💿🐜 Antkeeper source code
https://antkeeper.com
You can not select more than 25 topics
Topics must start with a letter or number, can include dashes ('-') and can be up to 35 characters long.
75 lines
2.2 KiB
75 lines
2.2 KiB
/*
|
|
* Copyright (C) 2021 Christopher J. Howard
|
|
*
|
|
* This file is part of Antkeeper source code.
|
|
*
|
|
* Antkeeper source code is free software: you can redistribute it and/or modify
|
|
* it under the terms of the GNU General Public License as published by
|
|
* the Free Software Foundation, either version 3 of the License, or
|
|
* (at your option) any later version.
|
|
*
|
|
* Antkeeper source code 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 General Public License for more details.
|
|
*
|
|
* You should have received a copy of the GNU General Public License
|
|
* along with Antkeeper source code. If not, see <http://www.gnu.org/licenses/>.
|
|
*/
|
|
|
|
#ifndef ANTKEEPER_ASTRO_ORBIT_HPP
|
|
#define ANTKEEPER_ASTRO_ORBIT_HPP
|
|
|
|
#include "utility/fundamental-types.hpp"
|
|
|
|
namespace astro
|
|
{
|
|
|
|
/**
|
|
* Contains six orbital elements which describe a Keplerian orbit.
|
|
*/
|
|
struct orbital_elements
|
|
{
|
|
double ec; ///< Eccentricity, e
|
|
double a; ///< Semi-major axis, a
|
|
double i; ///< Inclination, i (radians)
|
|
double om; ///< Longitude of the ascending node, OMEGA (radians)
|
|
double w; ///< Argument of periapsis, w (radians)
|
|
double ma; ///< Mean anomaly, M (radians)
|
|
};
|
|
|
|
/**
|
|
* Orbital state vectors.
|
|
*/
|
|
struct orbital_state
|
|
{
|
|
double3 r; ///< Cartesian position, r.
|
|
double3 v; ///< Cartesian velocity, v.
|
|
};
|
|
|
|
/**
|
|
* Iteratively solves Kepler's equation for eccentric anomaly, E.
|
|
*
|
|
* @param ec Eccentricity, e.
|
|
* @param ma Mean anomaly, M (radians).
|
|
* @param tolerance Tolerance of solution.
|
|
* @param iterations Maximum number of iterations.
|
|
* @return Eccentric anomaly.
|
|
*/
|
|
double solve_kepler(double ec, double ma, double tolerance, std::size_t iterations);
|
|
|
|
/**
|
|
* Calculates the ecliptic rectangular orbital position from Keplerian orbital elements.
|
|
*
|
|
* @note Only works for elliptical orbits.
|
|
*
|
|
* @param elements Orbital elements.
|
|
* @param ke_tolerance Kepler's equation tolerance.
|
|
* @param ke_iterations Kepler's equation iterations.
|
|
* @return Orbital state.
|
|
*/
|
|
double3 orbital_elements_to_ecliptic(const orbital_elements& elements, double ke_tolerance, std::size_t ke_iterations);
|
|
|
|
} // namespace astro
|
|
|
|
#endif // ANTKEEPER_ASTRO_ORBIT_HPP
|