本文整理汇总了C#中Orbit.GetEccVector方法的典型用法代码示例。如果您正苦于以下问题：C# Orbit.GetEccVector方法的具体用法？C# Orbit.GetEccVector怎么用？C# Orbit.GetEccVector使用的例子？那么, 这里精选的方法代码示例或许可以为您提供帮助。您也可以进一步了解该方法所在类Orbit的用法示例。
在下文中一共展示了Orbit.GetEccVector方法的4个代码示例，这些例子默认根据受欢迎程度排序。您可以为喜欢或者感觉有用的代码点赞，您的评价将有助于系统推荐出更棒的C#代码示例。
示例1: TrueAnomaly
private static double TrueAnomaly(Orbit orbit, Vector3d direction)
{
Vector3d periapsis = orbit.GetEccVector();
double trueAnomaly = Vector3d.Angle(periapsis, direction) * Deg2Rad;
if (Vector3d.Dot(Vector3d.Cross(periapsis, direction), orbit.GetOrbitNormal()) < 0) {
trueAnomaly = TwoPi - trueAnomaly;
}
return trueAnomaly;
}示例2: Print_Orbit_info
/// <summary>
///
/// </summary>
/// <param name="o">O.</param>
private static void Print_Orbit_info(Orbit o)
{
if (o == null) {
Debug.Log("Orbit is null");
return;
}
string Output = "";
Output += "Orbit Info \n";
Output += "\n activePatch:" + o.activePatch ;
Output += "\n altitude:"+ o.altitude ;
//Output += "\n an:"+ o.an ;
//Output += "\n ApA:"+ o.ApA ;
//Output += "\n ApR:"+ o.ApR ;
Output += "\n argumentOfPeriapsis:"+ o.argumentOfPeriapsis ;
//Output += "\n ClAppr:"+ o.ClAppr ;
//Output += "\n ClEctr1:"+ o.ClEctr1 ;
//Output += "\n ClEctr2:"+ o.ClEctr2 ;
Output += "\n closestEncounterBody:"+ o.closestEncounterBody ;
Output += "\n closestEncounterLevel:"+ o.closestEncounterLevel ;
Output += "\n closestEncounterPatch:"+ o.closestEncounterPatch ;
Output += "\n closestTgtApprUT:"+ o.closestTgtApprUT ;
//Output += "\n CrAppr:"+ o.CrAppr ;
//Output += "\n debugAN:"+ o.debugAN ;
//Output += "\n debugEccVec:"+ o.debugEccVec ;
//Output += "\n debugH:"+ o.debugH ;
//Output += "\n debugPos:"+ o.debugPos ;
//Output += "\n debugVel:"+ o.debugVel ;
//Output += "\n debug_returnFullEllipseTrajectory:"+ o.debug_returnFullEllipseTrajectory ;
//Output += "\n E:"+ o.E ;
//Output += "\n eccentricAnomaly:"+ o.eccentricAnomaly ;
//Output += "\n eccentricity:"+ o.eccentricity ;
//Output += "\n eccVec:"+ o.eccVec ;
//Output += "\n EndUT:"+ o.EndUT ;
Output += "\n epoch:"+ o.epoch ;
//Output += "\n FEVp:"+ o.FEVp;
//Output += "\n FEVs:"+ o.FEVs ;
//Output += "\n fromE:"+ o.fromE ;
//Output += "\n fromV:"+ o.fromV ;
//Output += "\n h:"+ o.h ;
