Index of Functions: A B C D E F G H I J K L M N O P Q R S T U V W X
Index Page evsgp4_c
Table of contents
Procedure Abstract Required_Reading Keywords Brief_I/O Detailed_Input | Detailed_Output Parameters Exceptions Files Particulars Examples | Restrictions Literature_References Author_and_Institution Version Index_Entries
#### Procedure
       evsgp4_c ( Evaluate "two-line" element data )

       void evsgp4_c ( SpiceDouble         et,
                       ConstSpiceDouble    geophs [8],
                       ConstSpiceDouble    elems  [10],
                       SpiceDouble         state  [6] )
#### Abstract
       Evaluate NORAD two-line element data for earth orbiting
       spacecraft. This evaluator uses algorithms as described
       in Vallado 2006 [4].
#### Required_Reading
       None.
#### Keywords
       EPHEMERIS
#### Brief_I/O
       VARIABLE  I/O  DESCRIPTION
       --------  ---  --------------------------------------------------
       et         I   Epoch in seconds past ephemeris epoch J2000.
       geophs     I   Geophysical constants
       elems      I   Two-line element data
       state      O   Evaluated state
#### Detailed_Input
       et          is the epoch in seconds past ephemeris epoch J2000
                   at which a state should be produced from the
                   input elements.

       geophs      is a collection of 8 geophysical constants needed
                   for computing a state. The order of these
                   constants must be:

                      geophs[0] = J2 gravitational harmonic for Earth.
                      geophs[1] = J3 gravitational harmonic for Earth.
                      geophs[2] = J4 gravitational harmonic for Earth.

                   These first three constants are dimensionless.

                      geophs[3] = KE: Square root of the GM for Earth where
                                  GM is expressed in Earth radii cubed per
                                  minutes squared.

                      geophs[4] = QO: High altitude bound for atmospheric
                                  model in km.

                      geophs[5] = SO: Low altitude bound for atmospheric
                                  model in km.

                      geophs[6] = RE: Equatorial radius of the earth in km.

                      geophs[7] = AE: Distance units/earth radius
                                  (normally 1).

                   Below are currently recommended values for these
                   items:

                      J2 =    1.082616e-3
                      J3 =   -2.53881e-6
                      J4 =   -1.65597e-6

                   The next item is the square root of GM for the Earth
                   given in units of earth-radii**1.5/Minute

                      KE =    7.43669161e-2

                   The next two items define the top and bottom of the
                   atmospheric drag model used by the type 10 ephemeris
                   type. Don't adjust these unless you understand the full
                   implications of such changes.

                      QO =  120.0e0
                      SO =   78.0e0

                   The ER value is the equatorial radius in km of the Earth
                   as used by NORAD.

                      ER = 6378.135e0

                   The value of AE is the number of distance units per
                   Earth radii used by the NORAD state propagation
                   software. The value should be 1 unless you've got a very
                   good understanding of the NORAD routine SGP4 and the
                   affect of changing this value.

                      AE =    1.0e0

       elems       is an array containing two-line element data
                   as prescribed below. The elements NDD6O and BSTAR
                   must already be scaled by the proper exponent stored
                   in the two line elements set. Moreover, the
                   various items must be converted to the units shown
                   here.

                      elems[ 0 ] = NDT20 in radians/minute**2
                      elems[ 1 ] = NDD60 in radians/minute**3
                      elems[ 2 ] = BSTAR
                      elems[ 3 ] = INCL  in radians
                      elems[ 4 ] = NODE0 in radians
                      elems[ 5 ] = ECC
                      elems[ 6 ] = OMEGA in radians
                      elems[ 7 ] = M0    in radians
                      elems[ 8 ] = N0    in radians/minute
                      elems[ 9 ] = EPOCH of the elements in seconds
                                   past ephemeris epoch J2000.
#### Detailed_Output
       state       is the state produced by evaluating the input elements
                   at the input epoch `et'. Units are km and km/sec relative
                   to the TEME reference frame.
#### Parameters
       None.
#### Exceptions
       1)  No checks are made on the reasonableness of the inputs.

       2)  If a problem occurs when evaluating the elements, an
           error is signaled by a routine in the call tree of this
           routine.
#### Files
       None.
#### Particulars
       This routine evaluates any NORAD two-line element sets for
       near-earth orbiting satellites using the algorithms described in
       Vallado 2006 [4].
#### Examples
       The numerical results shown for this example may differ across
       platforms. The results depend on the SPICE kernels used as
       input, the compiler and supporting libraries, and the machine
       specific arithmetic implementation.

       1) Suppose you have a set of two-line elements for the LUME-1
          cubesat. This example shows how you can use this routine
          together with the routine getelm_c to propagate a state to an
          epoch of interest.

          Use the meta-kernel shown below to load the required SPICE
          kernels.

             KPL/MK

             File name: evsgp4_ex1.tm

             This meta-kernel is intended to support operation of SPICE
             example programs. The kernels shown here should not be
             assumed to contain adequate or correct versions of data
             required by SPICE-based user applications.

             In order for an application to use this meta-kernel, the
             kernels referenced here must be present in the user's
             current working directory.

