ootk/dist/body/Earth.d.ts

Orbital Object Toolkit including Multiple Propagators, Initial Orbit Determination, and Maneuver Calculations.

/**
 * @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 { EpochUTC, Kilometers, RadiansPerSecond, Vector3D } from '../main.js';
import { NutationAngles } from './NutationAngles.js';
import { PrecessionAngles } from './PrecessionAngles.js';
export declare class Earth {
    private constructor();
    static readonly mu: number;
    static readonly radiusEquator: Kilometers;
    static readonly flattening: number;
    static readonly radiusPolar: Kilometers;
    static readonly radiusMean: Kilometers;
    static readonly eccentricitySquared: number;
    static readonly j2: number;
    static readonly j3: number;
    static readonly j4: number;
    static readonly j5: number;
    static readonly j6: number;
    static readonly rotation: Vector3D<RadiansPerSecond>;
    static smaToMeanMotion(semimajorAxis: Kilometers): RadiansPerSecond;
    /**
     * Converts revolutions per day to semi-major axis.
     * @param rpd - The number of revolutions per day.
     * @returns The semi-major axis value.
     */
    static revsPerDayToSma(rpd: number): number;
    static precession(epoch: EpochUTC): PrecessionAngles;
    static nutation(epoch: EpochUTC): NutationAngles;
    static smaToDrift(semimajorAxis: number): number;
    static smaToDriftDegrees(semimajorAxis: number): number;
    static driftToSemimajorAxis(driftRate: number): number;
    static driftDegreesToSma(driftRate: number): number;
    /**
     * Calculates the diameter of the Earth based on the satellite position.
     * @param satPos The position of the satellite.
     * @returns The diameter of the Earth.
     */
    static diameter(satPos: Vector3D): number;
    private static readonly zetaPoly_;
    private static readonly thetaPoly_;
    private static readonly zedPoly_;
    private static readonly moonAnomPoly_;
    private static readonly sunAnomPoly_;
    private static readonly moonLatPoly_;
    private static readonly sunElongPoly_;
    private static readonly moonRaanPoly_;
    private static readonly meanEpsilonPoly_;
}