * RAD);
x1 = x0 + Convert.ToSingle(scale * pos.x);
y1 = y0 - Convert.ToSingle(scale * pos.y);
V += dV;
pos = craft.get_cartesian_pos(V * RAD);
x2 = x0 + Convert.ToSingle(scale * pos.x);
y2 = y0 - Convert.ToSingle(scale * pos.y);
if (pos.z >= 0)
pen.DashStyle = System.Drawing.Drawing2D.DashStyle.Solid;
else
pen.DashStyle = System.Drawing.Drawing2D.DashStyle.Dash;
graph.DrawLine(pen, x1, y1, x2, y2);
} while (V <= V1);
// Destination body position
SolidBrush brush = new SolidBrush(Color.Blue);
// Draw Planets at departure date
float radius = 5.0F;
destBody.get_position(trans.arrivTime, ref orbit_pos);
pos = destBody.get_cartesian_pos(orbit_pos.theta);
x = x0 + Convert.ToSingle(scale * pos.x);
y = y0 - Convert.ToSingle(scale * pos.y);
float x5 = x;
float y5 = y;
graph.FillEllipse(brush, x - radius, y - radius, 2 * radius, 2 * radius);
arivBody.get_position(trans.arrivTime, ref orbit_pos);
pos = arivBody.get_cartesian_pos(orbit_pos.theta);
x = x0 + Convert.ToSingle(scale * pos.x);
y = y0 - Convert.ToSingle(scale * pos.y);
graph.FillEllipse(brush, x - radius, y - radius, 2 * radius, 2 * radius);
brush.Color = Color.Red;
// Draw Planets at arrival date
destBody.get_position(trans.depTime, ref orbit_pos);
pos = destBody.get_cartesian_pos(orbit_pos.theta);
x = x0 + Convert.ToSingle(scale * pos.x);
y = y0 - Convert.ToSingle(scale * pos.y);
graph.FillEllipse(brush, x - radius, y - radius, 2 * radius, 2 * radius);
arivBody.get_position(trans.depTime, ref orbit_pos);
pos = arivBody.get_cartesian_pos(orbit_pos.theta);
x = x0 + Convert.ToSingle(scale * pos.x);
y = y0 - Convert.ToSingle(scale * pos.y);
float x3 = x;
float y3 = y;
EclipticPos epos = new EclipticPos();
arivBody.get_ecliptic_coords(orbit_pos.theta, ref epos);
epos.lambda += Math.PI;
double opos_theta = Lambert.get_dest_theta(destBody, epos.lambda);
pos = destBody.get_cartesian_pos(opos_theta);
float x4 = x0 + Convert.ToSingle(scale * pos.x);
float y4 = y0 - Convert.ToSingle(scale * pos.y);
graph.FillEllipse(brush, x - radius, y - radius, 2 * radius, 2 * radius);
// Draw Psi angle
pen.Color = Color.LightGray;
pen.DashStyle = System.Drawing.Drawing2D.DashStyle.DashDot;
pen.Width = 1.0F;
graph.DrawLine(pen, x3, y3, x4, y4);
graph.DrawLine(pen, x0, y0, x5, y5);
//
float sunRadius = 10.0F;
if (ariv_data.refBody == "Sun")
brush.Color = Color.Yellow;
else
brush.Color = Color.Blue;
graph.FillEllipse(brush, x0 - sunRadius, y0 - sunRadius, 2 * sunRadius, 2 * sunRadius);
}
