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Satellite Orbit Computation

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Satellite Orbit Computation

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29 Sep 2010 (Updated )

Modified SGP4 code for GPS interface

newtonnu ( ecc,nu );
% ------------------------------------------------------------------------------
%
%                           function newtonnu
%
%  this function solves keplers equation when the true anomaly is known.
%    the mean and eccentric, parabolic, or hyperbolic anomaly is also found.
%    the parabolic limit at 168 is arbitrary. the hyperbolic anomaly is also
%    limited. the hyperbolic sine is used because it's not double valued.
%
%  author        : david vallado                  719-573-2600   27 may 2002
%
%  revisions
%    vallado     - fix small                                     24 sep 2002
%
%  inputs          description                    range / units
%    ecc         - eccentricity                   0.0  to
%    nu          - true anomaly                   -2pi to 2pi rad
%
%  outputs       :
%    e0          - eccentric anomaly              0.0  to 2pi rad       153.02 deg
%    m           - mean anomaly                   0.0  to 2pi rad       151.7425 deg
%
%  locals        :
%    e1          - eccentric anomaly, next value  rad
%    sine        - sine of e
%    cose        - cosine of e
%    ktr         - index
%
%  coupling      :
%    arcsinh     - arc hyperbolic sine
%    sinh        - hyperbolic sine
%
%  references    :
%    vallado       2007, 85, alg 5
%
% [e0,m] = newtonnu ( ecc,nu );
% ------------------------------------------------------------------------------

function [e0,m] = newtonnu ( ecc,nu );

        % ---------------------  implementation   ---------------------
        e0= 999999.9;
        m = 999999.9;
        small = 0.00000001;

        % --------------------------- circular ------------------------
        if ( abs( ecc ) < small  )
            m = nu;
            e0= nu;
          else
            % ---------------------- elliptical -----------------------
            if ( ecc < 1.0-small  )
                sine= ( sqrt( 1.0 -ecc*ecc ) * sin(nu) ) / ( 1.0 +ecc*cos(nu) );
                cose= ( ecc + cos(nu) ) / ( 1.0  + ecc*cos(nu) );
                e0  = atan2( sine,cose );
                m   = e0 - ecc*sin(e0);
              else
                % -------------------- hyperbolic  --------------------
                if ( ecc > 1.0 + small  )
                    if (ecc > 1.0 ) & (abs(nu)+0.00001 < pi-acos(1.0 /ecc))
                        sine= ( sqrt( ecc*ecc-1.0  ) * sin(nu) ) / ( 1.0  + ecc*cos(nu) );
                        e0  = asinh( sine );
                        m   = ecc*sinh(e0) - e0;
                      end
                  else
                    % ----------------- parabolic ---------------------
                    if ( abs(nu) < 168.0*pi/180.0  )
                        e0= tan( nu*0.5  );
                        m = e0 + (e0*e0*e0)/3.0;
                      end
                  end
              end
          end

        if ( ecc < 1.0  )
            m = rem( m,2.0 *pi );
            if ( m < 0.0  )
                m= m + 2.0 *pi;
              end
            e0 = rem( e0,2.0 *pi );
          end

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