//Output += "\n inclination:"+ o.inclination ;
//Output += "\n LAN:"+ o.LAN ;
//Output += "\n mag:"+ o.mag ;
//Output += "\n meanAnomaly:"+ o.meanAnomaly ;
//Output += "\n meanAnomalyAtEpoch:"+ o.meanAnomalyAtEpoch ;
Output += "\n nearestTT:"+ o.nearestTT ;
Output += "\n nextPatch:"+ o.nextPatch ;
Output += "\n nextTT:"+ o.nextTT ;
//Output += "\n ObT:"+ o.ObT ;
Output += "\n ObTAtEpoch :"+ o.ObTAtEpoch ;
//Output += "\n orbitalEnergy :"+ o.orbitalEnergy ;
//Output += "\n orbitalSpeed:"+ o.orbitalSpeed ;
//Output += "\n orbitPercent :"+ o.orbitPercent ;
Output += "\n patchEndTransition :"+ o.patchEndTransition ;
Output += "\n patchStartTransition :"+ o.patchStartTransition ;
//Output += "\n period :"+ o.period ;
//Output += "\n pos :"+ o.pos ;
Output += "\n previousPatch :"+ o.previousPatch ;
//Output += "\n radius :"+ o.radius ;
Output += "\n referenceBody :"+ o.referenceBody ;
//Output += "\n sampleInterval :"+ o.sampleInterval ;
Output += "\n secondaryPosAtTransition1 :"+ o.secondaryPosAtTransition1 ;
Output += "\n secondaryPosAtTransition2 :"+ o.secondaryPosAtTransition2 ;
//Output += "\n semiLatusRectum :"+ o.semiLatusRectum ;
//Output += "\n semiMajorAxis :"+ o.semiMajorAxis ;
//Output += "\n semiMinorAxis :"+ o.semiMinorAxis ;
//Output += "\n SEVp :"+ o.SEVp ;
//Output += "\n SEVs :"+ o.SEVs ;
//Output += "\n StartUT :"+ o.StartUT ;
Output += "\n timeToAp :"+ o.timeToAp ;
Output += "\n timeToPe :"+ o.timeToPe ;
Output += "\n timeToTransition1 :"+ o.timeToTransition1 ;
Output += "\n timeToTransition2 :"+ o.timeToTransition2 ;
//Output += "\n toE :"+ o.toE ;
//Output += "\n toV :"+ o.toV ;
//Output += "\n trueAnomaly :"+ o.trueAnomaly ;
//Output += "\n UTappr :"+ o.UTappr ;
//Output += "\n UTsoi :"+ o.UTsoi ;
//Output += "\n V :"+ o.V ;
//Output += "\n vel :"+ o.vel ;
Debug.Log(Output);
if (!o.activePatch) {
return;
}
try{
//Functions
Output = "Orbit Functions: \n";
Output += "\n PeA :"+ o.PeA ;
Output += "\n PeR :"+ o.PeR ;
Output += "\n GetANVector:"+ o.GetANVector() ;
Output += "\n GetEccVector:"+ o.GetEccVector() ;
Output += "\n GetFrameVel:"+ o.GetFrameVel() ;
Output += "\n GetHashCode:"+ o.GetHashCode() ;
//.........这里部分代码省略.........
