import { Satellite } from '../sat';
/** An error output from an sgp4 computation */
export interface SGP4ErrorOutput {
    type: number;
    error: string;
}
/** A successful output from an sgp4 computation */
export interface SGP4Output {
    position: {
        x: number;
        y: number;
        z: number;
    };
    velocity: {
        x: number;
        y: number;
        z: number;
    };
}
/**
 *                             procedure sgp4
 *
 *  this procedure is the sgp4 prediction model from space command. this is an
 *    updated and combined version of sgp4 and sdp4, which were originally
 *    published separately in spacetrack report //3. this version follows the
 *    methodology from the aiaa paper (2006) describing the history and
 *    development of the code.
 *
 *  author        : david vallado                  719-573-2600   28 jun 2005
 *
 *  inputs        :
 *    tle  - initialised structure from sgp4init() call.
 *    tsince  - time since epoch (minutes)
 *
 *  outputs       :
 *    r           - position vector                     km
 *    v           - velocity                            km/sec
 *  return code - non-zero on error.
 *                   1 - mean elements, ecc >= 1.0 or ecc < -0.001 or a < 0.95 er
 *                   2 - mean motion less than 0.0
 *                   3 - pert elements, ecc < 0.0  or  ecc > 1.0
 *                   4 - semi-latus rectum < 0.0
 *                   5 - epoch elements are sub-orbital
 *                   6 - satellite has decayed
 *
 *  locals        :
 *    am          -
 *    axnl, aynl        -
 *    betal       -
 *    cosim   , sinim   , cosomm  , sinomm  , cnod    , snod    , cos2u   ,
 *    sin2u   , coseo1  , sineo1  , cosi    , sini    , cosip   , sinip   ,
 *    cosisq  , cossu   , sinsu   , cosu    , sinu
 *    delm        -
 *    delomg      -
 *    dndt        -
 *    eccm        -
 *    emsq        -
 *    ecose       -
 *    el2         -
 *    eo1         -
 *    eccp        -
 *    esine       -
 *    argpm       -
 *    argpp       -
 *    omgadf      -
 *    pl          -
 *    r           -
 *    rtemsq      -
 *    rdotl       -
 *    rl          -
 *    rvdot       -
 *    rvdotl      -
 *    su          -
 *    t2  , t3   , t4    , tc
 *    tem5, temp , temp1 , temp2  , tempa  , tempe  , templ
 *    u   , ux   , uy    , uz     , vx     , vy     , vz
 *    inclm       - inclination
 *    mm          - mean anomaly
 *    nm          - mean motion
 *    nodem       - right asc of ascending node
 *    xinc        -
 *    xincp       -
 *    xl          -
 *    xlm         -
 *    mp          -
 *    xmdf        -
 *    xmx         -
 *    xmy         -
 *    nodedf      -
 *    xnode       -
 *    nodep       -
 *    np          -
 *
 *  coupling      :
 *    getgravconst-
 *    dpper
 *    dspace
 *
 *  references    :
 *    hoots, roehrich, norad spacetrack report //3 1980
 *    hoots, norad spacetrack report //6 1986
 *    hoots, schumacher and glover 2004
 *    vallado, crawford, hujsak, kelso  2006
 * @param sat - the satellite object to propagate
 * @param tsince - the time since the epoch
 * @returns - the position and velocity of the satellite or an error report
 */
export declare function sgp4(sat: Satellite, tsince: number): SGP4ErrorOutput | SGP4Output;
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