public float TTB(float dV, float throttle = -1)
{
if (throttle < 0)
{
throttle = ThrottleControl.NextThrottle(dV, 1, VSL);
}
return(TTB(dV, MaxThrustM, MaxMassFlow, throttle));
}
public float AntigravTTB(float vertical_V, float throttle = -1)
{
if (throttle < 0)
{
throttle = ThrottleControl.NextThrottle(vertical_V, 1, VSL);
}
return(VSL.Engines.TTB(vertical_V,
Utils.ClampL(MaxThrustM - VSL.Physics.StG * VSL.Physics.M, 1e-5f),
MaxMassFlow, throttle));
}
public static float BrakeDistance(float V0, VesselWrapper VSL, out float ttb)
{
ttb = VSL.Engines.TTB(V0);
var throttle = ThrottleControl.NextThrottle((float)V0, 1, VSL);
if (CheatOptions.InfinitePropellant)
{
return((V0 - VSL.Engines.MaxThrustM * throttle * ttb / 2 / VSL.Physics.M) * ttb);
}
return(V0 * ttb +
VSL.Engines.MaxThrustM / VSL.Engines.MaxMassFlow *
((ttb - VSL.Physics.M / VSL.Engines.MaxMassFlow / throttle) *
Mathf.Log((VSL.Physics.M - VSL.Engines.MaxMassFlow * throttle * ttb) / VSL.Physics.M) - ttb));
}
public float TTB_Precise(float dV)
{
var ttb = 0f;
var mass = VSL.Physics.M;
var throttle = ThrottleControl.NextThrottle(dV, 1, mass, MaxThrustM, DecelerationTime10);
while (dV > 0.1)
{
throttle = ThrottleControl.NextThrottle(dV, throttle, mass, MaxThrustM, DecelerationTime10);
dV /= 2;
ttb += TTB(dV, MaxThrustM, mass, MaxMassFlow, throttle, out mass);
}
throttle = ThrottleControl.NextThrottle(dV, throttle, mass, MaxThrustM, DecelerationTime10);
return(ttb + TTB(dV, MaxThrustM, mass, MaxMassFlow, throttle, out mass));
}
public static float BrakeDistancePrecise(float V0, VesselWrapper VSL, out float ttb)
{
ttb = 0f;
var dist = 0f;
var mass = VSL.Physics.M;
var throttle = ThrottleControl.NextThrottle(V0, 1, mass, VSL.Engines.MaxThrustM, VSL.Engines.DecelerationTime10);
float next_mass;
float ttb_cur;
while (V0 > 0.1)
{
throttle = ThrottleControl.NextThrottle(V0, throttle, mass, VSL.Engines.MaxThrustM, VSL.Engines.DecelerationTime10);
ttb_cur = EnginesProps.TTB(V0 / 2, VSL.Engines.MaxThrustM, mass, VSL.Engines.MaxMassFlow, throttle, out next_mass);
dist += BrakeDistance(V0, ttb_cur, VSL.Engines.MaxThrustM, mass, VSL.Engines.MaxMassFlow, throttle);
ttb += ttb_cur;
mass = next_mass;
V0 /= 2;
}
throttle = ThrottleControl.NextThrottle(V0, throttle, mass, VSL.Engines.MaxThrustM, VSL.Engines.DecelerationTime10);
ttb_cur = EnginesProps.TTB(V0, VSL.Engines.MaxThrustM, mass, VSL.Engines.MaxMassFlow, throttle, out next_mass);
dist += BrakeDistance(V0, ttb_cur, VSL.Engines.MaxThrustM, mass, VSL.Engines.MaxMassFlow, throttle);
ttb += ttb_cur;
return(dist);
}
public static float BrakingDistance(float V0, VesselWrapper VSL, out float ttb)
{
return(BrakingDistance(V0, VSL.Engines.MaxThrustM, VSL.Engines.MaxMassFlow,
ThrottleControl.NextThrottle((float)V0, 1, VSL),
VSL, out ttb));
}
public double FromSurfaceTTA(double ApA, double alpha, double gturn_curve, double surface_vel)
{
var t = 0.0;
var v = new Vector3d(0, surface_vel);
var h = (double)VSL.Altitude.Absolute;
var m = (double)VSL.Physics.M;
var eStats = VSL.Engines.NoActiveEngines?
