Commit ac692073 authored by lengyelb's avatar lengyelb
Browse files

Merge branch 'Rel20_TS_28.541_CR1718_Ephemeris_orbital_parms_corrections_YANG'... 

Merge branch 'Rel20_TS_28.541_CR1718_Ephemeris_orbital_parms_corrections_YANG' into 'Integration_Rel20_SA5_167_YANG'

Rel20 ts 28.541 cr1718 ephemeris orbital parms corrections yang

See merge request !2129
parents f82495de 20fe9fd8

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

+8 −12
Original line number Diff line number Diff line
@@ -19,6 +19,7 @@ module _3gpp-nr-nrm-ntnfunction { 
    TTA, TTC). All rights reserved.";

  reference "3GPP TS 28.541";

  

  revision 2026-05-08 { reference "CR-1718"; }

  revision 2026-02-02 { reference "CR-1682 CR-1683"; } //Common in r19, r20

  revision 2025-03-27 { reference CR-1512; }

  revision 2025-02-17 { reference CR-1479 ; }
@@ -114,8 +115,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      }

      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).";

    }
@@ -125,8 +125,7 @@ module _3gpp-nr-nrm-ntnfunction { 
        range -524288..524287;

      }

      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).";

    }
@@ -137,8 +136,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      }

      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).";

    }
@@ -150,7 +148,7 @@ 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).";

    }
@@ -161,8 +159,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      }

      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).";

    }
@@ -173,8 +170,7 @@ module _3gpp-nr-nrm-ntnfunction { 
      }

      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).";

    }
@@ -213,7 +209,7 @@ 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;

        key idx;

        leaf idx { type uint32; }