public static ReferenceFrame CreateAtCurrentTime(CelestialBody referenceBody)
{
ReferenceFrame ret = new ReferenceFrame();
ret.lat0lon0AtStart = referenceBody.GetSurfaceNVector(0, 0);
ret.lat0lon90AtStart = referenceBody.GetSurfaceNVector(0, 90);
ret.lat90AtStart = referenceBody.GetSurfaceNVector(90, 0);
ret.epoch = Planetarium.GetUniversalTime();
ret.referenceBody = referenceBody;
return ret;
}
Vector3d x; //coordinate system used is centered on main body
#endregion Fields
#region Constructors
public ReentrySimulation(Orbit initialOrbit, double UT, double dragCoefficient, List<SimulatedParachute> parachuteList, double mass,
IDescentSpeedPolicy descentSpeedPolicy, double endAltitudeASL, double maxThrustAccel)
{
CelestialBody body = initialOrbit.referenceBody;
bodyHasAtmosphere = body.atmosphere;
seaLevelAtmospheres = body.atmosphereMultiplier;
scaleHeight = 1000 * body.atmosphereScaleHeight;
bodyRadius = body.Radius;
gravParameter = body.gravParameter;
this.dragCoefficient = dragCoefficient;
this.parachutes = parachuteList;
this.mass = mass;
bodyAngularVelocity = body.angularVelocity;
this.descentSpeedPolicy = descentSpeedPolicy;
landedRadius = bodyRadius + endAltitudeASL;
aerobrakedRadius = bodyRadius + body.RealMaxAtmosphereAltitude();
mainBody = body;
this.maxThrustAccel = maxThrustAccel;
referenceFrame = ReferenceFrame.CreateAtCurrentTime(initialOrbit.referenceBody);
orbitReenters = OrbitReenters(initialOrbit);
if (orbitReenters)
{
startUT = UT;
t = startUT;
AdvanceToFreefallEnd(initialOrbit);
}
maxDragGees = 0;
deltaVExpended = 0;
trajectory = new List<AbsoluteVector>();
}
Vector3d x; //coordinate system used is centered on main body
#endregion Fields
#region Constructors
public ReentrySimulation(Orbit _initialOrbit, double _UT, double _dragMassExcludingUsedParachutes, List<SimulatedParachute> _parachuteList, double _mass,
IDescentSpeedPolicy _descentSpeedPolicy, double _decelEndAltitudeASL, double _maxThrustAccel, double _parachuteSemiDeployMultiplier, double _probableLandingSiteASL, bool _multiplierHasError, double _dt)
{
// Store all the input values as they were given
input_initialOrbit = _initialOrbit;
input_UT = _UT;
input_dragMassExcludingUsedParachutes = _dragMassExcludingUsedParachutes;
input_parachuteList = _parachuteList;
input_mass = _mass;
input_descentSpeedPolicy = _descentSpeedPolicy;
input_decelEndAltitudeASL = _decelEndAltitudeASL;
input_maxThrustAccel = _maxThrustAccel;
input_parachuteSemiDeployMultiplier = _parachuteSemiDeployMultiplier;
input_probableLandingSiteASL = _probableLandingSiteASL;
input_multiplierHasError = _multiplierHasError;
input_dt = _dt;
max_dt = _dt;
dt = max_dt;
CelestialBody body = _initialOrbit.referenceBody;
bodyHasAtmosphere = body.atmosphere;
seaLevelAtmospheres = body.atmosphereMultiplier;
scaleHeight = 1000 * body.atmosphereScaleHeight;
bodyRadius = body.Radius;
gravParameter = body.gravParameter;
this.dragMassExcludingUsedParachutes = _dragMassExcludingUsedParachutes;
this.parachutes = _parachuteList;
this.parachuteSemiDeployMultiplier = _parachuteSemiDeployMultiplier;
this.multiplierHasError = _multiplierHasError;
this.mass = _mass;
bodyAngularVelocity = body.angularVelocity;
this.descentSpeedPolicy = _descentSpeedPolicy;
decelRadius = bodyRadius + _decelEndAltitudeASL;
aerobrakedRadius = bodyRadius + body.RealMaxAtmosphereAltitude();
mainBody = body;
this.maxThrustAccel = _maxThrustAccel;
this.probableLandingSiteASL = _probableLandingSiteASL;
this.probableLandingSiteRadius = _probableLandingSiteASL + bodyRadius;
referenceFrame = ReferenceFrame.CreateAtCurrentTime(_initialOrbit.referenceBody);
orbitReenters = OrbitReenters(_initialOrbit);
if (orbitReenters)
{
startUT = _UT;
t = startUT;
AdvanceToFreefallEnd(_initialOrbit);
}
maxDragGees = 0;
deltaVExpended = 0;
trajectory = new List<AbsoluteVector>();
}