示例3: ComputeEjectionManeuver
static ManeuverParameters ComputeEjectionManeuver(Vector3d exit_velocity, Orbit initial_orbit, double UT_0)
{
double GM = initial_orbit.referenceBody.gravParameter;
double C3 = exit_velocity.sqrMagnitude;
double sma = -GM / C3;
double Rpe = initial_orbit.semiMajorAxis;
double ecc = 1 - Rpe / sma;
double theta = Math.Acos(-1 / ecc);
Vector3d intersect_1;
Vector3d intersect_2;
// intersect_1 is the optimal position on the orbit assuming the orbit is circular and the sphere of influence is infinite
IntersectConePlane(exit_velocity, theta, initial_orbit.h, out intersect_1, out intersect_2);
Vector3d eccvec = initial_orbit.GetEccVector();
double true_anomaly = AngleAboutAxis(eccvec, intersect_1, initial_orbit.h);
// GetMeanAnomalyAtTrueAnomaly expects degrees and returns radians
double mean_anomaly = initial_orbit.GetMeanAnomalyAtTrueAnomaly(true_anomaly * 180 / Math.PI);
double delta_mean_anomaly = MuUtils.ClampRadiansPi(mean_anomaly - initial_orbit.MeanAnomalyAtUT(UT_0));
double UT = UT_0 + delta_mean_anomaly / initial_orbit.MeanMotion();
Vector3d V_0 = initial_orbit.getOrbitalVelocityAtUT(UT);
Vector3d pos = initial_orbit.getRelativePositionAtUT(UT);
double final_vel = Math.Sqrt(C3 + 2 * GM / pos.magnitude);
Vector3d x = pos.normalized;
Vector3d z = Vector3d.Cross(x, exit_velocity).normalized;
Vector3d y = Vector3d.Cross(z, x);
theta = Math.PI / 2;
double dtheta = 0.001;
Orbit sample = new Orbit();
double theta_err = Double.MaxValue;
for (int iteration = 0 ; iteration < 50 ; ++iteration)
{
Vector3d V_1 = final_vel * (Math.Cos(theta) * x + Math.Sin(theta) * y);
sample.UpdateFromStateVectors(pos, V_1, initial_orbit.referenceBody, UT);
theta_err = AngleAboutAxis(exit_velocity, sample.getOrbitalVelocityAtUT(OrbitExtensions.NextTimeOfRadius(sample, UT, sample.referenceBody.sphereOfInfluence)), z);
if (double.IsNaN(theta_err))
return null;
if (Math.Abs(theta_err) <= Math.PI / 1800)
return new ManeuverParameters((V_1 - V_0).xzy, UT);
V_1 = final_vel * (Math.Cos(theta + dtheta) * x + Math.Sin(theta + dtheta) * y);
sample.UpdateFromStateVectors(pos, V_1, initial_orbit.referenceBody, UT);
double theta_err_2 = AngleAboutAxis(exit_velocity, sample.getOrbitalVelocityAtUT(OrbitExtensions.NextTimeOfRadius(sample, UT, sample.referenceBody.sphereOfInfluence)), z);
V_1 = final_vel * (Math.Cos(theta - dtheta) * x + Math.Sin(theta - dtheta) * y);
sample.UpdateFromStateVectors(pos, V_1, initial_orbit.referenceBody, UT);
double theta_err_3 = AngleAboutAxis(exit_velocity, sample.getOrbitalVelocityAtUT(OrbitExtensions.NextTimeOfRadius(sample, UT, sample.referenceBody.sphereOfInfluence)), z);
double derr = MuUtils.ClampRadiansPi(theta_err_2 - theta_err_3) / (2 * dtheta);
theta = MuUtils.ClampRadiansTwoPi(theta - theta_err / derr);
// if theta > pi, replace with 2pi - theta, the function ejection_angle=f(theta) is symmetrc wrt theta=pi
if (theta > Math.PI)
theta = 2 * Math.PI - theta;
}
return null;
}示例4: ComputeEjectionManeuver
public static ManeuverParameters ComputeEjectionManeuver(Vector3d exit_velocity, Orbit initial_orbit, double UT_0)
{
double GM = initial_orbit.referenceBody.gravParameter;
double C3 = exit_velocity.sqrMagnitude;
double Mh = initial_orbit.referenceBody.sphereOfInfluence;
double Rpe = initial_orbit.semiMajorAxis;
double isma = 2 / Mh - C3 / GM; //inverted Semi-major Axis, will work for parabolic orbit
double ecc = 1.0 - Rpe * isma;
//double vstart = Math.Sqrt(GM * (2 / Rpe - isma)); //{ total start boost}
//double slat = Rpe * Rpe * vstart * vstart / GM;
//the problem here should be R for circular orbit instead of Rpe
double slat = 2 * Rpe - isma * Rpe * Rpe; //but we don't know start point (yet) in elliptic orbit
double theta = Math.Acos((slat / Mh - 1) / ecc);
/*
//old way infinity hyperbolic:
//problems: it's not necessary hyperbolic (in case of low speed exit_velocity),
//and exit_velocity appears not infinite far from celestial body, but only sphereOfInfluence far
//i.e. Mh in previous statements(theta, isma) is not infinity!