             The names and contents of the kernels referenced
             by this meta-kernel are as follows:

                File name           Contents
                ---------           ------------------------------------
                naif0012.tls        Leapseconds
                geophysical.ker     geophysical constants for evaluation
                                    of two-line element sets.

             The geophysical.ker is a PCK file that is provided with the
             CSPICE toolkit under the "/data" directory.

             \begindata

                KERNELS_TO_LOAD = ( 'naif0012.tls',
                                    'geophysical.ker'  )

             \begintext

             End of meta-kernel

          Example code begins here.

          /.
             Program evsgp4_ex1
          ./
          #include <stdio.h>
          #include <string.h>
          #include "SpiceUsr.h"

          int main( )
          {

             /.
             Local parameters.
             ./
             #define TIMSTR       "2020-05-26 02:25:00"
             #define PNAMLN       3
             #define TLELLN       70

             /.
             The LUME-1 cubesat is an Earth orbiting object; set
             the center ID to the Earth ID.
             ./
             #define CENTER       399

             /.
             Local variables.
             ./
             SpiceDouble          elems  [10];
             SpiceDouble          epoch;
             SpiceDouble          et;
             SpiceDouble          geophs [8];
             SpiceDouble          state  [6];

             SpiceInt             i;
             SpiceInt             n;

             /.
             These are the variables that will hold the constants
             required by evspg4_c. These constants are available from
             the loaded PCK file, which provides the actual values and
             units as used by NORAD propagation model.

                Constant   Meaning
                --------   ------------------------------------------
                J2         J2 gravitational harmonic for Earth.
                J3         J3 gravitational harmonic for Earth.
                J4         J4 gravitational harmonic for Earth.
                KE         Square root of the GM for Earth.
                QO         High altitude bound for atmospheric model.
                SO         Low altitude bound for atmospheric model.
                ER         Equatorial radius of the Earth.
                AE         Distance units/earth radius.
             ./
             SpiceChar            noadpn [8][PNAMLN] = { "J2", "J3", "J4", "KE",
                                                         "QO", "SO", "ER", "AE" };

             /.
             Define the Two-Line Element set for LUME-1.
             ./
             SpiceChar            tle    [2][TLELLN] = {
                        "1 43908U 18111AJ  20146.60805006  .00000806"
                                         "  00000-0  34965-4 0  9999",
                        "2 43908  97.2676  47.2136 0020001 220.6050 "
                                         "139.3698 15.24999521 78544" };

             /.
             Load the MK file that includes the PCK file that provides
             the geophysical constants required for the evaluation of
             the two-line elements sets and the LSK, as it is required
             by getelm_c to perform time conversions.
             ./
             furnsh_c ( "evsgp4_ex1.tm" );

             /.
             Retrieve the data from the kernel, and place it on
             the `geophs' array.
             ./
             for ( i = 0; i < 8; i++ )
             {
                bodvcd_c ( CENTER, noadpn[i], 1, &n, geophs+i );
             }

             /.
             Convert the Two Line Elements lines to the element sets.
             Set the lower bound for the years to be the beginning
             of the space age.
             ./
             getelm_c ( 1957, TLELLN, tle, &epoch, elems );

             /.
             Now propagate the state using evsgp4_c to the epoch
             of interest.
             ./
             str2et_c ( TIMSTR, &et );
             evsgp4_c ( et, geophs, elems, state );

             /.
             Display the results.
             ./
             printf( "Epoch   : %s\n", TIMSTR );
             printf( "Position: %15.8f %15.8f %15.8f\n",
                            state[0], state[1], state[2] );
             printf( "Velocity: %15.8f %15.8f %15.8f\n",
                            state[3], state[4], state[5] );

             return ( 0 );
          }

          When this program was executed on a PC/Linux/gcc/64-bit
          platform, the output was:

          Epoch   : 2020-05-26 02:25:00
          Position:  -4644.60403398  -5038.95025539   -337.27141116
          Velocity:     -0.45719025      0.92884817     -7.55917355
#### Restrictions
       None.
#### Literature_References
       [1]  F. Hoots and R. Roehrich, "Spacetrack Report #3: Models for
            Propagation of the NORAD Element Sets," U.S. Air Force
            Aerospace Defense Command, Colorado Springs, CO, 1980.

       [2]  F. Hoots, "Spacetrack Report #6: Models for Propagation of
            Space Command Element Sets,"  U.S. Air Force Aerospace
            Defense Command, Colorado Springs, CO, 1986.

       [3]  F. Hoots, P. Schumacher and R. Glover, "History of Analytical
            Orbit Modeling in the U. S. Space Surveillance System,"
            Journal of Guidance, Control, and Dynamics. 27(2):174-185,
            2004.

       [4]  D. Vallado, P. Crawford, R. Hujsak and T. Kelso, "Revisiting
            Spacetrack Report #3," paper AIAA 2006-6753 presented at the
            AIAA/AAS Astrodynamics Specialist Conference, Keystone, CO.,
            August 21-24, 2006.
#### Author_and_Institution
       M. Costa Sitja      (JPL)
#### Version
       -CSPICE Version 1.0.0, 05-NOV-2021 (MCS)
#### Index_Entries
       Evaluate NORAD two-line element data using SGP4.
#### Link to routine evsgp4_c source file evsgp4_c.c

    Fri Dec 31 18:41:06 2021