C# CelestialBody.GetDensity方法代码示例

        protected override Vector3 UpdatePosition()
        {
            if (EditorLogic.RootPart == null) {
                /* DragCubes can get NaNed without this check */
                return Vector3.zero;
            }
            if (RCSBuildAid.Mode != PluginMode.Parachutes) {
                return Vector3.zero;
            }

            hasParachutes = RCSBuildAid.Parachutes.Count > 0;
            body = Settings.selected_body;
            altitude = MenuParachutes.altitude;
            temperature = body.GetTemperature (altitude);
            pressure = body.GetPressure (altitude);
            density = body.GetDensity (pressure, temperature);
            mach = (float)(speed / body.GetSpeedOfSound(pressure, density));
            gravity = body.gravity(altitude);

            findCenterOfDrag();
            speed = Vt = calculateTerminalVelocity ();
            /* unless I go at mach speeds I don't care about this
            reynolds = (float)(density * speed);
            reynoldsDragMult = PhysicsGlobals.DragCurvePseudoReynolds.Evaluate (reynolds);
            */
            dragForce.Vector = calculateDragForce ();

            return position;
        }

        public static double GetDensity(Vector3d position, CelestialBody body)
        {
            if (!body.atmosphere)
                return 0;

            double altitude = (position - body.position).magnitude - body.Radius;
            if (altitude > body.atmosphereDepth)
                return 0;

            double pressure = body.GetPressure(altitude);
            double temperature = GetTemperature(position, body);

            return body.GetDensity(pressure, temperature);
        }

        /// <summary>
        /// Gets the air density (rho) for the specified altitude on the specified body.
        /// This is an approximation, because actual calculations, taking sun exposure into account to compute air temperature, require to know the actual point on the body where the density is to be computed (knowing the altitude is not enough).
        /// However, the difference is small for high altitudes, so it makes very little difference for trajectory prediction.
        /// </summary>
        /// <param name="altitude">Altitude above sea level (in meters)</param>
        /// <param name="body"></param>
        /// <returns></returns>
        public static double GetDensity(double altitude, CelestialBody body)
        {
            if (!body.atmosphere)
                return 0;

            if (altitude > body.atmosphereDepth)
                return 0;

            double pressure = body.GetPressure(altitude);

            // get an average day/night temperature at the equator
            double sunDot = 0.5;
            float sunAxialDot = 0;
            double atmosphereTemperatureOffset = (double)body.latitudeTemperatureBiasCurve.Evaluate(0) + (double)body.latitudeTemperatureSunMultCurve.Evaluate(0) * sunDot + (double)body.axialTemperatureSunMultCurve.Evaluate(sunAxialDot);
            double temperature = body.GetTemperature(altitude) + (double)body.atmosphereTemperatureSunMultCurve.Evaluate((float)altitude) * atmosphereTemperatureOffset;

            return body.GetDensity(pressure, temperature);
        }

 public static float ComputeCutoffAlt(CelestialBody body, float cutoffDensity, float stepSize=100)
 {
     //This unfortunately doesn't seem to be coming up with the right altitude for Kerbin (~23km, it finds ~27km)
     double dens = 0;
     float alt = (float)body.atmosphereDepth;
     while (alt > 0)
     {
         dens = body.GetDensity(FlightGlobals.getStaticPressure(alt, body), body.atmosphereTemperatureCurve.Evaluate(alt)); //body.atmospherePressureCurve.Evaluate(alt)
         //Debug.Log("[SR] Alt: " + alt + " Pres: " + dens);
         if (dens < cutoffDensity)
             alt -= stepSize;
         else
             break;
     }
     return alt;
 }