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NR UE: introduce orbit propagation to improve N_UE_TA_adj accuracy

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Instead of trying to estimate N_UE_TA_adj with a second degree polynomial,
we introduce orbit propagation to calculate N_UE_TA_adj with higher accuracy.

When we receive the satellite ephemeris data consisting of the satellite position vector
and the satellite velocity vector, we calculate parameters for orbit propagation, assuming
a circular orbit in the plane created by the satellite position vector and the satellite
velocity vector. This is done in the function prepare_ue_sat_ta().

Every millisecond, we use these parameters together with the time since epoch to calculate
the satellite position on that orbit and from this the reound-trip-time between UE and the
satellite, what corresponds to N_UE_TA_adj. This is done in the function apply_ntn_timing_advance().
This commit is contained in:
Thomas Schlichter
2025-11-19 10:05:45 +01:00
committed by francescomani
parent 43722e6bac
commit 59af5e4ad2
8 changed files with 121 additions and 93 deletions
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executables/position_interface.h
-5
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@@ -22,11 +22,6 @@
#ifndef __POSITION_INTERFACE__H__
#define __POSITION_INTERFACE__H__
#include <executables/nr-softmodem-common.h>
#include <executables/softmodem-common.h>
#include "PHY/defs_nr_UE.h"
#include "executables/nr-uesoftmodem.h"
/* position configuration parameters name */
#define CONFIG_STRING_POSITION_X "x"
#define CONFIG_STRING_POSITION_Y "y"