ootk
Version:
Orbital Object Toolkit including Multiple Propagators, Initial Orbit Determination, and Maneuver Calculations.
100 lines (99 loc) • 3.7 kB
TypeScript
/**
* @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
*
* This class was ported from the python-sgp4 library by Brandon Rhodes. That library
* is licensed under the MIT license and he maintains the copyright for that work.
*
* 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 { OmmParsedDataFormat } from '../interfaces/OmmFormat.js';
import { Sgp4OpsMode } from '../enums/Sgp4OpsMode.js';
import { GreenwichMeanSiderealTime, SatelliteRecord, StateVectorSgp4, Vec3Flat } from '../types/types.js';
export declare enum Sgp4GravConstants {
wgs72old = "wgs72old",
wgs72 = "wgs72",
wgs84 = "wgs84"
}
export declare enum Sgp4Methods {
NEAR_EARTH = "n",
DEEP_SPACE = "d"
}
export declare class Sgp4 {
private static angle_;
private static asinh_;
static createSatrec(tleLine1: string, tleLine2: string, whichconst?: Sgp4GravConstants, opsmode?: Sgp4OpsMode): SatelliteRecord;
static createSatrecFromOmm(omm: OmmParsedDataFormat, whichconst?: Sgp4GravConstants, opsmode?: Sgp4OpsMode): SatelliteRecord;
private static cross_;
static days2mdhms(year: number, days: number): {
mon: number;
day: number;
hr: number;
min: number;
sec: number;
};
private static dot_;
static gstime(jdut1: number): GreenwichMeanSiderealTime;
static invjday(jd: number, jdfrac: number): {
year: number;
mon: number;
day: number;
hr: number;
min: number;
sec: number;
};
static jday(year: number | Date, mon?: number, day?: number, hr?: number, min?: number, sec?: number, ms?: number): {
jd: number;
jdFrac: number;
};
private static mag_;
private static newtonnu_;
static propagate(satrec: SatelliteRecord, tsince: number): StateVectorSgp4;
static rv2coe(r: Vec3Flat, v: Vec3Flat, mus: number): {
p: number;
a: number;
ecc: number;
incl: number;
omega: number;
argp: number;
nu: number;
m: number;
arglat: number;
truelon: number;
lonper: number;
};
/**
* Determines the sign of a given number.
* @param x - The input number to evaluate.
* @returns `-1.0` if the input number is less than `0.0`, otherwise `1.0`.
*/
private static sgn_;
/**
* Computes the hyperbolic sine of a given number.
*
* The hyperbolic sine is calculated using the formula:
* sinh(x) = (e^x - e^(-x)) / 2
* @param x - The input number for which to calculate the hyperbolic sine.
* @returns The hyperbolic sine of the input number.
*/
private static sinh_;
private static dpper_;
private static dscom_;
private static dsinit_;
private static dspace_;
private static getgravconst_;
private static initl_;
private static sgp4init_;
}