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NR UE: provide velocity vector down to nr-ue.c, preparing for Doppler calculation

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This commit is contained in:
Thomas Schlichter
2025-12-19 16:38:59 +01:00
parent 479be40b30
commit b59bcaf494
6 changed files with 81 additions and 24 deletions
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openair2/LAYER2/NR_MAC_UE/config_ue.c
+33 -9
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@@ -279,29 +279,49 @@ static void prepare_ue_sat_ta(const NR_PositionVelocity_r17_t *sat_pos, ntn_timi
const double vel_sat_2 = vel_sat.X * vel_sat.X + vel_sat.Y * vel_sat.Y + vel_sat.Z * vel_sat.Z;
const double vel_mag = sqrt(vel_sat_2);
// calculate angular velocity in rad/ms
const double omega = vel_mag / (radius * 1000);
double omega; // angular velocity in rad/ms
position_t pos_sat_90; // sat position vector in 90° orbit
position_t vel_sat_90; // sat velocity vector in 90° orbit
// calculate sat position in 90° orbit
position_t pos_sat_90 = pos_sat;
if (vel_mag) {
const double scaling = radius / vel_mag;
// assuming circular orbit when satellite moves faster than 1000 m/s
// 1000 m/s are chosen because according to Wikipedia, this seems to be a reasonable minimal
// orbital velocity: https://en.wikipedia.org/wiki/Orbital_speed#Tangential_velocities_at_altitude
if (vel_mag > 1000) {
omega = vel_mag / (radius * 1000);
double scaling = radius / vel_mag;
pos_sat_90 = (position_t){vel_sat.X * scaling, vel_sat.Y * scaling, vel_sat.Z * scaling};
scaling = -vel_mag / radius;
vel_sat_90 = (position_t){pos_sat.X * scaling, pos_sat.Y * scaling, pos_sat.Z * scaling};
} else {
omega = 0;
pos_sat_90 = pos_sat;
vel_sat_90 = vel_sat;
}
LOG_I(NR_MAC,
"Satellite angular velocity = %e rad/ms, sat_pos = {%f, %f, %f}, sat_pos_90 = {%f, %f, %f}\n",
omega,
"Satellite orbital radius %f m, pos_sat_0 = {%f, %f, %f}, pos_sat_90 = {%f, %f, %f}\n"
"Satellite velocity %f m/s, angular velocity = %e rad/ms, vel_sat_0 = {%f, %f, %f}, vel_sat_90 = {%f, %f, %f}\n",
radius,
pos_sat.X,
pos_sat.Y,
pos_sat.Z,
pos_sat_90.X,
pos_sat_90.Y,
pos_sat_90.Z);
pos_sat_90.Z,
vel_mag,
omega,
vel_sat.X,
vel_sat.Y,
vel_sat.Z,
vel_sat_90.X,
vel_sat_90.Y,
vel_sat_90.Z);
ntn_ta->omega = omega;
ntn_ta->pos_sat_0 = pos_sat;
ntn_ta->pos_sat_90 = pos_sat_90;
ntn_ta->vel_sat_0 = vel_sat;
ntn_ta->vel_sat_90 = vel_sat_90;
}
// populate ntn_ta structure from mac
@@ -332,11 +352,15 @@ static void configure_ntn_ta(ntn_timing_advance_componets_t *ntn_ta, const NR_NT
ntn_ta->omega = 0;
ntn_ta->pos_sat_0 = (position_t){0, 0, 0};
ntn_ta->pos_sat_90 = (position_t){0, 0, 0};
ntn_ta->vel_sat_0 = (position_t){0, 0, 0};
ntn_ta->vel_sat_90 = (position_t){0, 0, 0};
}
} else { // Need R - Release if not present
ntn_ta->omega = 0;
ntn_ta->pos_sat_0 = (position_t){0, 0, 0};
ntn_ta->pos_sat_90 = (position_t){0, 0, 0};
ntn_ta->vel_sat_0 = (position_t){0, 0, 0};
ntn_ta->vel_sat_90 = (position_t){0, 0, 0};
}
// handle cellSpecificKoffset_r17
openair2/LAYER2/NR_MAC_UE/mac_defs.h
+6 -2
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@@ -552,10 +552,14 @@ typedef struct ntn_timing_advance_components {
// orbital angular velocity in rad/ms
double omega;
// satellite position at epoch time
// satellite position vector at epoch time
position_t pos_sat_0;
// satellite position at 90° orbit
// satellite position vector at 90° orbit
position_t pos_sat_90;
// satellite velocity vector at epoch time
position_t vel_sat_0;
// satellite velocity vector at 90° orbit
position_t vel_sat_90;
// N_common_ta_adj represents common round-trip-time between gNB and SAT received in SIB19 (ms)
double N_common_ta_adj;
openair2/LAYER2/NR_MAC_UE/nr_ue_scheduler.c
+2
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@@ -2855,6 +2855,8 @@ static void schedule_ntn_config_command(fapi_nr_dl_config_request_t *dl_config,
ntn_config_command_pdu->omega = mac->ntn_ta.omega;
ntn_config_command_pdu->pos_sat_0 = mac->ntn_ta.pos_sat_0;
ntn_config_command_pdu->pos_sat_90 = mac->ntn_ta.pos_sat_90;
ntn_config_command_pdu->vel_sat_0 = mac->ntn_ta.vel_sat_0;
ntn_config_command_pdu->vel_sat_90 = mac->ntn_ta.vel_sat_90;
ntn_config_command_pdu->N_common_ta_adj = mac->ntn_ta.N_common_ta_adj;
ntn_config_command_pdu->N_common_ta_drift = mac->ntn_ta.N_common_ta_drift;