new-horizons/NewHorizons/Components/Orbital/OrbitalParameters.cs

using System;
using System.Collections.Generic;
using System.Linq;
using System.Text;
using System.Threading.Tasks;
using UnityEngine;
using Logger = NewHorizons.Utility.Logger;

namespace NewHorizons.Components.Orbital
{
    public class OrbitalParameters
    {
        public float Inclination { get; private set; }
        public float SemiMajorAxis { get; private set; }
        public float LongitudeOfAscendingNode { get; private set; }
        public float Eccentricity { get; private set; }
        public float ArgumentOfPeriapsis { get; private set; }
        public float TrueAnomaly { get; private set; }
        public float MeanAnomaly { get; private set; }
        public float EccentricAnomaly { get; private set; }
        public float Period { get; private set; }

        public Vector3 InitialPosition { get; private set; }
        public Vector3 InitialVelocity { get; private set; }


        public static OrbitalParameters FromTrueAnomaly(Gravity primaryGravity, Gravity secondaryGravity, float eccentricity, float semiMajorAxis, float inclination, float argumentOfPeriapsis, float longitudeOfAscendingNode, float trueAnomaly)
        {
            var orbitalParameters = new OrbitalParameters();
            orbitalParameters.Inclination = inclination;   
            orbitalParameters.SemiMajorAxis = semiMajorAxis;
            orbitalParameters.LongitudeOfAscendingNode = longitudeOfAscendingNode;
            orbitalParameters.Eccentricity = eccentricity;
            orbitalParameters.ArgumentOfPeriapsis = argumentOfPeriapsis;    
            orbitalParameters.TrueAnomaly = trueAnomaly;

            // Have to calculate the rest

            var primaryMass = primaryGravity.Mass;
            var secondaryMass = secondaryGravity.Mass;

            var power = primaryGravity.Power;
            var period = (float) (GravityVolume.GRAVITATIONAL_CONSTANT * (primaryMass + secondaryMass) / (4 * Math.PI * Math.PI * Math.Pow(semiMajorAxis, power)));

            // All in radians
            var f = Mathf.Deg2Rad * trueAnomaly;
            var eccentricAnomaly = Mathf.Atan2(Mathf.Sqrt(1 - (eccentricity * eccentricity)) * Mathf.Sin(f), eccentricity + Mathf.Cos(f));
            var meanAnomaly = eccentricAnomaly - eccentricity * Mathf.Sin(eccentricAnomaly);

            orbitalParameters.Period = period;
            orbitalParameters.MeanAnomaly = meanAnomaly * Mathf.Rad2Deg;
            orbitalParameters.EccentricAnomaly = eccentricAnomaly * Mathf.Rad2Deg;

            var p = semiMajorAxis * (1 - (eccentricity * eccentricity)); // Semi-latus rectum
            var r = p / (1 + eccentricity * Mathf.Cos(f));

            var G = GravityVolume.GRAVITATIONAL_CONSTANT;
            var mu = G * (primaryMass);

            var r_p = semiMajorAxis * (1 - eccentricity);
            var r_a = semiMajorAxis * (1 + eccentricity);

            float v;

            // For linear
            if(primaryGravity.Power == 1)
            {
                // Have to deal with a limit
                if(eccentricity == 0)
                {
                    var v2 = 2 * mu * (Mathf.Log(r_a / r) + (1 / 2f));
                    v = Mathf.Sqrt(v2);
                }
                else
                {
                    var coeff = (r_p * r_p) / (r_p * r_p - r_a * r_a);
                    var v2 = 2 * mu * (coeff * Mathf.Log(r_p / r_a) + Mathf.Log(r_a / r));
                    v = Mathf.Sqrt(v2);
                }
            }
            // For inverseSquare
            else
            {
                v = Mathf.Sqrt(G * primaryMass * ((2f / r) - (1f / semiMajorAxis)));
            }

            var semiMinorAxis = semiMajorAxis * Mathf.Sqrt(1 - (eccentricity * eccentricity));
            var focusDistance = Mathf.Sqrt((semiMajorAxis * semiMajorAxis) - (semiMinorAxis * semiMinorAxis));

            var x = semiMajorAxis * Mathf.Cos(eccentricAnomaly) - focusDistance;
            var y = semiMinorAxis * Mathf.Sin(eccentricAnomaly);

            var R1 = Quaternion.AngleAxis(longitudeOfAscendingNode, Vector3.up);
            var R2 = Quaternion.AngleAxis(inclination, Vector3.forward);
            var R3 = Quaternion.AngleAxis(argumentOfPeriapsis, Vector3.up);

            var n_p = new Vector2(x, y).normalized;
            var n_v = new Vector2(-y, x).normalized;

            var pos = new Vector3(r * n_p.x, 0f, r * n_p.y);
            var vel = new Vector3(v * n_v.x, 0f, v * n_v.y);

            orbitalParameters.InitialPosition = R1 * R2 * R3 * pos;
            orbitalParameters.InitialVelocity = R1 * R2 * R3 * vel;

            return orbitalParameters;
        }
    }
}