From 20fe9fd814e7c57b644957f190c3ae5b50c9c109 Mon Sep 17 00:00:00 2001
From: scottma <mark.scott@ericsson.com>
Date: Fri, 8 May 2026 14:55:06 +0000
Subject: [PATCH] Remove all references to "NIMA" in the attribute definitions.

---
 yang-models/_3gpp-nr-nrm-ntnfunction.yang | 20 ++++++++------------
 1 file changed, 8 insertions(+), 12 deletions(-)

diff --git a/yang-models/_3gpp-nr-nrm-ntnfunction.yang b/yang-models/_3gpp-nr-nrm-ntnfunction.yang
index 53095b40..d554f219 100644
--- a/yang-models/_3gpp-nr-nrm-ntnfunction.yang
+++ b/yang-models/_3gpp-nr-nrm-ntnfunction.yang
@@ -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; }
-- 
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