Forecast of Conjunctions: 50 Latest Payloads vs. All (32628) Objects
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Time of Closest Approach (TCA), UTC
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NORAD ID 1
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Object Name 1
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NORAD ID 2
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Object Name 2
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Distance at TCA, km
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RIC Distance, km
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Rel.Speed
km/s
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2026-11-14 23:44:48.383
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55438
↓
↺
→
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STARLINK-5074
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101293
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OBJECT C
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3.958
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2.644, -0.397, -2.918
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15.0420
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2026-11-15 00:10:15.821
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101072
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FLOCK 4J 2
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101283
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OBJECT A
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2.964
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0.571, -1.022, -2.722
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14.2454
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2026-11-15 00:18:42.742
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61253
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STARLINK-11311
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101247
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STARLINK-38166
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4.111
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4.014, 0.537, 0.710
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12.2405
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2026-11-15 00:36:58.808
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21131
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SL-8 R/B
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101325
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HULIANWANG DIGUI 237
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4.988
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4.546, -0.903, 1.843
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13.2720
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2026-11-15 01:22:41.956
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813
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OPS 4467 B
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101276
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QIANFAN-261
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4.190
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-4.126, -0.118, 0.717
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14.6988
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2026-11-15 01:39:49.418
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42562
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DELTA 1 DEB
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101269
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QIANFAN-254
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4.770
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4.768, -0.050, -0.132
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14.3118
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2026-11-15 01:54:23.184
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36864
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METEOR 2-8 DEB
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101270
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QIANFAN-255
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1.969
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-0.003, -0.159, 1.963
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14.8298
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2026-11-15 01:57:08.848
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101067
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OBJECT H
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101294
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OBJECT D
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4.703
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0.996, -0.603, -4.557
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15.0497
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2026-11-15 02:21:14.875
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61055
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STARLINK-11268
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101256
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STARLINK-38457
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4.731
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4.728, -0.159, -0.037
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3.4997
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2026-11-15 02:45:08.482
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36864
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METEOR 2-8 DEB
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101270
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QIANFAN-255
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2.508
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1.509, -0.163, -1.996
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14.8156
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Our orbit propagation model is based on SGP4/SDP4 and uses data sourced from space-track.org. Object 1 and Object 2 are arranged by their NORAD ID (NORAD_CAT_ID).
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The "Within ellipsoid" option allows you to check if the predicted miss distance is within the RIC (Radial, In-track, Cross-track) ellipsoid, centered on either Object 1 or Object 2 at TCA, with specified semi-axis lengths.
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To exclude long-lasting conjunctions of ride-sharing satellites, you can use the "Relative Speed > 0.01 km/s" filter. Additionally, connected modules of ISS and CSS are not included in the forecast. Some ride-sharing satellites may also be temporarily excluded from the forecast.
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Gray background indicates a >1 km difference between the latest published position of a conjunction object and the position propagated from the TLE used for conjunction detection, indicating that the record may no longer be current.
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If comparison of the velocity vector and Keplerian orbital parameters from the latest published TLE with the corresponding values propagated from the TLE used for conjunction detection shows a deviation exceeding ±3× the background RMSE, indicating probable maneuvering, the following symbols identify the orbital parameter and direction of the probable change:
↑ ↓ - semimajor axis increase/decrease
↺ ↻ - inclination increase/decrease
→ ← - RAAN increase/decrease
↗ - probable maneuvering detected based on a propagated-versus-published velocity-vector difference exceeding 3× the background RMSE, while the semimajor axis, inclination, and RAAN deviations each remain within ±3× their respective background RMSEs.
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Please note that the "Selected Objects vs. All" option and Email Notifications are only available for registered users, with registration currently being free of charge.
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