VSL.Engines.GetNearestEnginedStageStats() :
VSL.Engines.GetEnginesStats(VSL.Engines.Active);
var mT = eStats.MaxThrust;
var mflow = eStats.MaxMassFlow;
var mTm = mT.magnitude * Mathfx.Lerp(0.6, 0.95, Utils.ClampH(
VSL.Torque.AngularAcceleration(eStats.TorqueInfo.Torque + VSL.Torque.RCSLimits.Max + VSL.Torque.WheelsLimits.Max).magnitude, 1));
var s = VSL.Geometry.AreaInDirection(mT);
var R = Body.Radius;
var thrust = true;
var throttle = 1.0;
// var alpha0 = alpha; //debug
while (v.x >= 0)
{
var atmF = Utils.Clamp(h / Body.atmosphereDepth, 0, 1);
if (thrust)
{
double apaT;
var apa = freeclimb_altitude(m, s, h, v.x, v.y, DeltaTime * 4, out apaT);
var dapa = (ApA - apa) * gturn_curve;
var arc = (alpha - v.y * apaT / (R + (h + apa) / 2)) * (R + apa);
var vv = Utils.ClampL(dapa, 0);
var hv = Utils.ClampL(arc - dapa, 0) * Utils.Clamp((h - VSL.Altitude.Absolute) / GLB.ORB.GTurnOffset, 0, 1);
if (h < Body.atmosphereDepth)
{
hv *= Math.Sqrt(atmF);
}
var angle = Math.Atan2(vv, hv);
throttle = ThrottleControl.NextThrottle((float)(Math.Sqrt(vv * vv + hv * hv) * Globals.Instance.ORB.Dist2VelF * VSL.Physics.StG / Utils.G0),
(float)throttle, (float)m, (float)mTm, 0);
var v_throttle = Math.Sin(angle);
v.x += (mTm * v_throttle * throttle / m - G(h, v.y)) * DeltaTime;
var h_throttle = 0.0;
if (arc > 0)
{
h_throttle = Math.Cos(angle);
v.y += (mTm * h_throttle * throttle / m) * DeltaTime;
}
thrust = ApA - apa > GLB.ORB.Dtol && arc > GLB.ORB.Dtol;
if (!CheatOptions.InfinitePropellant)
{
var dm = mflow * (h_throttle + v_throttle) * throttle * DeltaTime;
if (m < dm)
{
thrust = false; continue;
}
m -= dm;
}
// Utils.Log("apaT {}, dapa {}, arc {}, throttle {}, h-thr {}, v-thr {}", apaT, dapa, arc, throttle);//debug
}
else
{
v.x -= G(h, v.y) * DeltaTime;
}
if (h < Body.atmosphereDepth)
{
var y = v.y - surface_vel * (1 - atmF);
var vm = Math.Sqrt(v.x * v.x + y * y);
var D = drag(s, h, vm) / m * DeltaTime / vm;
v.x -= v.x * D;
v.y -= y * D;
}
alpha -= v.y * DeltaTime / Body.Radius;
h += v.x * DeltaTime;
t += DeltaTime;
// Utils.Log("v.v {}, v.h {}, drag {}, h {}, hmove {}", v.x, v.y, drag(s, h, vm)/m, h, hmove);//debug
// DebugUtils.CSV("LambertSolver", t, v.x, v.y, (alpha0-alpha)*(R+h), h, m, mTm*throttle, throttle, Math.Atan2(v.x, v.y)*Mathf.Rad2Deg);//debug
}
return(t - DeltaTime / 2);
}
public float TTB(float dV)
{
return(TTB(dV, MaxThrustM, MaxMassFlow, ThrottleControl.NextThrottle(dV, 1, VSL)));
}
