/**
 * @author @thkruz Theodore Kruczek
 * @description Orbital Object ToolKit (ootk) is a collection of tools for working
 * with satellites and other orbital objects.
 * @license AGPL-3.0-or-later
 * @copyright (c) 2025 Kruczek Labs LLC
 *
 * Many of the classes are based off of the work of @david-rc-dayton and his
 * Pious Squid library (https://github.com/david-rc-dayton/pious_squid) which
 * is licensed under the MIT license.
 *
 * Orbital Object ToolKit is free software: you can redistribute it and/or modify it under the
 * terms of the GNU Affero General Public License as published by the Free Software
 * Foundation, either version 3 of the License, or (at your option) any later version.
 *
 * Orbital Object ToolKit is distributed in the hope that it will be useful, but WITHOUT ANY WARRANTY;
 * without even the implied warranty of MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.
 * See the GNU Affero General Public License for more details.
 *
 * You should have received a copy of the GNU Affero General Public License along with
 * Orbital Object ToolKit. If not, see <http://www.gnu.org/licenses/>.
 */

import { Minutes, PositionVelocity, Kilometers, Radians, Seconds } from '../main.js';
import { EpochUTC } from '../time/EpochUTC.js';
import { earthGravityParam, MINUTES_PER_DAY, TAU } from '../utils/constants.js';
import { newtonM } from '../utils/functions.js';
import { ClassicalElements } from './ClassicalElements.js';
import { EquinoctialElementsParams } from '../interfaces/EquinoctialElementsParams.js';

/**
 * Equinoctial elements are a set of orbital elements used to describe the
 * orbits of celestial bodies, such as satellites around a planet. They provide
 * an alternative to the traditional Keplerian elements and are especially
 * useful for avoiding singularities and numerical issues in certain types of
 * orbits.
 *
 * Unlike Keplerian elements, equinoctial elements don't suffer from
 * singularities at zero eccentricity (circular orbits) or zero inclination
 * (equatorial orbits). This makes them more reliable for numerical simulations
 * and analytical studies, especially in these edge cases.
 * @see https://faculty.nps.edu/dad/orbital/th0.pdf
 */
export class EquinoctialElements {
  epoch: EpochUTC;
  /** The semi-major axis of the orbit in kilometers. */
  a: Kilometers;
  /** The h component of the eccentricity vector. */
  h: number;
  /** The k component of the eccentricity vector. */
  k: number;
  /** The p component of the ascending node vector. */
  p: number;
  /** The q component of the ascending node vector. */
  q: number;
  /** The mean longitude of the orbit in radians. */
  lambda: Radians;
  /** The gravitational parameter of the central body in km³/s². */
  mu: number;
  /** The retrograde factor. 1 for prograde orbits, -1 for retrograde orbits. */
  I: 1 | -1;
  constructor({ epoch, h, k, lambda, a, p, q, mu, I }: EquinoctialElementsParams) {
    this.epoch = epoch;
    this.h = h;
    this.k = k;
    this.lambda = lambda;
    this.a = a;
    this.p = p;
    this.q = q;
    this.mu = mu ?? earthGravityParam;
    this.I = I ?? 1;
  }

  /**
   * Returns a string representation of the EquinoctialElements object.
   * @returns A string representation of the EquinoctialElements object.
   */
  toString(): string {
    return [
      '[EquinoctialElements]',
      `  Epoch: ${this.epoch}`,
      `  a: ${this.a} km`,
      `  h: ${this.h}`,
      `  k: ${this.k}`,
      `  p: ${this.p}`,
      `  q: ${this.q}`,
      `  lambda: ${this.lambda} rad`,
    ].join('\n');
  }

  /**
   * Gets the semimajor axis.
   * @returns The semimajor axis in kilometers.
   */
  get semimajorAxis(): Kilometers {
    return this.a;
  }

  /**
   * Gets the mean longitude.
   * @returns The mean longitude in radians.
   */
  get meanLongitude(): Radians {
    return this.lambda;
  }

  /**
   * Calculates the mean motion of the celestial object.
   * @returns The mean motion in units of radians per second.
   */
  get meanMotion(): number {
    return Math.sqrt(this.mu / this.a ** 3);
  }

  /**
   * Gets the retrograde factor.
   * @returns The retrograde factor.
   */
  get retrogradeFactor(): number {
    return this.I;
  }

  /**
   * Checks if the orbit is prograde.
   * @returns True if the orbit is prograde, false otherwise.
   */
  isPrograde(): boolean {
    return this.I === 1;
  }

  /**
   * Checks if the orbit is retrograde.
   * @returns True if the orbit is retrograde, false otherwise.
   */
  isRetrograde(): boolean {
    return this.I === -1;
  }

  /**
   * Gets the period of the orbit.
   * @returns The period in minutes.
   */
  get period(): Minutes {
    const periodSec = (TAU * Math.sqrt(this.semimajorAxis ** 3 / this.mu)) as Seconds;

    return (periodSec / 60) as Minutes;
  }

  /**
   * Gets the number of revolutions per day.
   * @returns The number of revolutions per day.
   */
  get revsPerDay(): number {
    return MINUTES_PER_DAY / this.period;
  }

  /**
   * Converts the equinoctial elements to classical elements.
   * @returns The classical elements.
   */
  toClassicalElements(): ClassicalElements {
    const a = this.semimajorAxis;
    const e = Math.sqrt(this.k * this.k + this.h * this.h);
    const i = Math.PI * ((1.0 - this.I) * 0.5) + 2.0 * this.I * Math.atan(Math.sqrt(this.p * this.p + this.q * this.q));
    const o = Math.atan2(this.p, this.q);
    const w = Math.atan2(this.h, this.k) - this.I * Math.atan2(this.p, this.q);
    const m = this.lambda - this.I * o - w;
    const v = newtonM(e, m).nu;

    return new ClassicalElements({
      epoch: this.epoch,
      semimajorAxis: a,
      eccentricity: e,
      inclination: i as Radians,
      rightAscension: o as Radians,
      argPerigee: w as Radians,
      trueAnomaly: v as Radians,
      mu: this.mu,
    });
  }

  /**
   * Converts the equinoctial elements to position and velocity.
   * @returns The position and velocity in classical elements.
   */
  toPositionVelocity(): PositionVelocity {
    return this.toClassicalElements().toPositionVelocity();
  }
}