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Thomas Schlichter 59af5e4ad2 NR UE: introduce orbit propagation to improve N_UE_TA_adj accuracy
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().
2025-11-19 10:05:45 +01:00

39 lines
1.8 KiB
C

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#include "position_interface.h"
#include "executables/nr-uesoftmodem.h"
static void read_position_coordinates(char *sectionName, position_t *position)
{
paramdef_t position_params[] = POSITION_CONFIG_PARAMS_DEF;
int ret = config_get(config_get_if(), position_params, sizeofArray(position_params), sectionName);
AssertFatal(ret >= 0, "configuration couldn't be performed for position name: %s", sectionName);
}
void get_position_coordinates(int Mod_id, position_t *position)
{
AssertFatal(Mod_id < NB_UE_INST, "Mod_id must be less than NB_UE_INST. Mod_id:%d NB_UE_INST:%d", Mod_id, NB_UE_INST);
char positionName[64];
snprintf(positionName, sizeof(positionName), "position%d", Mod_id);
read_position_coordinates(positionName, position);
}