Commit 3b663846 authored by lengyelb's avatar lengyelb
Browse files

Merge branch 'Rel18_TS_28.541_CR1716_Ephemeris_orbital_parms_corrections_YANG'... 

Merge branch 'Rel18_TS_28.541_CR1716_Ephemeris_orbital_parms_corrections_YANG' into 'Integration_Rel18_SA5_167_YANG'

Rel18_TS_28.541_CR1716_Ephemeris_orbital_parms_corrections_YANG

See merge request !2127
parents 3f110b63 3aad78ab

yang-models/_3gpp-nr-nrm-ntnfunction.yang

+8 −12
Original line number Diff line number Diff line
@@ -18,6 +18,7 @@ module _3gpp-nr-nrm-ntnfunction { 
    TTA, TTC). All rights reserved.";

  reference "3GPP TS 28.541";

  

  revision 2026-05-06 { reference CR-1716 ; } 

  revision 2024-05-24 { reference CR-1273 ; } 

  

  feature NTNFunctionUnderSubNetwork {
@@ -116,8 +117,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      config false;

      default 0;

      units meter;

      description "Satellite orbital parameter: semi major axis alpha, 

        see NIMA TR 8350.2. 

      description "Satellite orbital parameter: semi major axis alpha. 

        Step of 4.249 * 10**-3 m. 

        Actual value = 6500000 + field value * (4.249 * 10**-3).";

    }
@@ -128,8 +128,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      }

      config false;

      default 0;

      description "Satellite orbital parameter: eccentricity e, 

        see NIMA TR 8350.2.

      description "Satellite orbital parameter: eccentricity e.

        Step 1.431 * 10**-8. 

        Actual value = field value * (1.431 * 10**-8).";

    }
@@ -141,8 +140,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      config false;

      default 0;

      units radian;

      description "Satellite orbital parameter: argument of periapsis omega, 

        see NIMA TR 8350.2. 

      description "Satellite orbital parameter: argument of periapsis omega. 

        Step of 2.341* 10**-8 rad. 

        Actual value = field value * (2.341* 10**-8).";

    }
@@ -155,7 +153,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      default 0;                

      units radian;

      description "Satellite orbital parameter: longitude of ascending node 

        OMEGA, see NIMA TR 8350.2. 

        omega. 

        Step of 2.341* 10**-8 rad.

        Actual value = field value * (2.341* 10**-8).";

    }
@@ -167,8 +165,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      config false;

      default 0;

      units radian;

      description "Satellite orbital parameter: inclination i, 

        see NIMA TR 8350.2. 

      description "Satellite orbital parameter: inclination i. 

        Step of 2.341* 10**-8 rad. 

        Actual value = field value * (2.341* 10**-8).";

    }
@@ -180,8 +177,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      config false;

      default 0;

      units radian;

      description "Satellite orbital parameter: Mean anomaly M at epoch time, 

        see NIMA TR 8350.2. 

      description "Satellite orbital parameter: Mean anomaly M at epoch time. 

        Step of 2.341* 10**-8 rad. 

        Actual value = field value * (2.341* 10**-8).";

    }
@@ -221,7 +217,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      

      list orbital {

        description "It indicates ephemeris is in orbital parameter ephemeris 

          format, as specified in NIMA TR 8350.2";

          format.";

        max-elements 1;

        config false;

        uses OrbitalGrp;