public ReentrySimulation(Orbit _initialOrbit, double _UT, SimulatedVessel _vessel, SimCurves _simcurves, IDescentSpeedPolicy _descentSpeedPolicy, double _decelEndAltitudeASL, double _maxThrustAccel, double _parachuteSemiDeployMultiplier, double _probableLandingSiteASL, bool _multiplierHasError, double _dt, double _min_dt)
{
// Store all the input values as they were given
input_initialOrbit = _initialOrbit;
input_UT = _UT;
vessel = _vessel;
input_descentSpeedPolicy = _descentSpeedPolicy;
input_decelEndAltitudeASL = _decelEndAltitudeASL;
input_maxThrustAccel = _maxThrustAccel;
input_parachuteSemiDeployMultiplier = _parachuteSemiDeployMultiplier;
input_probableLandingSiteASL = _probableLandingSiteASL;
input_multiplierHasError = _multiplierHasError;
input_dt = _dt;
// the vessel attitude relative to the surface vel. Fixed for now
attitude = Quaternion.Euler(180,0,0);
min_dt = _min_dt;
max_dt = _dt;
dt = max_dt;
// Get a copy of the original orbit, to be more thread safe
initialOrbit = new Orbit();
initialOrbit.UpdateFromOrbitAtUT(_initialOrbit, _UT, _initialOrbit.referenceBody);
CelestialBody body = _initialOrbit.referenceBody;
bodyHasAtmosphere = body.atmosphere;
bodyRadius = body.Radius;
gravParameter = body.gravParameter;
this.parachuteSemiDeployMultiplier = _parachuteSemiDeployMultiplier;
this.multiplierHasError = _multiplierHasError;
bodyAngularVelocity = body.angularVelocity;
this.descentSpeedPolicy = _descentSpeedPolicy;
decelRadius = bodyRadius + _decelEndAltitudeASL;
aerobrakedRadius = bodyRadius + body.RealMaxAtmosphereAltitude();
mainBody = body;
this.maxThrustAccel = _maxThrustAccel;
this.probableLandingSiteASL = _probableLandingSiteASL;
this.probableLandingSiteRadius = _probableLandingSiteASL + bodyRadius;
referenceFrame = ReferenceFrame.CreateAtCurrentTime(_initialOrbit.referenceBody);
orbitReenters = OrbitReenters(_initialOrbit);
if (orbitReenters)
startUT = _UT;
maxDragGees = 0;
deltaVExpended = 0;
trajectory = new List<AbsoluteVector>();
simCurves = _simcurves;
once = true;
}
public ReentrySimulation(Orbit _initialOrbit, double _UT, SimulatedVessel _vessel, SimCurves _simcurves, IDescentSpeedPolicy _descentSpeedPolicy, double _decelEndAltitudeASL, double _maxThrustAccel, double _parachuteSemiDeployMultiplier, double _probableLandingSiteASL, bool _multiplierHasError, double _dt, double _min_dt)
{
// Store all the input values as they were given
input_initialOrbit = _initialOrbit;
input_UT = _UT;
vessel = _vessel;
input_descentSpeedPolicy = _descentSpeedPolicy;
input_decelEndAltitudeASL = _decelEndAltitudeASL;
input_maxThrustAccel = _maxThrustAccel;
input_parachuteSemiDeployMultiplier = _parachuteSemiDeployMultiplier;
input_probableLandingSiteASL = _probableLandingSiteASL;
input_multiplierHasError = _multiplierHasError;
input_dt = _dt;
// the vessel attitude relative to the surface vel. Fixed for now
attitude = Quaternion.Euler(180, 0, 0);
min_dt = _min_dt;
max_dt = _dt;
dt = max_dt;
// Get a copy of the original orbit, to be more thread safe
initialOrbit = new Orbit();
initialOrbit.UpdateFromOrbitAtUT(_initialOrbit, _UT, _initialOrbit.referenceBody);
CelestialBody body = _initialOrbit.referenceBody;
bodyHasAtmosphere = body.atmosphere;
bodyRadius = body.Radius;
gravParameter = body.gravParameter;
this.parachuteSemiDeployMultiplier = _parachuteSemiDeployMultiplier;
this.multiplierHasError = _multiplierHasError;
bodyAngularVelocity = body.angularVelocity;
this.descentSpeedPolicy = _descentSpeedPolicy;
decelRadius = bodyRadius + _decelEndAltitudeASL;
aerobrakedRadius = bodyRadius + body.RealMaxAtmosphereAltitude();
mainBody = body;
this.maxThrustAccel = _maxThrustAccel;
this.probableLandingSiteASL = _probableLandingSiteASL;
this.probableLandingSiteRadius = _probableLandingSiteASL + bodyRadius;
referenceFrame = ReferenceFrame.CreateAtCurrentTime(_initialOrbit.referenceBody);
orbitReenters = OrbitReenters(_initialOrbit);
if (orbitReenters)
{
startUT = _UT;
}
maxDragGees = 0;
deltaVExpended = 0;
trajectory = new List <AbsoluteVector>();
simCurves = _simcurves;
once = true;
}