double sma = -GM / C3;
double ecc = 1 - Rpe / sma;
double theta = Math.Acos(-1 / ecc);
*/
Vector3d intersect_1;
Vector3d intersect_2;
// intersect_1 is the optimal position on the orbit assuming the orbit is circular and the sphere of influence is infinite
IntersectConePlane(exit_velocity, theta, initial_orbit.h, out intersect_1, out intersect_2);
Vector3d eccvec = initial_orbit.GetEccVector();
double true_anomaly = AngleAboutAxis(eccvec, intersect_1, initial_orbit.h);
// GetMeanAnomalyAtTrueAnomaly expects degrees and returns radians
double mean_anomaly = initial_orbit.GetMeanAnomalyAtTrueAnomaly(true_anomaly * 180 / Math.PI);
double delta_mean_anomaly = MuUtils.ClampRadiansPi(mean_anomaly - initial_orbit.MeanAnomalyAtUT(UT_0));
double UT = UT_0 + delta_mean_anomaly / initial_orbit.MeanMotion();
Vector3d V_0 = initial_orbit.getOrbitalVelocityAtUT(UT);
Vector3d pos = initial_orbit.getRelativePositionAtUT(UT);
double final_vel = Math.Sqrt(C3 + 2 * GM / pos.magnitude);
Vector3d x = pos.normalized;
Vector3d z = Vector3d.Cross(x, exit_velocity).normalized;
Vector3d y = Vector3d.Cross(z, x);
theta = Math.PI / 2;
double dtheta = 0.001;
Orbit sample = new Orbit();
double theta_err = Double.MaxValue;
for (int iteration = 0 ; iteration < 50 ; ++iteration)
{
Vector3d V_1 = final_vel * (Math.Cos(theta) * x + Math.Sin(theta) * y);
sample.UpdateFromStateVectors(pos, V_1, initial_orbit.referenceBody, UT);
theta_err = AngleAboutAxis(exit_velocity, sample.getOrbitalVelocityAtUT(OrbitExtensions.NextTimeOfRadius(sample, UT, sample.referenceBody.sphereOfInfluence)), z);
if (double.IsNaN(theta_err))
return null;
if (Math.Abs(theta_err) <= Math.PI / 1800)
return new ManeuverParameters((V_1 - V_0).xzy, UT);
V_1 = final_vel * (Math.Cos(theta + dtheta) * x + Math.Sin(theta + dtheta) * y);
sample.UpdateFromStateVectors(pos, V_1, initial_orbit.referenceBody, UT);
double theta_err_2 = AngleAboutAxis(exit_velocity, sample.getOrbitalVelocityAtUT(OrbitExtensions.NextTimeOfRadius(sample, UT, sample.referenceBody.sphereOfInfluence)), z);
V_1 = final_vel * (Math.Cos(theta - dtheta) * x + Math.Sin(theta - dtheta) * y);
sample.UpdateFromStateVectors(pos, V_1, initial_orbit.referenceBody, UT);
double theta_err_3 = AngleAboutAxis(exit_velocity, sample.getOrbitalVelocityAtUT(OrbitExtensions.NextTimeOfRadius(sample, UT, sample.referenceBody.sphereOfInfluence)), z);
double derr = MuUtils.ClampRadiansPi(theta_err_2 - theta_err_3) / (2 * dtheta);
theta = MuUtils.ClampRadiansTwoPi(theta - theta_err / derr);
// if theta > pi, replace with 2pi - theta, the function ejection_angle=f(theta) is symmetrc wrt theta=pi
if (theta > Math.PI)
theta = 2 * Math.PI - theta;
}
return null;
}