/**
 * Class for representing two-line element set (TLE)
 * The two-line element set represents the ephemerides that
 * describe satellite positions.  TLEs are a standard
 * way of representing ephemerides
 *
 * Publicly-available ephemerides for most satellites are
 * kept and updated at www.space-track.org
 *
 */
import { SatRV } from './sgp4.js';
export { SatRV } from './sgp4.js';
export default class TLE {
    raw: Array<string>;
    name: string;
    satid: string;
    launch_year: number;
    epoch: Date;
    inclination: number;
    mean_motion: number;
    mean_motion_dot: number;
    mean_motion_dot_dot: number;
    launch_number: number;
    launch_piece: string;
    raan: number;
    bstar: number;
    elsetnum: number;
    eccen: number;
    arg_of_perigee: number;
    mean_anomaly: number;
    revnum: number;
    satrec: any;
    /**
     *
     * Construct TLE from lines. This accepts as input the traditional
     * 2-line TLE, or the 3-line version with the first line identifying
     * the name of the satellite
     *
     * @constructor
     * @param {*} lines Array of lines representing the TLE, or 1st line
     * @param {*} tline2 If lines passed in 1 at a time, this is the 2nd line
     * @param {*} tline3 If lines passed in 1 at a time, this 3rd line
     */
    constructor(lines: string | Array<string>, tline2?: string, tline3?: string);
    /**
     *
     * SGP4 propagator computes position and velocity of satellite at given
     * time in the TEME coordinate frame given input TLE ephemerides
     *
     * @param {*} thedate Date for which to compute position and velocity
     * @param {*} whichconst Earth parameter values, 'wgs84' or 'wgs72'.  If ommited, 'wgs84' is default
     * @returns {dict} Dictionary with 'r' member indicating position in meters in TEME frame and 'v' member indicating velocity in meters / second in TEME frame
     *
     */
    sgp4(thedate: Date, whichconst?: string): SatRV | undefined;
}
//# sourceMappingURL=tle.d.ts.map