Forecast of Conjunctions: 50 Latest Payloads vs. All (32410) 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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2026-10-27 11:35:18.237
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49442
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STARLINK-3098
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101018
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STARLINK-38257
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2.954
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2.413, -0.883, -1.458
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13.1497
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2026-10-27 11:39:52.842
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4157
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THORAD AGENA D DEB
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101145
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HAWK 16B
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2.878
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2.867, -0.242, -0.061
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3.6879
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2026-10-27 11:55:53.228
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51769
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STARLINK-3621
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101145
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HAWK 16B
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2.753
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-2.473, 0.532, 1.087
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13.6516
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2026-10-27 12:07:40.219
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36983
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TITAN 3C TRANSTAGE DEB
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101029
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STARLINK-38473
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2.964
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-2.061, 1.147, -1.795
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12.6152
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2026-10-27 12:29:02.673
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60933
↓
↻
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STARLINK-11207
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101011
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STARLINK-36774
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0.291
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-0.109, -0.147, -0.226
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12.8943
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2026-10-27 12:32:48.572
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42193
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COSMOS 1275 DEB
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101000
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SDA-NG-T1TL-418
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3.188
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0.957, -2.780, 1.232
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5.8698
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2026-10-27 12:59:22.304
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62093
↑
↻
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STARLINK-11345
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101011
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STARLINK-36774
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4.805
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3.799, -2.819, 0.844
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4.3824
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2026-10-27 12:59:54.270
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61785
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RTU MIREA 1
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101014
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STARLINK-38493
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1.504
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1.306, -0.367, -0.650
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13.4265
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2026-10-27 13:05:40.508
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61788
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OBJECT BF
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101015
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STARLINK-38475
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2.132
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-1.589, 0.717, 1.227
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13.2743
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2026-10-27 13:32:48.880
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39452
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SWARM A
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101031
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DRAGON CRS-35
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2.841
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1.776, -2.109, 0.683
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4.7024
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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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