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Merge remote-tracking branch 'origin/nr_ue_sib19_ta' into integration_2025_w50 (!3638)

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NR UE: calculate TA based on SIB19 information in NTN mode, if autonomous TA is not enabled

To achieve the goal, the hyper frame number (HFN) is introduced at the NR UE
PHY, MAC and RRC layers.

Besides this, we also implemented an orbit propagation to improve the accuracy
of N_UE_TA_adj, and a fix to keep the N_TA from RAR and MAC CE.

Fixes #981
This commit is contained in:
Jaroslava Fiedlerova
2025-12-08 12:04:31 +01:00
parent 91e7030cf8 92107b18fe
commit e44b17668c
30 changed files with 313 additions and 181 deletions
Download Patch File Download Diff File Expand all files Collapse all files
radio/rfsimulator/apply_channelmod.c
+40 -7
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@@ -99,21 +99,54 @@ void rxAddInput(const c16_t *input_sig,
double vel_sat_gnb = 0;
double acc_sat_gnb = 0;
if (channelDesc->modelid == SAT_LEO_TRANS) {
const double acc_sat_x = 0;
const double acc_sat_y = -w_sat * w_sat * radius_sat * sin(w_sat * t);
const double acc_sat_z = -w_sat * w_sat * radius_sat * cos(w_sat * t);
const double t5 = t + 5;
const double t10 = t + 10;
const double pos_gnb_x = 0;
const double pos_gnb_y = 0;
const double pos_gnb_z = radius_earth;
const double pos_sat_x5 = 0;
const double pos_sat_y5 = radius_sat * sin(w_sat * t5);
const double pos_sat_z5 = radius_sat * cos(w_sat * t5);
const double pos_sat_x10 = 0;
const double pos_sat_y10 = radius_sat * sin(w_sat * t10);
const double pos_sat_z10 = radius_sat * cos(w_sat * t10);
const double dir_sat_gnb_x = pos_gnb_x - pos_sat_x;
const double dir_sat_gnb_y = pos_gnb_y - pos_sat_y;
const double dir_sat_gnb_z = pos_gnb_z - pos_sat_z;
const double dir_sat_gnb_x5 = pos_gnb_x - pos_sat_x5;
const double dir_sat_gnb_y5 = pos_gnb_y - pos_sat_y5;
const double dir_sat_gnb_z5 = pos_gnb_z - pos_sat_z5;
const double dir_sat_gnb_x10 = pos_gnb_x - pos_sat_x10;
const double dir_sat_gnb_y10 = pos_gnb_y - pos_sat_y10;
const double dir_sat_gnb_z10 = pos_gnb_z - pos_sat_z10;
dist_sat_gnb = sqrt(dir_sat_gnb_x * dir_sat_gnb_x + dir_sat_gnb_y * dir_sat_gnb_y + dir_sat_gnb_z * dir_sat_gnb_z);
vel_sat_gnb = (vel_sat_x * dir_sat_gnb_x + vel_sat_y * dir_sat_gnb_y + vel_sat_z * dir_sat_gnb_z) / dist_sat_gnb;
acc_sat_gnb = (acc_sat_x * dir_sat_gnb_x + acc_sat_y * dir_sat_gnb_y + acc_sat_z * dir_sat_gnb_z) / dist_sat_gnb;
const double dist_sat_gnb5 = sqrt(dir_sat_gnb_x5 * dir_sat_gnb_x5 + dir_sat_gnb_y5 * dir_sat_gnb_y5 + dir_sat_gnb_z5 * dir_sat_gnb_z5);
const double dist_sat_gnb10 = sqrt(dir_sat_gnb_x10 * dir_sat_gnb_x10 + dir_sat_gnb_y10 * dir_sat_gnb_y10 + dir_sat_gnb_z10 * dir_sat_gnb_z10);
// calculate vel_sat_gnb and acc_sat_gnb, so the delay is correct for epoch_time, epoch_time + 5 seconds and epoch_time + 10 seconds
//
// dist_sat_gnb = dist_sat_gnb + 0 * vel_sat_gnb + 0 * acc_sat_gnb;
// dist_sat_gnb5 = dist_sat_gnb + 5 * vel_sat_gnb + 25 * acc_sat_gnb;
// dist_sat_gnb10 = dist_sat_gnb + 10 * vel_sat_gnb + 100 * acc_sat_gnb;
//
// vel_sat_gnb = (dist_sat_gnb5 - dist_sat_gnb) / 5 - 5 * acc_sat_gnb;
// acc_sat_gnb = (dist_sat_gnb10 - dist_sat_gnb) / 100 - vel_sat_gnb / 10;
//
// vel_sat_gnb = (dist_sat_gnb5 - dist_sat_gnb) / 5 - 5 * ((dist_sat_gnb10 - dist_sat_gnb) / 100 - vel_sat_gnb / 10);
vel_sat_gnb = 2 * (dist_sat_gnb5 - dist_sat_gnb) / 5 - (dist_sat_gnb10 - dist_sat_gnb) / 10;
acc_sat_gnb = (dist_sat_gnb10 - dist_sat_gnb) / 50 - (dist_sat_gnb5 - dist_sat_gnb) / 25;
// in the moment when the satellite disappears behind the horizon acc_sat_gnb might become negative, what is invalid
if (acc_sat_gnb < 0)
acc_sat_gnb = 0;
}
const double prop_delay = (dist_ue_sat + dist_sat_gnb) / c;
@@ -128,7 +161,7 @@ void rxAddInput(const c16_t *input_sig,
last_TS = TS;
LOG_I(HW, "Satellite orbit: time %f s, Position = (%f, %f, %f), Velocity = (%f, %f, %f)\n", t, pos_sat_x, pos_sat_y, pos_sat_z, vel_sat_x, vel_sat_y, vel_sat_z);
LOG_I(HW, "Uplink delay %f ms, Doppler shift UE->SAT %f kHz\n", prop_delay * 1000, f_Doppler_shift_ue_sat / 1000);
LOG_I(HW, "Satellite velocity towards gNB: %f m/s, acceleration towards gNB: %f m/s²\n", vel_sat_gnb, acc_sat_gnb);
LOG_I(HW, "Satellite velocity towards gNB: %f m/s, acceleration towards gNB: %f m/s²\n", -vel_sat_gnb, acc_sat_gnb);
}
const int samples_per_subframe = channelDesc->sampling_rate / 1000;
@@ -138,7 +171,7 @@ void rxAddInput(const c16_t *input_sig,
.sfn = (abs_subframe / 10 + 1) % 1024,
.subframe = 0,
.delay = 2 * dist_sat_gnb / (c * 4.072e-9),
.drift = 2 * -vel_sat_gnb / (c * 0.2e-9),
.drift = 2 * vel_sat_gnb / (c * 0.2e-9),
.accel = 2 * acc_sat_gnb / (c * 0.2e-10),
.position.X = pos_sat_x / 1.3,
.position.Y = pos_sat_y / 1.3,